CN112896512A - Unmanned aerial vehicle and working method thereof - Google Patents
Unmanned aerial vehicle and working method thereof Download PDFInfo
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- CN112896512A CN112896512A CN202110356299.4A CN202110356299A CN112896512A CN 112896512 A CN112896512 A CN 112896512A CN 202110356299 A CN202110356299 A CN 202110356299A CN 112896512 A CN112896512 A CN 112896512A
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- aerial vehicle
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- 238000000034 method Methods 0.000 title claims abstract description 8
- 239000007769 metal material Substances 0.000 claims abstract description 4
- 235000014676 Phragmites communis Nutrition 0.000 claims description 35
- 244000273256 Phragmites communis Species 0.000 claims description 22
- 239000002184 metal Substances 0.000 claims description 5
- 238000001125 extrusion Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 244000082204 Phyllostachys viridis Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 238000009412 basement excavation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000011017 operating method Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
- B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention relates to an unmanned aerial vehicle and a working method thereof, wherein the unmanned aerial vehicle comprises a body of the unmanned aerial vehicle, a plurality of support arms fixedly connected with the body, and propellers fixed at the upper ends of the outer sides of the support arms; a battery for driving the aircraft to run and a controller for controlling the aircraft to run are arranged in the fuselage; a foldable undercarriage hinged with the support arm is arranged below the outer side end of the support arm, the undercarriage comprises a hollow main cylinder with one end provided with a hole and a telescopic rod connected with the main cylinder in a sliding manner, two electrodes are symmetrically arranged on the inner wall of the main cylinder in the radial direction, the electrodes are electrically connected with a controller, the telescopic rod is made of a conductive metal material, and when the telescopic rod is contracted towards the inside of the main cylinder, the two electrodes are connected and conducted through the telescopic rod; this unmanned vehicles moves about through the telescopic link when taking off and landing, and the switching on/off of control electrode, controller pass through the leading-in signal of telecommunication control screw of electrode and rotate or stop, and the reaction is sensitive and the security is high, effectively avoids unmanned vehicles to descend the back screw and continuously rotates.
Description
Technical Field
The invention relates to the field of aviation, in particular to an unmanned aerial vehicle and a working method thereof.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing radio remote control equipment and a self-contained program control device, and compared with a manned aircraft, the unmanned aerial vehicle has the advantages of small volume, low manufacturing cost, convenient use, low requirement on the battle environment, strong battlefield viability and the like; the existing unmanned aerial vehicle generally comprises a fuselage, a propeller and the like for providing flight power, and after the existing unmanned aerial vehicle abnormally falls, the propeller is still in a rotating state all the time and is easily wound by foreign matters to cause the damage of a motor; or when the unmanned aerial vehicle stops at a far position, the problem that children are injured by the propeller due to the fact that the unmanned aerial vehicle is not closed timely is caused sometimes; in addition, the propellers can also be started to rotate after the parts of the unmanned aerial vehicles are folded, and the safety hazard is large.
Disclosure of Invention
In order to solve the technical problem, the invention provides an unmanned aerial vehicle and a working method thereof, wherein the unmanned aerial vehicle comprises a body of the unmanned aerial vehicle, a plurality of support arms fixedly connected with the body, and propellers fixed at the upper ends of the outer sides of the support arms; a battery for driving the aircraft to run and a controller for controlling the aircraft to run are arranged in the fuselage; a foldable undercarriage hinged with the support arm is arranged below the outer side end of the support arm, the undercarriage comprises a hollow main cylinder with one end provided with a hole and a telescopic rod connected with the main cylinder in a sliding manner, two electrodes are symmetrically arranged on the inner wall of the main cylinder in the radial direction, the electrodes are electrically connected with a controller, the telescopic rod is made of a conductive metal material, and when the telescopic rod is contracted towards the inside of the main cylinder, the two electrodes are connected and conducted through the telescopic rod; this unmanned vehicles moves about through the telescopic link when taking off and landing, and the switching on/off of control electrode, controller pass through the leading-in signal of telecommunication control screw of electrode and rotate or stop, and the reaction is sensitive and the security is high, effectively avoids unmanned vehicles to descend the back screw and continuously rotates.
