CN210191823U

CN210191823U - Shoulder-back type electric vertical take-off and landing aircraft and vertical electric vertical take-off and landing aircraft

Info

Publication number: CN210191823U
Application number: CN201920258484.8U
Authority: CN
Inventors: Shouli Yang; 杨守利
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-02-28
Filing date: 2019-02-28
Publication date: 2020-03-27
Anticipated expiration: 2029-02-28

Abstract

The utility model discloses an electronic VTOL aircraft of shoulder back of body formula and electronic VTOL aircraft of vertical type. The shoulder-carried electric vertical take-off and landing aircraft comprises a rack, a driving mechanism and an operating mechanism; the rack comprises a transverse supporting device and a vertical supporting device connected with the transverse supporting device, and two ends of the transverse supporting device are respectively connected with a driving mechanism; the control mechanism comprises a pushing device for pushing the driving mechanism and a control device for controlling the running direction of the aircraft.

Description

Shoulder-back type electric vertical take-off and landing aircraft and vertical electric vertical take-off and landing aircraft

Technical Field

The utility model belongs to the technical field of small aircraft makes, concretely relates to electronic VTOL aircraft of shoulder back of body formula and electronic VTOL aircraft of vertical type.

Background

At present, several flying motorcycle type aircrafts at home and abroad comprise an X-shaped bracket, wherein an electric power combination (a motor and a propeller) or an upper electric power combination and a lower electric power combination (two motors and two propellers) are respectively arranged at four endpoints. A seat is installed above the X-bracket intersection, on which a person can ride. The whole machine body generates an inclination angle to realize front-back left-right flying by simultaneously adjusting the rotating speeds of the front motor and the rear motor or the left motor and the right motor, and the turning is realized by generating a rotating speed difference to generate a torsion force by simultaneously adjusting the rotating speeds of the opposite angle motors. The inventor finds that the aircraft has the defects that the gravity center is higher than the whole aircraft body, the flight stability is poor, the safety is poor, the action reaction time is relatively long, and the flight action is not sensitive enough in the research and development process.

At present, the domestic flying vehicle similar to the scheme is provided with a cabin below the central point of the X axis, and the rest structures and control modes are consistent with the scheme. The inventor finds in the development process that although the aircraft solves the problems of center of gravity and safety, the aircraft also has the defects of relatively long action response time and insensitive flying action. Foreign countries also have aircrafts which form a circular big bracket through a net bracket or a plurality of Y-shaped structures. An electric power device is arranged at each intersection, the control mode is similar to the scheme, and the front-back left-right flying and turning flying are realized by simultaneously regulating and controlling a plurality of rotating speeds. The inventor finds that the aircraft has the defects of being too complex in structure, relatively long in flight action response time and not sensitive enough in flight action in the research and development process.

Also fuel powered aircraft at home and abroad. Two ends of the cross rod are respectively provided with a fuel engine to drive the propeller to fly, and the engine can tilt. The inventor discovers that the rotational speed control of the oil-driven system of the fuel-powered aircraft is difficult to be compared with an electric system, the flight stability is poor, and the operation system simply adjusts the tilting of the engine and needs two hands to act simultaneously.

SUMMERY OF THE UTILITY MODEL

In order to overcome the deficiencies of the prior art, the present disclosure provides a shoulder-carried electric vtol aircraft and an upright electric vtol aircraft.

The technical scheme adopted by the disclosure is as follows:

the shoulder-carried electric vertical take-off and landing aircraft comprises a frame, a driving mechanism and an operating mechanism;

the rack comprises a transverse supporting device and a vertical supporting device connected with the transverse supporting device, and two ends of the transverse supporting device are respectively connected with a driving mechanism;

the control mechanism comprises a pushing device for driving the driving mechanism and a control device for controlling the running direction of the aircraft.

The vertical electric vertical take-off and landing aircraft comprises a plurality of vertical shoulder-back small electric vertical take-off and landing aircraft, and cabins are arranged among the plurality of vertical shoulder-back small electric vertical take-off and landing aircraft; a longitudinal support rod is connected between every two adjacent racks, and a longitudinal connecting rod is connected between every two adjacent motor swing arms.

Through above-mentioned technical scheme, this disclosed beneficial effect is:

the aircraft provided by the disclosure has the advantages of simple structure, small and light fuselage, capability of flying in a narrow space and convenience in loading; the left and right groups of propellers can tilt forwards and backwards, so that the flying is flexible, the flying action response is sensitive and timely, and the operation and the control are very easy; the device can be controlled by one hand, the other hand can execute a work task, and the device can be free of control and fly in an unmanned remote control mode after being matched with a flight control module and a GPS positioning module; the system can be used for high mountain rescue, sea rescue, cargo transportation between ships, travel exploration, short-distance cargo transportation, police, patrol, duty-on and other scenes, and can be applied to the fields of civil use, police use, military use, engineering construction, field operation and the like.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this disclosure, are included to provide a further understanding of the disclosure, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the application and not to limit the disclosure.

FIG. 1 is a block diagram of an electric VTOL aerial vehicle of the shoulder-back type according to the present embodiment;

FIG. 2 is a block diagram of the two-shoulder electric VTOL aerial vehicle of this embodiment;

FIG. 3 is a block diagram of the electric VTOL aerial vehicle of the present example with three shoulders;

FIG. 4 is a block diagram of the four-shoulder electric VTOL aerial vehicle of the present example;

FIG. 5 is a block diagram of the electric VTOL aerial vehicle of the fifth embodiment;

fig. 6 is a structural view of the six-shoulder electric vtol aircraft of the present example.

Detailed Description

The present disclosure is further described with reference to the following drawings and examples.

Example one

In one embodiment, a shoulder-carried electric vertical take-off and landing aircraft is provided, and the aircraft includes a frame, a first driving mechanism and a second driving mechanism symmetrically disposed at two ends of the frame, and a control mechanism for controlling a direction of the aircraft, as shown in fig. 1.

The rack comprises a first cross bar 11 and a second cross bar 12 which are arranged horizontally and in parallel, and a first vertical support bar 13 and a second vertical support bar 14 which are arranged vertically and in parallel; the top end of the first vertical support rod 13 is fixedly connected with one end of the first cross rod 11, and the top end of the second vertical support rod 14 is fixedly connected with the other end of the first cross rod 11; bearings used for being connected with a driving mechanism are installed at two ends of the first cross rod 11; one end of the second cross bar 12 is connected with the lower part of the first vertical support bar 13, and the other end is connected with the lower part of the second vertical support bar 14; a seat (not shown in the figure) is mounted on the second cross bar 12, a safety belt (not shown in the figure) is mounted in the middle of the first vertical support bar 13 and the second vertical support bar 14, a third vertical support bar (not shown in the figure) which is inclined forward is arranged on the seat, the first vertical support bar 13 and the second vertical support bar 14 can extend downward and bend to the left rear and the right rear respectively, the third vertical support bar can extend downward and bend forward, and the three vertical support bars form a three-point undercarriage.

The first driving mechanism comprises a first motor 15, a first propeller 16, a first motor cross arm and a first motor swing arm 18; the first motor cross arm is composed of a first motor fixing plate 17 and a first shaft sleeve 10, the first motor fixing plate 17 is fixedly connected with the first shaft sleeve 10, two first motors 15 are symmetrically installed at the upper part and the lower part of one end, far away from the first shaft sleeve, of the first motor fixing plate 17, an output shaft of each first motor 15 is connected with a first propeller 16, and one end, far away from the first motor fixing plate, of the first shaft sleeve 10 is sleeved on a bearing at one end of a first cross rod 11; one end of the first motor swing arm 18 is fixedly connected with the first shaft sleeve 10; the other end of the first motor swing arm 18 is connected with a first vertical connecting rod 19.