The technical scheme of the invention is as follows:
an unmanned aerial vehicle comprises a body of the aircraft, a plurality of support arms fixedly connected with the body, and a propeller fixed at the upper ends of the outer sides of the support arms, wherein the propeller is driven to rotate by a motor arranged above the support arms; a battery for driving the aircraft to run and a controller for controlling the aircraft to run are arranged in the fuselage; the foldable undercarriage is characterized in that a foldable undercarriage hinged with the support arm is arranged below the outer side end of the support arm, the undercarriage comprises a hollow main cylinder with a hole at one end and a telescopic rod connected with the main cylinder in a sliding mode, two electrodes are symmetrically arranged on the inner wall of the main cylinder in the radial direction, the electrodes are electrically connected with the controller, the telescopic rod is made of conductive metal, and when the telescopic rod contracts towards the inside of the main cylinder, the two electrodes are connected and conducted through the telescopic rod.
The hole wall of the main cylinder opening is provided with a plurality of hooks facing the axis, the side wall of the telescopic rod is dug with a linear clamping groove corresponding to the hooks, the inner diameter of a circle formed by the hooks is smaller than the outer diameter of the telescopic rod, and the main cylinder limits the telescopic rod in the main cylinder through the hooks; a compressed first spring is arranged between the telescopic rod and the bottom end of the opening of the main cylinder.
The landing gear comprises a supporting arm, a landing gear and a landing gear, wherein a square digging groove parallel to the length direction of the supporting arm is arranged on one side of the supporting arm connected with the landing gear, the width/depth of the digging groove is larger than the diameter of the landing gear, the length of the digging groove is larger than the height of the landing gear, and when the landing gear is folded, the landing gear is accommodated in the digging groove; the side surface of the digging groove is symmetrically provided with two reeds, the upper end and the lower end of the side surface of the digging groove at the fixing positions of the reeds are respectively provided with a fixing groove, the reeds are embedded in the fixing grooves, the distance between the two reeds is smaller than the diameter of the undercarriage, and when the undercarriage is folded in the digging groove, the undercarriage is clamped and fixed by the reeds.
And a push switch is arranged between the side surface of the digging groove and the two reeds respectively, the two push switches are connected with circuits at the positive end and the negative end of the motor respectively in series, and the reeds can touch the push switches after being extruded and deformed.
The inner wall of the digging groove is arranged into a circular arc at one end far away from the machine body, and the circle center of the circular arc is provided with a horizontal rotating shaft; the connecting end of the main cylinder and the support arm is arranged to be semicircular corresponding to the arc-shaped inner wall of the digging groove, and the main cylinder is hinged to the rotating shaft; the outer end face of the support arm is provided with a stepped hole, the stepped hole penetrates through the arc-shaped inner wall of the digging groove, a limiting pin controlled by a second spring is arranged in the stepped hole, and the outer wall of the limiting pin is in a stepped shape corresponding to the stepped hole; the second spring is locked inside the support arm by a plug, and the plug is rotationally connected with the support arm through threads; a semi-spherical groove is formed in the semi-circular end face of the main cylinder, and when the undercarriage rotates to the vertical direction, the limiting pin is pushed by a second spring to vertically fix the undercarriage; the connecting part of the groove and the end face of the main cylinder is designed into a fillet.
Wherein, an arc-shaped slot is arranged on the semicircular end surface of the main cylinder; and a sleeve is fixedly arranged above the slot of the main cylinder of the support arm, and a lead connected with the electrode and the controller penetrates through the sleeve.
An operating method of an unmanned aerial vehicle, comprising the following sequential steps:
firstly, the undercarriage folded in the digging groove is turned and opened, then the reed rebounds and releases the extrusion on the press switch, and at the moment, the motor and the battery are in a connected state; after the undercarriage is opened, the limiting pin is pushed by the second spring to vertically fix the undercarriage;
placing the unmanned aerial vehicle on a take-off platform, compressing the first spring at the moment, and connecting and conducting the electrodes through the telescopic rod;
controlling the unmanned aerial vehicle to take off through the wireless remote controller, driving the propeller to rotate from the motor of the unmanned aerial vehicle to the state that the unmanned aerial vehicle takes off and leaves the ground, wherein the time length is S1, after the unmanned aerial vehicle flies off the ground, the telescopic rod moves downwards under the pushing of the first spring, and at the moment, the two electrodes in the main cylinder are in a disconnected state;
controlling the unmanned aerial vehicle to land through the wireless remote controller, enabling the telescopic rod to contract and extrude the first spring after the unmanned aerial vehicle lands, enabling the electrodes to be connected through the metal telescopic rod at the moment, enabling electric signals to be transmitted to the controller after the electrodes are connected, enabling the controller to close a power supply for driving the motor to rotate after receiving the signals, enabling the time from the electrode connection to the power supply closing to be S2, and enabling the time from the controller to control the motor to start rotating to the controller to disconnect the power supply of the motor to be L1; the controller can automatically recognize that only two signals S1 and S2 are transmitted by the electrodes in the range of L1, and takes the signal S2 as a triggering signal for turning off the power supply;
after the unmanned aerial vehicle is closed, the undercarriage is folded into the digging groove, the reed is extruded and deformed at the moment, the press switch is extruded by the reed and is in a disconnected state, and at the moment, a lead connected with the battery by the motor is disconnected by the press switch.
The invention has the following beneficial effects:
1. the inner wall of the main cylinder of the unmanned aerial vehicle is radially and symmetrically provided with two electrodes, the electrodes are electrically connected with the controller, the corresponding telescopic rods are made of conductive metal materials, and when the telescopic rods contract towards the inside of the main cylinder, the two electrodes are connected and conducted through the telescopic rods; this unmanned vehicles moves about through the telescopic link when taking off and landing, and the switching on/off of control electrode, controller pass through the leading-in signal of telecommunication control screw of electrode and rotate or stop, and the reaction is sensitive and the security is high, effectively avoids unmanned vehicles to descend the back screw and continuously rotates.
2. According to the support arm of the unmanned aerial vehicle, the square digging groove parallel to the length direction of the support arm is formed in the side, connected with the undercarriage, of the support arm, when the undercarriage is folded, the undercarriage can be contained in the digging groove, the occupied space of the unmanned aerial vehicle is reduced, and the unmanned aerial vehicle is convenient to carry and store.
3. The two reeds are symmetrically arranged on the side face of the digging groove of the unmanned aerial vehicle, when the undercarriage is folded in the digging groove, the undercarriage is clamped and fixed by the reeds, and the fixing mode is simple and reliable; the reed is clamped in the fixed groove, so that subsequent maintenance and replacement are facilitated.
4. According to the unmanned aerial vehicle, the press switches are respectively arranged between the side face of the digging groove and the two reeds, the two press switches are respectively connected with the positive end circuit and the negative end circuit of the motor in series, when the undercarriage is turned over into the digging groove, the reeds are extruded and deformed to touch the press switches, and the press switches disconnect the lead connecting the motor and the battery, so that the problem that a propeller hurts a person due to misoperation of personnel is effectively avoided, and the safety of the unmanned aerial vehicle is improved; two push switches control the switch of positive and negative pole end circuit respectively, form two switch protection, and the reliability is higher.
5. The main cylinder of the unmanned aerial vehicle is limited and fixed with the limiting pin on the support arm through the groove arranged at the end part of the main cylinder, and the fixing mode is simple; the joint of the groove and the end face of the main cylinder is designed into a round angle, so that the main cylinder can rotate relative to the support arm conveniently.
6. According to the support arm of the unmanned aerial vehicle, the sleeve is fixedly arranged above the groove of the main cylinder, the lead connected with the electrode and the controller penetrates through the sleeve, the lead is prevented from being extruded by friction when the main cylinder is turned over, and the service life of the lead is prolonged.