The structure of the second driving mechanism is similar to that of the first driving mechanism, and specifically, the second driving mechanism comprises a second motor 115, a second propeller 116, a second motor cross arm and a second motor swing arm 118; the second motor cross arm is composed of a second motor fixing plate 117 and a second shaft sleeve 110, the second motor fixing plate 117 is fixedly connected with the second shaft sleeve 110, two second motors 115 are symmetrically installed at the upper part and the lower part of one end, far away from the second shaft sleeve, of the second motor fixing plate 117, an output shaft of each second motor 115 is connected with a second propeller 116, and one end, far away from the second motor fixing plate, of the second shaft sleeve 110 is sleeved on a bearing at the other end of the first cross rod 11; one end of the second motor swing arm 118 is fixedly connected with the second shaft sleeve 110; the other end of the second motor swing arm 118 is connected to a second vertical link 119.

The control mechanism comprises a first vertical connecting rod 19, a second vertical connecting rod 119, a transverse connecting rod 111, a control rod 112, a control rod longitudinal shaft 113 and a control rod transverse shaft 114, wherein one end of the first vertical connecting rod 19 is connected with the first motor swing arm 18, the other end of the first vertical connecting rod is connected with one end of the transverse connecting rod 111, one end of the second vertical connecting rod 119 is connected with the second motor swing arm 118, and the other end of the second vertical connecting rod 119 is connected with the other end of the transverse connecting rod 111; one end of the control lever longitudinal shaft 113 is connected with the middle of the transverse connecting rod 111, the other end of the control lever longitudinal shaft 113 is connected with the control lever 112, a control lever longitudinal shaft sleeve 120 is arranged in the middle of the control lever longitudinal shaft 113, control lever transverse shafts 114 are fixedly connected to two sides of the control lever longitudinal shaft sleeve 120 respectively, and the other end of the control lever transverse shaft 114 is inserted into a control lever transverse shaft sleeve 121 arranged at the lower end of the vertical supporting rod.

The working process of the shoulder-back type electric vertical take-off and landing aircraft provided by the embodiment is as follows:

when driving, the driver backs the aircraft on the back and fastens the safety belt, so that the man and the machine are integrated, and the control lever 112 is held by a single hand; when the aircraft is static, the rotating surfaces of the left and right groups of propellers connected with the motor face upwards, the motor is started to gradually increase the accelerator of the electronic speed regulator of the motor, the airflow generated by the relative rotation of the upper and lower propellers is vertically downward, the propellers generate a reaction force relative to the aircraft, namely an upward lift force, and the propellers generate enough lift force to drive the aircraft to vertically take off and rise after the motor obtains enough rotating speed; after the driver sits on the seat and pushes the operating rod 112 forward to a certain angle gradually after the driver ascends to a certain height, at the moment, the operating rod 112 presses the operating rod longitudinal axis 113 to tilt around the operating rod transverse axis 114, the other end of the operating rod longitudinal axis 114 ascends to lift the transverse connecting rod 111, the transverse connecting rod 111 pushes the first vertical connecting rod 19 and the second vertical connecting rod 119 upwards, the first vertical connecting rod 19 pushes the first motor swing arm 18, the second vertical connecting rod 119 pushes the second motor swing arm 118, and the first motor swing arm 18 drives the first motor cross arm 17 to tilt around the first cross rod 11 on the rack, so that the propeller surface of the first propeller 16 also tilts forward gradually; the second motor swing arm 118 drives the second motor cross arm 117 to tilt around the first cross rod 11 on the rack, so that the propeller surface of the second propeller 116 also tilts forward gradually; the air flow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to enable the aircraft to keep the height and fly forwards. The size of the tilting angle of the propeller surface is determined by the size of the activity angle of the operating lever; when the control rod 112 is pushed leftwards, the right end of the transverse connecting rod is driven to ascend, the left end of the transverse connecting rod descends, the paddle surface of the right propeller is driven to incline forwards, the paddle surface of the left propeller inclines backwards, and the aircraft turns leftwards in the original position until the control rod is pulled back to the original point; the control rod can move in a front-back and left-right direction, the propeller planes on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the pitch angle of the propeller planes on the right side is larger than that of the propeller planes on the left side and is slightly smaller when the aircraft is pushed forwards leftwards and forwards, so that the aircraft flies forwards and turns leftwards simultaneously, the aircraft can fly forwards and turns rightwards simultaneously when the control rod is pushed forwards and rightwards, and the aircraft can fly backwards and turn leftwards or rightwards simultaneously when the control rod is pulled leftwards and backwards.

The shoulder-carried electric vertical take-off and landing aircraft provided by the embodiment further comprises a control system, wherein the control system comprises a flight control module, a GPS (global positioning system) positioning module, a wireless communication module and a battery module, the flight control module is respectively connected with the first motor 15 and the second motor 115 and used for controlling the first motor 15 and the second motor 115 to work, and the GPS positioning module is connected with the flight control module and used for collecting position information of the aircraft; the wireless communication module is connected with the flight control module and used for receiving a remote control instruction, and the flight control module controls the aircraft to fly according to the received control instruction; the battery module is used for providing power for the whole aircraft and can adopt a battery pack.

Example two

The second embodiment provides a shoulder-carried electric vertical take-off and landing aircraft, which includes a frame, a first driving mechanism and a second driving mechanism symmetrically disposed at two ends of the frame, and a control mechanism for controlling the direction of the aircraft, as shown in fig. 2.

The rack comprises a first cross bar 21 and a second cross bar 22 which are arranged transversely and mutually in parallel, a first longitudinal bar 222, a second longitudinal bar 223, a third longitudinal bar 224 and a fourth longitudinal bar 225 which are arranged longitudinally and mutually in parallel, and a first vertical support bar 23 and a second vertical support bar 24 which are arranged vertically and mutually in parallel; the first vertical rod 222 and the third vertical rod 224 are respectively perpendicular to the first vertical support rod 23, one end of the first vertical rod 222 is connected with one end of the first cross rod 21, the other end of the first vertical rod is connected with the top end of the first vertical support rod 23, and the bottom end of the first vertical support rod 23 is connected with one end of the third vertical rod 224; the second vertical rod 223 and the fourth vertical rod 225 are respectively perpendicular to the second vertical support rod 24, one end of the second vertical rod 223 is connected with the other end of the first cross rod 21, the other end of the second vertical rod 223 is connected with the top end of the second vertical support rod 24, and the bottom end of the second vertical support rod 24 is connected with one end of the fourth vertical rod 225; the second cross bars 22 are respectively connected between the lower ends of the first vertical supporting bar 23 and the second vertical supporting bar 24; a seat (not shown in the figure) is mounted on the second cross rod 22 between the lower ends of the first vertical support rod 23 and the second vertical support rod 24, a safety belt (not shown in the figure) is mounted in the middle of the first vertical support rod 23 and the second vertical support rod 24, a third vertical support rod (not shown in the figure) which is obliquely arranged forward is arranged on the seat, the first vertical support rod 23 and the second vertical support rod 24 can be extended downward and bent backward and backward to the left respectively, the third vertical support rod can be extended downward and bent forward, and the three vertical support rods form a three-point landing gear.

The first driving mechanism comprises a first motor 25, a first propeller 26, a first motor cross arm and a first motor swing arm 28; the first motor cross arm consists of a first motor fixing plate 27 and a first shaft sleeve 20, the first motor fixing plate 27 is fixedly connected with the first shaft sleeve 20, two first motors 25 are symmetrically arranged at the upper part and the lower part of one end, far away from the first shaft sleeve, of the first motor fixing plate 27, the output shaft of each first motor 25 is connected with a first propeller 26, and one end, far away from the first motor fixing plate, of the first shaft sleeve 20 is sleeved on a bearing at one end of a first cross rod 21; one end of the first motor swing arm 28 is fixedly connected with the first shaft sleeve 20; the other end of the first motor swing arm 28 is connected to a first vertical link 29.

The structure of the second driving mechanism is similar to that of the first driving mechanism, and specifically, the second driving mechanism comprises a second motor 215, a second propeller 216, a second motor cross arm and a second motor swing arm 218; the second motor cross arm is composed of a second motor fixing plate 217 and a second shaft sleeve 210, the second motor fixing plate 217 is fixedly connected with the second shaft sleeve 210, two second motors 215 are symmetrically installed at the upper part and the lower part of one end, far away from the second shaft sleeve, of the second motor fixing plate 217, the output shaft of each second motor 215 is connected with a second propeller 216, and one end, far away from the second motor fixing plate, of the second shaft sleeve 210 is sleeved on a bearing at the other end of the first cross rod 21; one end of the second motor swing arm 218 is fixedly connected with the second shaft sleeve 210; the other end of the second motor swing arm 218 is connected to a second vertical link 219.