7. According to the unmanned aerial vehicle, the main cylinder limits the telescopic rod in the main cylinder through the clamping hook, the limiting structure is simple, an operator can assemble and replace parts by himself, and the maintenance convenience of the unmanned aerial vehicle is improved; be provided with the first spring of a compression between the trompil bottom of telescopic link and main section of thick bamboo, first spring not only provides the power of kick-backing for the telescopic link, provides the buffering for unmanned vehicles descends moreover.
Drawings
FIG. 1 is a schematic view of the present invention;
FIG. 2 is a partial cross-sectional view of the present invention;
FIG. 3 is a schematic view of an end of a support arm according to the present invention;
FIG. 4 is a schematic view of the landing gear of the present invention;
FIG. 5 is a cross-sectional view of the main cartridge of the present invention;
FIG. 6 is a top view of the main cartridge of the present invention;
FIG. 7 is an enlarged view of the invention taken from the circled position of FIG. 3;
FIG. 8 is a cross-sectional view of the reed position of the arm of the present invention;
FIG. 9 is a schematic view of the connection position of the arm and the main cylinder according to the present invention;
FIG. 10 is a control flow diagram of the present invention;
FIG. 11 is a timing diagram illustrating the electrode turn-on trigger according to the present invention.
The reference numbers in the figures denote:
1-fuselage, 2-support arm, 201-grooving, 202-reed, 203-fixed groove, 204-rotating shaft, 205-second spring, 206-limit pin, 207-plug, 208-sleeve, 3-propeller, 4-motor, 5-battery, 6-controller, 7-landing gear, 701-main cylinder, 702-telescopic rod, 703-electrode, 704-hook, 705-clamping groove, 706-first spring, 707-groove, 708-grooving and 8-push switch.
Detailed Description
The invention is described in detail below with reference to the figures and the specific embodiments.
Referring to fig. 1 to 3, an unmanned aerial vehicle comprises a body 1 of the aircraft, a plurality of support arms 2 fixedly connected with the body 1, and a propeller 3 fixed at the upper ends of the outer sides of the support arms 2, wherein the propeller 3 is driven to rotate by a motor 4 arranged above the support arms 2; a battery 5 for driving the aircraft to run and a controller 6 for controlling the aircraft to run are arranged in the fuselage 1; a folding undercarriage 7 hinged with the support arm 2 is arranged below the outer side end of the support arm 2, the undercarriage 7 comprises a hollow main cylinder 701 with an opening at one end and a telescopic rod 702 in sliding connection with the main cylinder 701, two electrodes 703 are radially and symmetrically arranged on the inner wall of the main cylinder 701, the electrodes 703 are electrically connected with the controller 6, the telescopic rod 702 is made of conductive metal, and when the telescopic rod 702 is contracted towards the inside of the main cylinder 701, the two electrodes 703 are connected and conducted through the telescopic rod 702; by means of the up/down movement of the telescopic rod 702 during landing, the on/off of the electrode 703 is controlled, and the controller 6 controls the propeller 3 to rotate or stop through an electric signal led in by the electrode 703, so that the propeller is effectively prevented from continuously rotating after the unmanned aerial vehicle lands.
Further, referring to fig. 4 to 8, a plurality of hooks 704 facing the axis are disposed on the hole wall of the opening of the main cylinder 701, a linear-shaped slot 705 corresponding to the hook 704 is dug on the side wall of the telescopic rod 702, the inner diameter of a circle enclosed by the plurality of hooks 704 is smaller than the outer diameter of the telescopic rod 702, the main cylinder 701 limits the telescopic rod 702 in the main cylinder 701 through the hook 704, the limiting structure is simple, an operator can assemble and replace parts by himself, and the maintenance convenience of the unmanned aerial vehicle is improved; a compressed first spring 706 is arranged between the telescopic rod 702 and the bottom end of the opening of the main cylinder 701, and the first spring 706 not only provides rebounding force for the telescopic rod 702, but also provides buffering for the landing of the unmanned aerial vehicle.
Furthermore, a square digging groove 201 parallel to the length direction of the support arm 2 is arranged on one side of the support arm 2 connected with the landing gear 7, the width/depth of the digging groove 201 is larger than the diameter of the landing gear 7, the length of the digging groove 201 is larger than the height of the landing gear 7, and when the landing gear 7 is folded, the landing gear 7 is accommodated in the digging groove 201, so that the occupied space of the unmanned aerial vehicle is reduced; the side surface of the digging groove 201 is symmetrically provided with two reeds 202, the side surface of the digging groove 201 is respectively provided with a fixing groove 203 at the upper end and the lower end of the fixing position of the reeds 202, and the reeds 202 are embedded in the fixing grooves 203, so that the subsequent maintenance and replacement are facilitated; the distance between the two spring pieces 202 is smaller than the diameter of the undercarriage 7, when the undercarriage 7 is folded in the groove 201, the undercarriage 7 is clamped and fixed by the spring pieces 202, and the fixing mode is simple and reliable.
Further, a push switch 8 is respectively arranged between the side surface of the digging groove 201 and the two reeds 202, the two push switches 8 are respectively connected with the positive end circuit and the negative end circuit of the motor 4 in series, and the two push switches 8 respectively control the switches of the positive end circuit and the negative end circuit to form double-switch protection; when the undercarriage 7 is turned and folded in the excavation groove 201, the undercarriage 7 extruding reed 202 deforms, the reed 202 touches the press switch 8 after being extruded and deformed, and then the press switch 8 disconnects the motor 4 and the battery 5 through a lead, so that the problem that the propeller 3 hurts people due to misoperation of personnel is effectively solved, and the safety of the unmanned aerial vehicle is improved.
Further, the inner wall of the digging groove 201 is arranged to be arc-shaped at one end far away from the machine body 1, and a horizontal rotating shaft 204 is arranged at the center of the arc-shaped circle; the connecting end of the main cylinder 701 and the support arm 2 is set to be semicircular corresponding to the arc-shaped inner wall of the digging groove 201, and the main cylinder 701 is hinged on the rotating shaft 204; the outer side end face of the support arm 2 is provided with a stepped hole, the stepped hole penetrates through the arc-shaped inner wall of the groove 201, a limit pin 206 controlled by a second spring 205 is arranged in the stepped hole, and the outer wall of the limit pin 206 is in a stepped shape corresponding to the stepped hole; the second spring 205 is locked inside the support arm 2 by a plug 207, and the plug 207 is rotatably connected with the support arm 2 through threads; a semi-spherical groove 707 is formed in the semi-circular end face of the main barrel 701, when the landing gear 7 rotates to the vertical direction, the limit pin 206 is pushed by the second spring 205 to move into the groove 707, so that the landing gear 7 is vertically fixed, and the fixing mode is quick and simple; the connection between the groove 707 and the end surface of the main cylinder 701 is designed as a round angle, which facilitates the smooth disengagement of the limit pin 206 when the main cylinder 701 rotates.
Further, referring to fig. 9, an arc-shaped slot 708 is formed on the semicircular end surface of the main cylinder 701; the sleeve 208 is fixedly arranged above the slot 708 of the main cylinder 701 of the support arm 2, and a lead connected with the electrode 703 and the controller 6 penetrates through the sleeve 208, so that the lead is prevented from being extruded by friction when the main cylinder 701 is turned over, and the service life of the lead is prolonged.