The control mechanism comprises a first vertical connecting rod 29, a second vertical connecting rod 219, a transverse connecting rod 211, a control rod 212, a control rod longitudinal shaft 213 and a control rod transverse shaft 214, one end of the first vertical connecting rod 29 is connected with the first motor swing arm 28, the other end of the first vertical connecting rod is connected with one end of the transverse connecting rod 211, one end of the second vertical connecting rod 219 is connected with the second motor swing arm 218, and the other end of the second vertical connecting rod 219 is connected with the other end of the transverse connecting rod 211; one end of the control lever longitudinal shaft 213 is connected with the middle of the transverse link 211, the other end is connected with the control lever 212, a control lever longitudinal shaft sleeve 220 is arranged in the middle of the control lever longitudinal shaft 213, control lever transverse shafts 214 are fixedly connected to both sides of the control lever longitudinal shaft sleeve 220, the other end of the control lever transverse shaft 214 is inserted into the control lever transverse shaft sleeve 221, and the two control lever transverse shaft sleeves 221 are fixedly connected with the other ends of the third longitudinal rod 224 and the fourth longitudinal rod 225 respectively.

The working process of the shoulder-back type electric vertical take-off and landing aircraft provided by the second embodiment is as follows:

when driving, the driver backs the aircraft on the back and fastens the safety belt, so that the man and the machine are integrated, and only one hand holds the operating rod 212; when the motor is static, the rotating surfaces of the left and right groups of propellers connected with the motor face upwards, the motor is started to gradually increase the accelerator of the electronic speed regulator of the motor, the airflow generated by the relative rotation of the upper and lower propellers is vertically downward, the propellers generate a reaction force relative to the aircraft and an upward lift force, and the propellers generate enough lift force to drive the aircraft to vertically take off and ascend after the motor obtains enough rotating speed; after the driver sits on the seat and pushes the operating rod 212 forward to a certain angle gradually after the driver ascends to a certain height, at the moment, the operating rod 212 presses the operating rod longitudinal shaft 213 to tilt around the operating rod transverse shaft 214, one end of the operating rod longitudinal shaft 213 ascends to lift the transverse connecting rod 211, the transverse connecting rod 211 pushes the first vertical connecting rod 29 and the second vertical connecting rod 219 upwards, the first vertical connecting rod 29 pushes the first motor swing arm 28, the second vertical connecting rod 219 pushes the second motor swing arm 218, and the first motor swing arm 28 drives the first motor cross arm 27 to tilt around the first cross rod 21 on the rack, so that the propeller surface of the first propeller 26 also tilts forward gradually; the second motor swing arm 218 drives the second motor cross arm 217 to tilt around the first cross rod 21 on the rack, so that the propeller surface of the second propeller 216 also tilts forwards gradually; the air flow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to enable the aircraft to keep the height and fly forwards. The size of the tilting angle of the propeller surface is determined by the size of the activity angle of the operating lever; when the control rod 212 is pushed leftwards, the right end of the transverse connecting rod is driven to ascend, the left end of the transverse connecting rod descends, the propeller surface of the right propeller is driven to incline forwards, the propeller surface of the left propeller inclines backwards, and the aircraft turns leftwards in the original position until the control rod is pulled back to the original point; the control rod can move in a front-back and left-right direction, the propeller planes on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the pitch angle of the propeller planes on the right side is larger than that of the propeller planes on the left side and is slightly smaller when the aircraft is pushed forwards leftwards and forwards, so that the aircraft flies forwards and turns leftwards simultaneously, the aircraft can fly forwards and turns rightwards simultaneously when the control rod is pushed forwards and rightwards, and the aircraft can fly backwards and turn leftwards or rightwards simultaneously when the control rod is pulled leftwards and backwards.

The shoulder-back type electric vertical take-off and landing aircraft provided by the second embodiment further comprises a control system, wherein the control system comprises a flight control module, a GPS (global positioning system) positioning module, a wireless communication module and a battery module, the flight control module is respectively connected with the first motor 25 and the second motor 215 and is used for controlling the first motor 25 and the second motor 215 to work, and the GPS positioning module is connected with the flight control module and is used for collecting position information of the aircraft; the wireless communication module is connected with the flight control module and used for receiving remote control instructions, and the flight control module controls the aircraft to fly according to the received control instructions. The battery module is used for providing power for the whole aircraft and can adopt a battery pack.

EXAMPLE III

In a third embodiment, a shoulder-carried electric vertical take-off and landing aircraft is provided, where the aircraft includes a frame, a first driving mechanism and a second driving mechanism symmetrically disposed at two ends of the frame, and a control mechanism for controlling the first driving mechanism and the second driving mechanism, as shown in fig. 3.

The frame comprises a first frame shaft sleeve 310, a second frame shaft sleeve 329, a shaft sleeve fixing beam 326, a first transverse rod 31 and a second transverse rod 32 which are transversely arranged in parallel, a first shaft sleeve longitudinal arm 322, a second shaft sleeve longitudinal arm 323, a third shaft sleeve longitudinal arm 324 and a fourth shaft sleeve longitudinal arm 325 which are longitudinally arranged in parallel, and a first vertical supporting rod 33 and a second vertical supporting rod 34 which are vertically arranged in parallel.

Specifically, the first rack shaft sleeve 310 is sleeved on a first motor cross arm 37 of the first driving mechanism, the second rack shaft sleeve 329 is sleeved on a second motor cross arm 317 of the second driving mechanism, a shaft sleeve fixing beam 326 is connected between the first rack shaft sleeve 310 and the second rack shaft sleeve 329, and the left and right rack shaft sleeves are fixedly connected through the shaft sleeve fixing beam 326; the first shaft sleeve longitudinal arm 322 and the third shaft sleeve longitudinal arm 324 are respectively perpendicular to the first vertical support rod 33 and the first cross bar 31, one end of the first shaft sleeve longitudinal arm 322 is connected with the first rack shaft sleeve 310, and the other end is connected with one end of the first cross bar 31; one end of the first cross bar 31 is further connected with the top end of the first vertical support bar 33, the third shaft sleeve longitudinal arm 324 is connected with the bottom end of the first vertical support bar 33, and the other end of the third shaft sleeve longitudinal arm 324 is connected with the control lever transverse shaft sleeve 321; the second shaft sleeve longitudinal arm 323 and the fourth shaft sleeve longitudinal arm 325 are respectively perpendicular to the second vertical support rod 34 and the first cross bar 31, one end of the second shaft sleeve longitudinal arm 323 is connected with the second rack shaft sleeve 329, and the other end is connected with the other end of the first cross bar 31; the other end of the first cross bar 31 is further connected with the top end of the second vertical support bar 34, the fourth shaft sleeve longitudinal arm 325 is connected with the bottom end of the second vertical support bar 34, and the other end of the fourth shaft sleeve longitudinal arm 325 is connected with an operating lever transverse shaft sleeve 321; one end of the second cross bar 32 is connected with the lower end of the first vertical support bar 33, and the other end is connected with the lower end of the second vertical support bar 34; the first cross bar 31 is further symmetrically provided with an L-shaped first corner swing arm 327 and a second corner swing arm 328; a seat (not shown in the figure) is mounted on the second cross bar 32, a safety belt (not shown in the figure) is mounted in the middle of the first vertical support bar 33 and the second vertical support bar 34, a third vertical support bar (not shown in the figure) which is obliquely arranged forward is arranged on the seat, the first vertical support bar 33 and the second vertical support bar 34 can extend downwards and bend towards the left rear and the right rear respectively, the third vertical support bar can extend downwards and bend forwards, and the three vertical support bars form a three-point undercarriage.

The first driving mechanism comprises a first motor 35, a first propeller 36, a first motor cross arm 37 and a first motor swing arm 38; a motor fixing plate is arranged at one end of the first motor cross arm 37, two first motors 35 are symmetrically arranged on the motor fixing plate of the first motor cross arm 37 from top to bottom, an output shaft of each first motor 35 is connected with a first propeller 36, and the other end of the first motor cross arm 37 penetrates through a first rack shaft sleeve 310 to be connected with one end of a first motor swing arm 38; the other end of the first motor swing arm 38 is connected to a first longitudinal link 330.

The structure of the second driving mechanism is similar to that of the first driving mechanism, and specifically, the second driving mechanism comprises a second motor 315, a second propeller 316, a second motor cross arm 317 and a second motor swing arm 318; a motor fixing plate is arranged at one end of the second motor cross arm 317, two second motors 315 are symmetrically arranged on the motor fixing plate of the second motor cross arm 317 from top to bottom, an output shaft of each second motor 315 is connected with a second propeller 316, and the other end of the second motor cross arm 317 penetrates through a second rack shaft sleeve 329 to be connected with one end of a second motor swing arm 318; the other end of the second motor swing arm 318 is connected to a second longitudinal link 331.

The control mechanism comprises a first longitudinal connecting rod 330, a second longitudinal connecting rod 331, a first vertical connecting rod 39, a second vertical connecting rod 319, a transverse connecting rod 311, a control rod 312, a control rod longitudinal shaft 313 and a control rod transverse shaft 314, one end of the first longitudinal connecting rod 330 is connected with the first motor swing arm 38, the other end of the first longitudinal connecting rod 330 is connected with the top end of the first vertical connecting rod 39 through a first corner swing arm 327, the bottom end of the first vertical connecting rod 39 is connected with one end of the transverse connecting rod 311, one end of the second longitudinal connecting rod 331 is connected with the second motor swing arm 318, the other end of the second longitudinal connecting rod 331 is connected with the top end of the second vertical connecting rod 319 through a second corner swing arm 328, and the bottom end of the second vertical connecting rod 319 is connected; one end of the control lever longitudinal shaft 313 is connected with the middle of the transverse connecting rod 311, the other end is connected with the control lever 312, a control lever longitudinal shaft sleeve 320 is arranged in the middle of the control lever longitudinal shaft 313, control lever transverse shafts 314 are fixedly connected to two sides of the control lever longitudinal shaft sleeve 320 respectively, and the other end of the control lever transverse shaft 314 is inserted into the control lever transverse shaft sleeve 321.

The third embodiment provides a working process of the shoulder-back type electric vertical take-off and landing aircraft, which is as follows:

when driving, the driver backs the aircraft on the back and fastens the safety belt, so that the man and the machine are integrated, and only one hand holds the operating lever 312; when the motor is static, the rotating surfaces of the left and right groups of propellers connected with the motor face upwards, the motor is started to gradually increase the accelerator of the electronic speed regulator of the motor, the airflow generated by the relative rotation of the upper and lower propellers is vertically downward, the propellers generate a reaction force relative to the aircraft and an upward lift force, and the propellers generate enough lift force to drive the aircraft to vertically take off and ascend after the motor obtains enough rotating speed; after the driver sits on the seat and gradually pushes the operating rod 312 forward to a certain angle after the driver ascends to a certain height, at the moment, the operating rod 312 presses the operating rod longitudinal shaft 313 to tilt around the operating rod transverse shaft 314, the other end of the operating rod longitudinal shaft 314 ascends to lift the transverse connecting rod 311, the transverse connecting rod 311 pushes the first vertical connecting rod 39 and the second vertical connecting rod 319 upwards, the first vertical connecting rod 39 pushes the first motor swing arm 38 through the first longitudinal connecting rod 330 and the first corner swing arm 327, the second vertical connecting rod 319 pushes the second motor swing arm 318 through the second longitudinal connecting rod 331 and the second corner swing arm 328, and the first motor swing arm 38 drives the first motor cross arm 37 to tilt in the first frame shaft sleeve 310, so that the propeller surface of the first propeller 36 also gradually tilts forward; the second motor swing arm 318 drives the second motor cross arm 317 to tilt in the second rack shaft sleeve 329, so that the propeller surface of the second propeller 316 also tilts forward gradually; the air flow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to enable the aircraft to keep the height and fly forwards. The size of the tilting angle of the propeller surface is determined by the size of the activity angle of the operating lever; when the control rod 312 is pushed leftwards, the right end of the transverse connecting rod is driven to ascend, the left end of the transverse connecting rod is driven to descend, the paddle surface of the right propeller is driven to incline forwards, the paddle surface of the left propeller inclines backwards, and the aircraft turns leftwards in the original position until the control rod is pulled back to the original point; the control rod can move in a front-back and left-right direction, the propeller planes on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the pitch angle of the propeller planes on the right side is larger than that of the propeller planes on the left side and is slightly smaller when the aircraft is pushed forwards leftwards and forwards, so that the aircraft flies forwards and turns leftwards simultaneously, the aircraft can fly forwards and turns rightwards simultaneously when the control rod is pushed forwards and rightwards, and the aircraft can fly backwards and turn leftwards or rightwards simultaneously when the control rod is pulled leftwards and backwards.

The shoulder-carried electric vertical take-off and landing aircraft provided by the third embodiment further comprises a control system, wherein the control system comprises a flight control module, a GPS (global positioning system) positioning module, a wireless communication module and a battery module, the flight control module is respectively connected with the first motor 35 and the second motor 315 and used for controlling the first motor 35 and the second motor 315 to work, and the GPS positioning module is connected with the flight control module and used for collecting the position information of the aircraft; the wireless communication module is connected with the flight control module and used for receiving remote control instructions, and the flight control module controls the aircraft to fly according to the received control instructions. The battery module is used for providing power for the whole aircraft and can adopt a battery pack.

Example four

In a fourth embodiment, an electric shoulder-carried vertical take-off and landing aircraft is provided, where the aircraft includes a frame, a first driving mechanism and a second driving mechanism symmetrically disposed at two ends of the frame, and a control mechanism for controlling the first driving mechanism and the second driving mechanism, as shown in fig. 4.

The frame comprises a first cross bar 41, a longitudinal arm 42, a vertical supporting bar 43 and a second cross bar 44, wherein bearings are respectively arranged at two ends of the first cross bar 41; one end of the longitudinal arm 42 is connected with the middle of the first cross bar 41, the other end of the longitudinal arm is connected with the top end of the vertical support bar 43, the second cross bar is arranged in the middle of the vertical support bar 43, a seat 49 is installed at the bottom end of the vertical support bar 43, a safety belt (not shown in the figure) is installed on the second cross bar 44, a vertical support bar (not shown in the figure) which is arranged obliquely forward and can extend downward and bend forward is arranged on the seat 49, the vertical support bar 43 can be extended downward into two pieces and bend backward and backward, and the three pieces of vertical support bar form a three-point undercarriage.

The first driving mechanism comprises a first motor 45, first propellers 46 and a first motor cross arm, the first motor cross arm consists of a first motor fixing plate 47 and a first shaft sleeve 48, the first motor fixing plate 47 is fixedly connected with the first shaft sleeve 48, two first motors 45 are symmetrically arranged at the upper part and the lower part of one end, far away from the first shaft sleeve, of the first motor fixing plate 47, an output shaft of each first motor 45 is connected with the first propeller 46, and one end, far away from the first motor fixing plate, of the first shaft sleeve 48 is sleeved on a bearing at one end of the first cross rod 41; the first sleeve 48 is connected to a connecting member 410, and the connecting member 410 may be a cable, a belt, a chain, or the like.

The structure of the second driving mechanism is similar to that of the first driving mechanism, and specifically, the second driving mechanism comprises a second motor 415, a second propeller 416 and a second motor cross arm; the second motor cross arm is composed of a second motor fixing plate 417 and a second shaft sleeve 418, the second motor fixing plate 417 is fixedly connected with the second shaft sleeve 418, two second motors 415 are symmetrically installed on the upper portion and the lower portion of one end, far away from the second shaft sleeve, of the second motor fixing plate 417, the output shaft of each second motor 415 is connected with a second propeller 416, and one end, far away from the second motor fixing plate, of the second shaft sleeve 418 is sleeved on a bearing at the other end of the first cross rod 41; the second bushing 418 is connected to a connecting member 410, and the connecting member 410 may be a cable, a belt, a chain, or the like.