Referring to fig. 1 to 11, a working method of an unmanned aerial vehicle includes the following steps performed in sequence:
firstly, the landing gear 7 folded in the slot 201 is turned over and opened, then the reed 202 rebounds and releases the extrusion on the press switch 8, and at the moment, the motor 4 and the battery 5 are in a connection state; after the landing gear 7 is opened, the limiting pin 206 vertically fixes the landing gear 7 under the pushing of the second spring 205;
placing the unmanned aerial vehicle on a take-off platform, wherein the first spring 706 is compressed, and the electrode 703 is connected and conducted through the telescopic rod 702;
thirdly, the unmanned aerial vehicle is controlled to take off through the wireless remote controller, the motor 4 of the unmanned aerial vehicle drives the propeller 3 to rotate until the unmanned aerial vehicle takes off and leaves the ground, the time length is S1, after the unmanned aerial vehicle flies off the ground, the telescopic rod 702 moves downwards under the pushing of the first spring 706, and at the moment, the two electrodes 703 in the main cylinder 701 are in a disconnected state;
fourthly, the unmanned aerial vehicle is controlled to land through the wireless remote controller, after the unmanned aerial vehicle lands, the telescopic rod 702 contracts and extrudes the first spring 706, at the moment, the electrode 703 is connected through the metal telescopic rod 702 in a conducting manner, an electric signal is transmitted to the controller 6 after the electrode 703 is connected, the controller 6 closes the power supply for driving the motor 4 to rotate after receiving the signal, the time from the electrode 703 being connected to the power supply being closed is S2, the time from the control of the motor 4 to the control of the motor 6 to the turning-off of the motor 4 by the controller 6 is L1, the controller 6 can automatically recognize that only two signals S1 and S2 are transmitted by the electrode 703 in the range of L1, and the signal S2 is used as a trigger signal for closing the power supply;
after the unmanned aerial vehicle is closed, the undercarriage 7 is folded into the digging groove 201, the reed 202 is extruded and deformed at the moment, the press switch 8 is extruded by the reed 202 and is in a disconnected state, and at the moment, a lead connecting the motor 4 and the battery 5 is disconnected by the press switch 8.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (7)
1. An unmanned aerial vehicle, characterized in that: the aircraft comprises an aircraft body (1), a plurality of support arms (2) fixedly connected with the aircraft body (1), and a propeller (3) fixed at the upper ends of the outer sides of the support arms (2), wherein the propeller (3) is driven to rotate by a motor (4) arranged above the support arms (2); a battery (5) for driving the aircraft to run and a controller (6) for controlling the aircraft to run are arranged in the fuselage (1); the foldable landing gear (7) hinged to the support arm (2) is arranged below the outer side end of the support arm (2), the landing gear (7) comprises a hollow main cylinder (701) with an opening at one end and a telescopic rod (702) in sliding connection with the main cylinder (701), two electrodes (703) are radially and symmetrically arranged on the inner wall of the main cylinder (701), the electrodes (703) are electrically connected with a controller (6), the telescopic rod (702) is made of a conductive metal material, and when the telescopic rod (702) contracts towards the inside of the main cylinder (701), the two electrodes (703) are connected and communicated through the telescopic rod (702).
2. The unmanned aerial vehicle of claim 1, wherein: a plurality of clamping hooks (704) facing to the axis are arranged on the hole wall of the hole of the main cylinder (701), a linear clamping groove (705) corresponding to the clamping hook (704) is dug on the side wall of the telescopic rod (702), the inner diameter of a circle formed by the clamping hooks (704) is smaller than the outer diameter of the telescopic rod (702), and the telescopic rod (702) is limited in the main cylinder (701) by the main cylinder (701) through the clamping hook (704); a compressed first spring (706) is arranged between the telescopic rod (702) and the bottom end of the opening of the main cylinder (701).
3. An unmanned aerial vehicle as defined in claim 2, wherein: a square digging groove (201) parallel to the length direction of the support arm (2) is formed in one side, connected with the landing gear (7), of the support arm (2), the width/depth of the digging groove (201) is larger than the diameter of the landing gear (7), the length of the digging groove (201) is larger than the height of the landing gear (7), and when the landing gear (7) is folded and folded, the landing gear (7) is contained in the digging groove (201); the side surface of the digging groove (201) is symmetrically provided with two reeds (202), the side surface of the digging groove (201) is respectively provided with a fixing groove (203) at the upper end and the lower end of the fixing position of the reeds (202), the reeds (202) are embedded in the fixing grooves (203), the distance between the two reeds (202) is smaller than the diameter of the undercarriage (7), and when the undercarriage (7) is folded in the digging groove (201), the undercarriage (7) is clamped and fixed by the reeds (202).