The control mechanism comprises a connecting piece 410, a first pulley block 411, a second pulley block 419, a control lever 412, a control lever longitudinal shaft 413, a control lever transverse shaft 414, a first pulley block fixing rod 420 and a connecting piece fixing rod 421, wherein the first pulley block fixing rod 420 is fixedly connected to the top of the vertical support rod 43, the first pulley block 411 is composed of two first pulleys arranged at two ends of the first pulley block fixing rod 420, the second pulley block 419 is composed of two second pulleys arranged on the vertical support rod 43, the control lever 412 is connected with one end of the control lever transverse shaft 414, a control lever transverse shaft sleeve 423 is connected to the other end of the control lever transverse shaft 414, one end of the control lever longitudinal shaft 413 is inserted into the control lever longitudinal shaft sleeve 422, and the control lever longitudinal shaft sleeve 422 is arranged at the lower end of the vertical support rod 43, the other end of the control lever longitudinal shaft 413 is fixedly connected with a control lever transverse shaft sleeve 423; the other end of the control lever cross shaft 414 is also symmetrically provided with two connecting piece fixing rods 421, and the connecting pieces are fixedly connected with the two ends of the connecting piece fixing rods 421 by passing through the first pulley and the second pulley.

The working process of the shoulder-back type electric vertical take-off and landing aircraft provided by the fourth embodiment is as follows:

when driving, a driver backs the aircraft on the back and fastens the safety belt, so that the man and the machine are integrated, and only one hand holds the operating rod; when the motor is static, the rotating surfaces of the left and right groups of propellers are upward, the motor is started to gradually increase the accelerator of the electronic speed regulator of the motor, the airflow generated by the rotation of the upper and lower propellers in opposite directions is vertically downward, the propellers generate a reaction force relative to the aircraft, the lift force is upward, and the propellers generate enough lift force to drive the aircraft to vertically take off and rise after the motor obtains enough rotating speed; after the driver sits on the seat and gradually pushes the operating lever forward to a certain angle after the driver ascends to a certain height, the operating lever presses the operating lever cross rod to rotate around the shaft sleeve, and the front end of the left fixed rod pulls the lower cable of the right motor cross arm to enable the motor to tilt forward; the front end of the right fixed rod pulls the lower cable of the cross arm of the left motor to enable the left motor to tilt forwards; at the moment, the motor cross arms on the left side and the right side simultaneously tilt around the cross rod of the rack, and the propeller surface also gradually tilts forwards; at the moment, the airflow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to ensure that the aircraft can keep the height and fly forwards; the size of the tilting angle of the propeller surface is determined by the size of the activity angle of the operating lever; when the control lever is pushed leftwards, the right side fixing rod can release the right side upper cable and the left side lower cable, and meanwhile, the left side fixing rod can pull the left side upper cable and the right side lower cable, so that the paddle surface of the right side propeller inclines forwards and the paddle surface of the left side propeller inclines backwards, and the aircraft can turn leftwards in the original position until the control lever is pulled back to the original point; the control rod can move in a front-back and left-right direction, the propeller planes on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the pitch angle of the propeller planes on the right side is larger than that of the propeller planes on the left side and is slightly smaller when the aircraft is pushed forwards leftwards and forwards, so that the aircraft flies forwards and turns leftwards simultaneously, the aircraft can fly forwards and turns rightwards simultaneously when the control rod is pushed forwards and rightwards, and the aircraft can fly backwards and turn leftwards or rightwards simultaneously when the control rod is pulled leftwards and backwards.

The shoulder-back type electric vertical take-off and landing aircraft further comprises a control system, wherein the control system comprises a flight control module, a GPS positioning module, a wireless communication module and a battery module, the flight control module is respectively connected with the first motor 45 and the second motor 415 and is used for controlling the first motor 45 and the second motor 415 to work, and the GPS positioning module is connected with the flight control module and is used for collecting position information of the aircraft; the wireless communication module is connected with the flight control module and used for receiving remote control instructions, and the flight control module controls the aircraft to fly according to the received control instructions. The battery module is used for providing power for the whole aircraft and can adopt a battery pack.

EXAMPLE five

In a fifth embodiment, an electric shoulder-carried vertical take-off and landing aircraft is provided, where the aircraft includes a frame, a first driving mechanism and a second driving mechanism symmetrically disposed at two ends of the frame, and a control mechanism for controlling the first driving mechanism and the second driving mechanism, as shown in fig. 5.

The frame comprises a first frame shaft sleeve 511, a second frame shaft sleeve 512, a shaft sleeve fixing beam 51, a first cross bar 52, a first shaft sleeve longitudinal arm 59 and a second shaft sleeve longitudinal arm 510 which are longitudinally arranged in parallel, and a first vertical support bar 53 and a second vertical support bar 54 which are vertically arranged in parallel.

Specifically, a shaft sleeve fixing beam 51 is connected between the first frame shaft sleeve 511 and the second frame shaft sleeve 512, and the shaft sleeve fixing beam 51 connects and fixes the left and right frame shaft sleeves; one end of the first sleeve longitudinal arm 59 is connected with the first frame sleeve 511, and the other end is connected with one end of the first cross bar 52; one end of the first cross bar 52 is further connected with the top end of the first vertical support bar 53, one end of the second shaft sleeve longitudinal arm 510 is connected with the second rack shaft sleeve 512, and the other end is connected with the other end of the first cross bar 52; the other end of the first cross bar 52 is also connected with the top end of a second vertical support bar 54, and two rack shaft sleeves are connected with the two vertical support bars through two shaft sleeve longitudinal arms so as to be extended forwards; a safety belt (not shown in the figure) is installed in the middle of the first vertical support rod 53 and the second vertical support rod 54, a seat is connected between the bottoms of the first vertical support rod 53 and the second vertical support rod 54, a third vertical support rod (not shown in the figure) which is inclined forward is arranged on the seat, the first vertical support rod and the second vertical support rod can extend downwards and bend towards the left rear and the right rear respectively, the third vertical support rod can extend downwards and bend forwards, and the three vertical support rods form a three-point undercarriage.

The first driving mechanism comprises a first motor 55, a first propeller 56, a first motor cross arm 57 and a first steering engine 58; a motor fixing plate is arranged at one end of the first motor cross arm 57, two first motors 55 are symmetrically mounted on the motor fixing plate of the first motor cross arm 57, an output shaft of each first motor 55 is connected with a first propeller 56, and the other end of the first motor cross arm 57 penetrates through a first rack shaft sleeve 510 to be connected with an output shaft of a first steering engine 58.

The structure of the second driving mechanism is similar to that of the first driving mechanism, and specifically, the second driving mechanism comprises a second motor 515, a second propeller 516, a second motor cross arm 517 and a second steering engine 518; a motor fixing plate is arranged at one end of the second motor cross arm 517, two second motors 515 are symmetrically mounted on the motor fixing plate of the second motor cross arm 517, an output shaft of each second motor 515 is connected with a second propeller 516, and the other end of the second motor cross arm 517 penetrates through a second rack shaft sleeve 512 to be connected with the output of a second steering engine 518.

The control mechanism comprises a first steering engine 58, a second steering engine 518 and an electronic rocker 513, an output shaft of the first steering engine 58 is connected with a first motor cross arm 57, an output shaft of the second steering engine 518 is connected with a second motor cross arm 517, and the electronic rocker is arranged on a second vertical supporting rod 54.

The working process of the shoulder-back type electric vertical take-off and landing aircraft provided by the fifth embodiment is as follows:

when driving, a driver backs the aircraft on the back and fastens the safety belt, so that the man and the machine are integrated, and the driver can hold the rocker with one hand; when the motor is static, the rotating surfaces of the left and right groups of propellers are upward, the motor is started to gradually increase the accelerator of the electronic speed regulator of the motor, the airflow generated by the rotation of the upper and lower propellers in opposite directions is vertically downward, the propellers generate a reaction force relative to the aircraft, the lift force is upward, and the propellers generate enough lift force to drive the aircraft to vertically take off and rise after the motor obtains enough rotating speed; after the driver ascends to a certain height, the driver sits on the seat and pushes the rocker forwards to a certain angle gradually, the left steering engine and the right steering engine drive the two cross arms of the motor to tilt forwards, and the propeller surface of the propeller also tilts forwards gradually. At the moment, the airflow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to ensure that the aircraft can keep the height and fly forwards; the size of the tilting angle of the propeller surface is determined by the size of the moving angle of the rocker. When the rocker is pushed leftwards, the steering engine drives the propeller surface of the right propeller to incline forwards and the propeller surface of the left propeller to incline backwards, and the aircraft can turn leftwards in the original position until the rocker is pulled back to the original point; the rocker can move in all directions, the propellers on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the propeller pitch angle of the right propeller is larger than that of the left propeller when the aircraft is pushed forwards leftwards and forwards, the propeller pitch angle of the left propeller is slightly smaller, so that the aircraft flies forwards and flies leftwards, the aircraft can fly forwards and flies rightwards when the aircraft is pushed forwards and rightwards, and the aircraft can fly backwards and fly leftwards or rightwards when the aircraft is pulled leftwards and backwards.

The shoulder-back type electric vertical take-off and landing aircraft further comprises a control system, wherein the control system comprises a flight control module, a GPS (global positioning system) positioning module, a wireless communication module and a battery module, the flight control module is respectively connected with a first motor 55, a second motor 515, a first steering engine 58, a second steering engine 518 and an electronic rocker 513, and is used for controlling the first motor 55 and the second motor 515 to work, receiving action signals of the rocker and transmitting the action signals to the first steering engine 58 and the second steering engine 518 through signal lines, and the first steering engine 58 and the second steering engine 518 execute actions according to signal instructions; the GPS positioning module is connected with the flight control module and used for acquiring the position information of the aircraft; the wireless communication module is connected with the flight control module and used for receiving remote control instructions, and the flight control module controls the aircraft to fly according to the received control instructions. The battery module is used for providing power for the whole aircraft and can adopt a battery pack.

EXAMPLE six

The sixth embodiment provides a piggyback electric vertical take-off and landing aircraft, which includes a frame, a first driving mechanism and a second driving mechanism symmetrically disposed at two ends of the frame, a control mechanism for controlling the first driving mechanism and the second driving mechanism, and a first wing 625 and a second wing 626, as shown in fig. 6.

The rack comprises a first cross bar 61 and a second cross bar 62 which are arranged horizontally and mutually in parallel, and a first vertical support bar 63 and a second vertical support bar 64 which are arranged vertically and mutually in parallel; the top end of the first vertical support rod 63 is fixedly connected with one end of the first cross rod 61, and the top end of the second vertical support rod 64 is fixedly connected with the other end of the first cross rod 61; bearings used for being connected with a driving mechanism are installed at two ends of the first cross rod 61; one end of the second cross bar 62 is connected with the lower part of the first vertical support bar 63, and the other end is connected with the lower part of the second vertical support bar 64; a seat (not shown in the figure) is mounted on the second cross bar 62, a safety belt (not shown in the figure) is mounted in the middle of the first vertical support bar 63 and the second vertical support bar 64, a third vertical support bar (not shown in the figure) which is obliquely arranged forward is arranged on the seat, the first vertical support bar 63 and the second vertical support bar 64 can extend downwards and bend towards the left rear and the right rear respectively, the third vertical support bar can extend downwards and bend forwards, and the three vertical support bars form a three-point landing gear.

The first driving mechanism comprises a first motor 65, a first propeller 66, a first motor cross arm and a first motor swing arm 68; the first motor cross arm is composed of a first motor fixing plate 67 and a first shaft sleeve 60, the first motor fixing plate 67 is fixedly connected with the first shaft sleeve 60, two first motors 65 are symmetrically installed at the upper part and the lower part of one end, far away from the first shaft sleeve, of the first motor fixing plate 67, the output shaft of each first motor 65 is connected with a first propeller 66, and one end, far away from the first motor fixing plate, of the first shaft sleeve 60 is sleeved on a bearing at one end of a first cross rod 61; one end of the first motor swing arm 68 is fixedly connected with the first shaft sleeve 60; the other end of the first motor swing arm 68 is connected to a first vertical link 69.

The structure of the second driving mechanism is similar to that of the first driving mechanism, and specifically, the second driving mechanism comprises a second motor 615, a second propeller 616, a second motor cross arm and a second motor swing arm 618; the second motor cross arm is composed of a second motor fixing plate 617 and a second shaft sleeve 610, the second motor fixing plate 617 is fixedly connected with the second shaft sleeve 610, two second motors 615 are symmetrically mounted on one end, far away from the second shaft sleeve, of the second motor fixing plate 617 from the upper part and the lower part, an output shaft of each second motor 615 is connected with a second propeller 616, and one end, far away from the second motor fixing plate, of the second shaft sleeve 610 is sleeved on a bearing at the other end of the first cross rod 61; one end of the second motor swing arm 618 is fixedly connected with the second shaft sleeve 610; the other end of the second motor swing arm 618 is connected to a second vertical link 619.

The control mechanism comprises a first vertical connecting rod 69, a second vertical connecting rod 619, a first transverse telescopic connecting rod 611, a control lever 612, a control lever longitudinal shaft 613 and a control lever transverse shaft 614, one end of the first vertical connecting rod 69 is connected with a first motor swing arm 68, the other end of the first vertical connecting rod is connected with the rear end of the side face of the first wing 625 through a ball head, one end of the second vertical connecting rod 619 is connected with a second motor swing arm 618, and the other end of the second vertical connecting rod 619 is connected with the rear end of the side face of the second wing 626 through a ball head; one end of the operating lever longitudinal shaft 613 is inserted into an operating lever longitudinal shaft sleeve 620, two sides of the operating lever longitudinal shaft sleeve 620 are respectively and fixedly connected with an operating lever transverse shaft 614, and the other end of the operating lever transverse shaft 614 is inserted into an operating lever transverse shaft sleeve 621 arranged at the lower end of the vertical supporting rod; two ends of the first transverse telescopic connecting rod 611 are respectively connected with the front ends of the side surfaces of a first wing 625 and a second wing 626 through ball heads, a telescopic rod shaft sleeve 622 is sleeved on one end of the first transverse telescopic connecting rod 611, the other end of the control lever longitudinal shaft 613 is fixedly connected with one end of the telescopic rod shaft sleeve 622, a bearing is installed in a hole in the middle of the side surface of the first wing 625, a first wing cross rod 623 is inserted into the hole, one end of the first wing cross rod 623 is arranged in the first wing 625, the other end of the first wing cross rod 623 is fixedly connected with the lower end of a first vertical supporting rod 63, and the first wing 625 can tilt around the first wing cross rod 623; a bearing is installed in the middle of the side surface of the second wing 626, and a second wing cross bar 624 is inserted into the bearing, one end of the second wing cross bar 624 is arranged in the second wing 626, the other end of the second wing cross bar 624 is fixedly connected with the lower end of the second vertical support rod 64, and the second wing 626 can tilt around the second wing cross bar 624.