4. An unmanned aerial vehicle as defined in claim 3, wherein: a press switch (8) is arranged between the side surface of the digging groove (201) and the two reeds (202), the two press switches (8) are connected with circuits at the positive end and the negative end of the motor (4) in series, and the reeds (202) can touch the press switch (8) after being extruded and deformed.
5. An unmanned aerial vehicle as defined in claim 4, wherein: the inner wall of the digging groove (201) is arranged into a circular arc at one end far away from the machine body (1), and the circle center of the circular arc is provided with a horizontal rotating shaft (204); the connecting end of the main cylinder (701) and the support arm (2) is arranged to be semicircular corresponding to the arc-shaped inner wall of the digging groove (201), and the main cylinder (701) is hinged to the rotating shaft (204); the outer side end face of the support arm (2) is provided with a stepped hole, the stepped hole penetrates through the arc-shaped inner wall of the digging groove (201), a limiting pin (206) controlled by a second spring (205) is arranged in the stepped hole, and the outer wall of the limiting pin (206) is in a stepped shape corresponding to the stepped hole; the second spring (205) is locked inside the support arm (2) by a plug (207), and the plug (207) is rotationally connected with the support arm (2) through threads; a semi-spherical groove (707) is formed in the semi-circular end face of the main cylinder (701), and when the landing gear (7) rotates to the vertical direction, the limiting pin (206) is pushed by the second spring (205) to vertically fix the landing gear (7); the joint of the groove (707) and the end face of the main cylinder (701) is designed to be a round angle.
6. An unmanned aerial vehicle as defined in claim 5, wherein: an arc-shaped slot (708) is formed in the semicircular end face of the main cylinder (701); the support arm (2) is fixedly provided with a sleeve (208) above the slot (708) of the main cylinder (701), and a lead connected with the electrode (703) and the controller (6) penetrates through the sleeve (208).
7. A method of operating an unmanned aerial vehicle as claimed in claim 6, wherein: comprises the following steps which are carried out in sequence:
firstly, the landing gear (7) folded in the digging groove (201) is turned over and opened, then the reed (202) rebounds and releases the extrusion on the press switch (8), and at the moment, the motor (4) and the battery (5) are in a connection state; after the undercarriage (7) is opened, the limiting pin (206) is pushed by the second spring (205) to vertically fix the undercarriage (7);
placing the unmanned aerial vehicle on a take-off platform, wherein the first spring (706) is compressed, and the electrode (703) is connected and communicated through the telescopic rod (702);
controlling the unmanned aerial vehicle to take off through the wireless remote controller, starting to drive the propeller (3) to rotate from the motor (4) of the unmanned aerial vehicle until the unmanned aerial vehicle takes off and leaves the ground, wherein the time length is S1, after the unmanned aerial vehicle flies off the ground, the telescopic rod (702) moves downwards under the pushing of the first spring (706), and at the moment, the two electrodes (703) in the main cylinder (701) are in a disconnected state;
controlling the unmanned aerial vehicle to land through the wireless remote controller, wherein after the unmanned aerial vehicle lands, the telescopic rod (702) contracts and extrudes the first spring (706), at the moment, the electrode (703) is connected through the metal telescopic rod (702), an electric signal is transmitted to the controller (6) after the electrode (703) is connected, the controller (6) closes a power supply for driving the motor (4) to rotate after receiving the signal, the time from the connection of the electrode (703) to the closing of the power supply is S2, and the time from the control of the motor (4) by the controller (6) to the turning-off of the motor (4) by the controller (6) is L1; the controller (6) can automatically recognize that only two signals S1 and S2 are transmitted by the electrode (703) in the range of L1, and takes the signal S2 as a triggering signal for turning off the power supply;
after the unmanned aerial vehicle is closed, the undercarriage (7) is folded into the digging groove (201), the reed (202) is extruded and deformed, the press switch (8) is extruded by the reed (202) and is in a disconnected state, and at the moment, a wire connected with the battery (5) and the motor (4) is disconnected by the press switch (8).
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