The working process of the shoulder-back type electric vertical take-off and landing aircraft provided by the sixth embodiment is as follows:

when driving, a driver sits on the seat and fastens the safety belt, and only holds the operating rod 612 with one hand; when the motor is not started, the rotating surfaces of the left and right groups of propellers are upward, and the front edges of the left and right wings are upward (the side surfaces of the wings are vertically upward). The motor is started to gradually increase an accelerator of the electronic speed regulator of the motor, airflow generated by the rotation of the upper propeller and the lower propeller in opposite directions is vertically downward, the propeller generates a reaction force relative to the aircraft, the reaction force is an upward lift force, and the propellers generate enough lift force to drive the aircraft to vertically take off and ascend after the motor obtains enough rotating speed; after the pilot sits on the seat and gradually pushes the operating rod 612 forward to a certain angle after the pilot rises to a certain height, the operating rod 612 presses the operating rod longitudinal shaft 613 to tilt around the operating rod transverse shaft 614, and meanwhile, the first transverse telescopic connecting rod 611 is pushed to enable the first wing 625 and the second wing 626 to tilt forwards; because the rear ends of the side surfaces of the two wings are respectively connected with the two vertical connecting rods through the ball heads, the two wings simultaneously push the first vertical connecting rod 69 and the second vertical connecting rod 619, the first vertical connecting rod 69 pushes the first motor swing arm 68, the second vertical connecting rod 619 pushes the second motor swing arm 618, and the first motor swing arm 68 drives the first motor cross arm 67 to tilt around the first cross rod 61 on the rack, so that the propeller surface of the first propeller 66 also tilts forwards gradually; the second motor swing arm 618 drives the second motor cross arm 617 to tilt around the first cross bar 61 on the rack, so that the propeller surface of the second propeller 616 also tilts forward gradually; at the moment, the airflow direction gradually generates a backward inclination angle from vertical to downward, upward and backward reaction forces are generated to ensure that the aircraft keeps the height and pulls the two wings to fly forward, and the wings gradually generate enough lift force to support the load at the moment, so that the motor outputs relatively small power to realize the flight. The size of the tilting angle of the propeller surface and the wing is determined by the size of the activity angle of the control lever; when the control lever 612 is pushed leftwards, the right end of the first transverse telescopic connecting rod is driven to ascend, the left end of the first transverse telescopic connecting rod is driven to descend, the right wing and the propeller surface of the propeller are driven to incline forwards, the propeller surface of the propeller on the left side inclines backwards, and the aircraft can turn leftwards in the original position until the control lever is pulled back to the original point; the control rod can move in a front-back left-right direction, the wings and the propeller surfaces on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards simultaneously, when the control rod is pushed leftwards and forwards, the propeller forward angle of the right wing is larger, the propeller forward angle of the left wing is smaller, the aircraft flies forwards and turns leftwards simultaneously, the control rod is pushed rightwards and forwards, the aircraft flies can fly forwards and turn rightwards simultaneously, and when the control rod is pulled leftwards and backwards or rightwards, the aircraft flies backwards and turns left.

The backpack type electric vertical take-off and landing aircraft further comprises a control system, wherein the control system comprises a flight control module, a GPS (global positioning system) positioning module, a wireless communication module and a battery module, the flight control module is respectively connected with the first motor 65 and the second motor 615 and used for controlling the first motor 65 and the second motor 615 to work, and the GPS positioning module is connected with the flight control module and used for collecting position information of the aircraft; the wireless communication module is connected with the flight control module and used for receiving remote control instructions, and the flight control module controls the aircraft to fly according to the received control instructions. The battery module is used for providing power for the whole aircraft and can adopt a battery pack.

EXAMPLE seven

The seventh embodiment provides a vertical electric vertical take-off and landing aircraft, which includes three shoulder-back electric vertical take-off and landing aircraft as described in the fifth embodiment, wherein a cargo box or a passenger cabin is installed on a rack of the three shoulder-back electric vertical take-off and landing aircraft; two longitudinal support rods which are arranged in parallel are connected between two adjacent racks, a first motor transverse arm of each first driving mechanism is connected with a first motor swing arm, a longitudinal connecting rod is connected between two adjacent first motor swing arms, a second motor transverse arm of each second driving mechanism is connected with a second motor swing arm, and a longitudinal connecting rod is also connected between two adjacent second motor swing arms.

The working process of the vertical electric vertical take-off and landing aircraft provided by the seventh embodiment is as follows:

when driving, a driver sits in the cabin and fastens the safety belt, and only holds the electronic rocker with one hand; when the motor is static, the rotating surfaces of the left and right groups of propellers are upward, the motor is started to gradually increase the accelerator of an electronic speed regulator of the motor, airflow generated by the rotation of the propellers is vertically downward, the propellers generate a reaction force relative to the aircraft, the lift force is upward, and the propellers generate enough lift force to drive the aircraft to vertically take off and rise after the motor obtains enough rotating speed; after the driver ascends to a certain height, the driver sits on the seat and pushes the control rod forwards to a certain angle gradually, the control rod presses the control rod longitudinal shaft to tilt around the control rod transverse shaft, the control rod transverse shaft lifts the transverse connecting rod, the transverse connecting rod upwards pushes the two vertical connecting rods, the vertical connecting rod pushes the left right two right angle swing arms, and the two right angle swing arms push the two motor swing arms to tilt forwards and simultaneously drive the motor cross arm to tilt forwards and the propeller surface also tilts forwards gradually. At the moment, the airflow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to ensure that the aircraft can keep the height and fly forwards; the size of the tilting angle of the propeller surface is determined by the size of the moving angle of the operating rod. When the control rod is pushed leftwards, the right end of the transverse connecting rod is driven to ascend, the left end of the transverse connecting rod descends, the propeller surface of the right propeller is driven to incline forwards, the propeller surface of the left propeller inclines backwards, and the aircraft can turn leftwards in the original position until the control rod is pulled back to the original point. The control rod can move in a front-back and left-right direction, the propeller planes on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the pitch angle of the propeller planes on the right side is larger than that of the propeller planes on the left side and is slightly smaller when the aircraft is pushed forwards leftwards and forwards, so that the aircraft flies forwards and turns leftwards simultaneously, the aircraft can fly forwards and turns rightwards simultaneously when the control rod is pushed forwards and rightwards, and the aircraft can fly backwards and turn leftwards or rightwards simultaneously when the control rod is pulled leftwards and backwards.

Example eight

The eighth embodiment provides a vertical electric vertical take-off and landing aircraft, which comprises three shoulder-back electric vertical take-off and landing aircraft as described in the third embodiment, wherein a cargo box or a passenger cabin is installed on a rack of the three shoulder-back electric vertical take-off and landing aircraft; two longitudinal support rods which are arranged in parallel are connected between two adjacent racks, a first motor transverse arm of each first driving mechanism is connected with a first motor swing arm, a longitudinal connecting rod is connected between two adjacent first motor swing arms, a second motor transverse arm of each second driving mechanism is connected with a second motor swing arm, and a longitudinal connecting rod is also connected between two adjacent second motor swing arms.

The working process of the vertical electric vertical take-off and landing aircraft provided by the eighth embodiment is as follows:

when driving, a driver sits in the cabin and fastens the safety belt, and only holds the electronic rocker with one hand; when the aircraft is static, the rotating surfaces of the left and right groups of propellers connected with the motor face upwards, the motor is started to gradually increase the accelerator of the electronic speed regulator of the motor, airflow generated by the rotation of the propellers is vertically downward, the propellers generate reaction force and upward lift force relative to the aircraft, and the propellers generate enough lift force to drive the aircraft to vertically take off and rise after the motor obtains enough rotating speed; after the driver ascends to a certain height, the driver sits on the seat and pushes the control lever forwards gradually to a certain angle, at the moment, the control lever presses the control lever to tilt around the control lever transverse shaft, one end of the control lever longitudinal shaft upwards lifts the transverse connecting rod, the transverse connecting rod upwards pushes the first vertical connecting rod and the second vertical connecting rod, the first vertical connecting rod pushes the first motor swing arm, the second vertical connecting rod pushes the second motor swing arm, the first motor swing arm drives the first motor cross arm to tilt around the first transverse rod on the rack, and therefore the propeller surface of the first propeller also tilts forwards gradually; the second motor swing arm drives the second motor cross arm to tilt around the first cross rod on the rack, so that the propeller surface of the second propeller also tilts forwards gradually; the air flow direction gradually generates a backward inclination angle from vertical to downward, and generates upward and backward reaction force to enable the aircraft to keep the height and fly forwards. The size of the tilting angle of the propeller surface is determined by the size of the activity angle of the operating lever; when the control rod is pushed leftwards, the right end of the transverse connecting rod is driven to ascend, the left end of the transverse connecting rod descends, the propeller surface of the right propeller is driven to incline forwards, the propeller surface of the left propeller inclines backwards, and the aircraft can turn leftwards in the original position until the control rod is pulled back to the original point; the control rod can move in a front-back and left-right direction, the propeller planes on the two sides are pulled backwards, the aircraft tilts backwards and flies backwards, the pitch angle of the propeller planes on the right side is larger than that of the propeller planes on the left side and is slightly smaller when the aircraft is pushed forwards leftwards and forwards, so that the aircraft flies forwards and turns leftwards simultaneously, the aircraft can fly forwards and turns rightwards simultaneously when the control rod is pushed forwards and rightwards, and the aircraft can fly backwards and turn leftwards or rightwards simultaneously when the control rod is pulled leftwards and backwards.

From the above description, it can be seen that one or more of the embodiments described above achieve the following technical effects:

the aircraft provided by the disclosure has the advantages of simple structure, small and light fuselage, capability of flying in a narrow space and convenience in loading; the left and right groups of propellers can tilt forwards and backwards, so that the flying is flexible, the flying action response is sensitive and timely, and the operation and the control are very easy; the device can be controlled by one hand, the other hand can execute a work task, and the device can be free of control and fly in an unmanned remote control mode after being matched with a flight control module and a GPS positioning module; the aircraft can be used for high mountain rescue, marine rescue, cargo transportation of personnel and goods among marine ships, travel exploration, short-distance cargo transportation, police, patrol, duty-on and other scenes, and can be applied to the fields of civil use, police use, military use, engineering construction, field operation and the like.

Although the present disclosure has been described with reference to specific embodiments, it should be understood that the scope of the present disclosure is not limited thereto, and those skilled in the art will appreciate that various modifications and changes can be made without departing from the spirit and scope of the present disclosure.

Claims

1. The shoulder-carried electric vertical take-off and landing aircraft is characterized by comprising a rack, a driving mechanism and an operation mechanism;

2. The electric vertical take-off and landing shoulder-back aircraft according to claim 1, wherein said drive mechanism comprises a motor cross arm, at least one motor mounted on one end of the motor cross arm, a propeller connected to an output shaft of the motor, and a motor swing arm connected to the other end of the motor cross arm;

the lower end of the frame is connected with two symmetrically arranged wings.

3. The electric vertical take-off and landing piggyback aircraft according to claim 2, wherein the lateral support device comprises a first cross bar and a second cross bar which are arranged in parallel, and two ends of the first cross bar are respectively connected with the other ends of the corresponding motor cross arms;

the vertical supporting device comprises two vertical supporting rods which are arranged in parallel; the top ends of the two vertical supporting rods are respectively connected with the first cross rod; the bottom ends of the two vertical supporting rods are respectively connected with the control device; the safety seat is characterized in that the second cross rod is connected between the lower ends of the two vertical supporting rods, a seat is mounted on the second cross rod, and a safety belt is mounted in the middle of the two vertical supporting rods.

4. The electric vertical take-off and landing piggyback aircraft according to claim 2, wherein the lateral support device comprises a first cross bar and a second cross bar which are arranged in parallel, and two ends of the first cross bar are respectively connected with the other ends of the corresponding motor cross arms;

the vertical supporting device comprises two vertical supporting rods which are arranged in parallel; the top ends of the two vertical supporting rods are respectively connected with the first cross rod through the longitudinal supporting rod; the bottom ends of the two vertical supporting rods are respectively connected with a longitudinal supporting rod used for being connected with the control device; the lower ends of the two vertical supporting rods are connected with the second cross rod respectively, the second cross rod located at the lower end is provided with a seat, and the middle parts of the two vertical supporting rods are provided with safety belts.

5. The piggyback electric VTOL aerial vehicle of claim 3 or 4, wherein the pushing device comprises a transverse connecting rod and two vertical connecting rods arranged in parallel; the top end of each vertical connecting rod is connected with the corresponding motor swing arm, and a transverse connecting rod is connected between the bottom ends of the two vertical connecting rods;

the control device comprises a control lever, a control lever longitudinal shaft and a control lever transverse shaft, one end of the control lever longitudinal shaft is connected with the middle of the transverse connecting rod, the other end of the control lever longitudinal shaft is connected with the control lever, a control lever longitudinal shaft sleeve is arranged in the middle of the control lever longitudinal shaft, the two sides of the control lever longitudinal shaft sleeve are fixedly connected with control lever transverse shafts respectively, the other end of the control lever transverse shaft is inserted into the control lever transverse shaft sleeve, and the control lever transverse shaft sleeve is fixedly connected with the bottom.

6. The electric vertical take-off and landing aircraft of claim 2, wherein the lateral support device comprises two frame bushings and a bushing fixing beam connected with the two frame bushings, and the motor cross arm passes through the frame bushings and is connected with the motor swing arm;

the vertical supporting device comprises two vertical supporting rods which are arranged in parallel; the top ends of the two vertical supporting rods are respectively connected with the corresponding rack shaft sleeves through the longitudinal supporting rods; the bottom ends of the two vertical supporting rods are respectively connected with a longitudinal supporting rod used for being connected with a transverse shaft sleeve of the control lever; a first cross rod is connected between the top ends of the two vertical supporting rods, and two corner swing arms are arranged on the first cross rod; the safety seat is characterized in that a second cross rod is connected between the bottom ends of the two vertical supporting rods, a seat is mounted on the second cross rod, and a safety belt is mounted in the middle of the two vertical supporting rods.

7. The piggyback electric VTOL aerial vehicle of claim 6, wherein the pushing device comprises a transverse link, two parallel arranged longitudinal links and two parallel arranged vertical links; one end of each longitudinal connecting rod is connected with the corresponding motor swing arm, the other end of each longitudinal connecting rod is connected with the corresponding corner swing arm, and the other end of each corner swing arm is connected with the top end of the corresponding vertical connecting rod; a transverse connecting rod is connected between the bottom ends of the two vertical connecting rods; the control device comprises a control lever, a control lever longitudinal shaft and a control lever transverse shaft, one end of the control lever longitudinal shaft is connected with the middle of the transverse connecting rod, the other end of the control lever longitudinal shaft is connected with the control lever, a control lever longitudinal shaft sleeve is arranged in the middle of the control lever longitudinal shaft, the two sides of the control lever longitudinal shaft sleeve are fixedly connected with control lever transverse shafts respectively, the other end of the control lever transverse shaft is inserted into the control lever transverse shaft sleeve, and the control lever transverse shaft sleeve is fixedly connected with the bottom;

the pushing device comprises two steering engines, and output shafts of the steering engines are connected with a cross arm of the motor; the control device comprises an electronic rocker arranged on the vertical supporting rod.

8. The electric vertical take-off and landing piggyback aircraft according to claim 2, wherein the lateral support device comprises a first cross bar and a second cross bar, and two ends of the first cross bar are respectively connected with the other ends of the corresponding motor cross arms;

the vertical supporting device comprises a longitudinal arm and a vertical supporting rod, the top end of the vertical supporting rod is connected with the middle part of the first cross rod through the longitudinal arm, the middle part of the vertical supporting rod is connected with the second cross rod, and a safety belt is arranged on the second cross rod; and a seat is installed at the bottom end of the vertical supporting rod.

9. The piggyback electric vtol aircraft of claim 8, wherein the pushing device comprises a connecting member connected to each motor cross arm, a first pulley block and a second pulley block, the vertical support bar is provided at an upper end thereof with a first pulley block fixing bar, the pulleys of the first pulley block are mounted at two ends of the first pulley block fixing bar, and the pulleys of the second pulley block are mounted on the vertical support bar;

the control device comprises a control lever, a control lever longitudinal shaft and a control lever transverse shaft, wherein the control lever is connected with one end of the control lever transverse shaft, the other end of the control lever transverse shaft is connected with a control lever transverse shaft sleeve, one end of the control lever longitudinal shaft is inserted into the control lever longitudinal shaft sleeve, the control lever longitudinal shaft sleeve is installed at the lower end of the vertical support rod, and the other end of the control lever longitudinal shaft is connected with the control lever transverse shaft sleeve; and the other end of the transverse shaft of the operating lever is also symmetrically provided with two connecting piece fixing rods, and the connecting pieces are fixedly connected with the two ends of the connecting piece fixing rods by bypassing the first pulley block and the second pulley block.

10. An upright electric vertical take-off and landing aircraft, characterized in that the aircraft comprises a plurality of shoulder-back electric vertical take-off and landing aircraft according to any one of claims 1 to 9, and a cabin is arranged between the plurality of shoulder-back electric vertical take-off and landing aircraft; a longitudinal support rod is connected between every two adjacent racks, and a longitudinal connecting rod is connected between every two adjacent motor swing arms.