WO2009149592A1

WO2009149592A1 - Vertical takeoff and landing airplane

Info

Publication number: WO2009149592A1
Application number: PCT/CN2008/002094
Authority: WO
Inventors: 张庆柳
Original assignee: Zhang Qingliu
Priority date: 2008-06-12
Filing date: 2008-12-26
Publication date: 2009-12-17
Also published as: CN101602403A

Abstract

A vertical takeoff and landing airplane comprises a driving cabin (1), a fuselage (16), an aero-engine (10), a wing (9), a horizontal tail (7), a vertical tail (6), a reducer (13) and a control system. The aero-engine (10) is connected with the reducer (13) through a driving shaft (11) and a clutch (12). Steering vector tail propelling nozzle (8) is assembled on the back part of the aero-engine (10). A rotor wing (5) is assembled on the top of the fuselage (6), and the said rotor wing (5) is connected with a rotor wing shaft (3). The vertical takeoff and landing airplane has a retracting device (14) of the rotor wing shaft (3) and an open-close rotor wing cabin (2) which can contain the furled rotor wing (5). The said open-close rotor wing cabin (2) is located on the top of the fuselage (6). The rotor wing shaft (3) is connected with the reducer (13) and the retracting device (14) of the rotor wing shaft (3). An automatic positioning device (4) is assembled on the rotor wing (5), and an automatic positioning device (4) of the rotor wing shaft (3) is assembled on the rotor wing shaft (3).

Description

Vertical takeoff and landing aircraft

The present invention relates to an aircraft, and more particularly to a vertical takeoff and landing aircraft. Background technique

So far, the vertical take-off and landing aircraft have developed five major types: tailstock type, tilting force device type, thrust steering type, special lift power unit type and the above three types of hybrid configuration, typical representatives such as Boeing Company of the United States V-22 tilt-rotor aircraft, British "鹞"-type deflection nozzle vertical take-off and landing aircraft, the US Lockheed Martin F-35B uses a lift fan and an afterburning turbofan engine with a steering vector nozzle Short takeoff / vertical landing aircraft. Several of these vertical take-off and take-off/vertical landing aircraft have been put into use, as they do not require special airports and runways, making them more effective in increasing maneuverability and flexibility in warfare. But at the same time, there are also many major shortcomings. Because of the large diameter of the rotor, the speed of the tilting rotorcraft can only be within 400 km/h during the leveling, and the "鹞" type deflection nozzle is used for vertical take-off and landing. The take-off weight of the aircraft can only be 83%-85% of the engine thrust, which greatly limits the aircraft's payload, affecting the aircraft's fuel load and range. At the same time, the engine works at its maximum state when the aircraft takes off vertically. The amount of oil is extremely large, which limits the operational radius of the aircraft. The F-35B developed by Lockheed Martin of the United States uses a lift fan and a short-range take-off/vertical landing aircraft with a steering vector nozzle, due to the lift fan and belt steering. The lift generated by the vector nozzle is not enough to make the aircraft take off and land vertically. It can only change the pain to short takeoff/vertical takeoff and landing, which greatly reduces the maneuverability of the aircraft. The increase of engine power is very much under current technical conditions. hard. Summary of the invention The invention overcomes the deficiencies of the prior art, and provides a vertical take-off and landing aircraft which has a simple structure, is easy to manufacture, can take off and land vertically, and can fly at a high speed. In order to obtain maximum lift when the aircraft takes off vertically, the present invention The top of the aircraft is equipped with an openable and rotatable rotor cabin. When the aircraft moves up and down, the rotor cabin is opened. The rotor shaft expansion device extends the rotor shaft and the rotor connected to the rotor shaft out of the rotor cabin. When the aircraft reaches a certain height and reaches a certain speed. When turning to level flight, the rotor automatic positioning device automatically closes the rotor and opens the rotor cabin. The rotor shaft expansion device shrinks the rotor shaft and the rotor into the rotor cabin, the rotor cabin is closed, and the aircraft enters a normal level flight state.

According to an aspect of the present invention, a vertical take-off and landing aircraft is provided, the hoisting and landing aircraft including a cockpit, a fuselage, an aeroengine, a wing, a horizontal tail, a vertical tail, a speed reducer and a control system, and an aeroengine through a drive shaft The clutch is connected to the reducer, the rear of the aircraft engine is equipped with a steering vector tail nozzle, and the upper part of the fuselage is equipped with a rotor, and the rotor is connected with a rotor shaft, and the vertical takeoff and landing aircraft is further provided with a rotor shaft expansion device and can be accommodated An openable and rotatable rotor nacelle of the gathered rotor, the openable and rotatable rotor nacelle is disposed on a top of the fuselage, the rotor shaft is coupled to the reducer and the rotor shaft telescopic device, and the rotor is equipped with a rotor The automatic positioning device is provided with a rotor shaft automatic positioning device on the rotor shaft.

Preferably, the rotor automatic positioning device is composed of an elastic member and a limiting member for automatically positioning the rotor in a position parallel to the body.

Preferably, the rotor shaft automatic positioning device is constituted by a positioning member and a locking member, and when the rotor is folded, the rotor shaft is fixed at a position parallel to the rotor capsule after the rotor is gathered.

Preferably, the rotor shaft expansion device includes a hydraulic telescopic member for extending the rotor shaft, the rotor, or the contraction into the rotor module.

Preferably, the rotor cabin is provided with a rotor wing cover plate, and when the aircraft is vertically taken off and landing, the rotor wing cover plate is folded and folded to the left and right sides, so that the gathered rotor can extend or retract into the rotor cabin, when the aircraft When flying flat, the rotor gathers and retracts into the rotor cabin. The rotor pod cover is closed toward the middle to close the rotor pod.

Preferably, the rotor structure at the upper portion of the fuselage may be a coaxial reversing double rotor, and the rotor shaft is a coaxial reversing rotor shaft.

Preferably, the reducer is coupled to a plurality of aircraft engines via a corresponding drive shaft and clutch, and an auxiliary aeroengine is mounted on the vertical tail.

Preferably, the aero-engine is equipped with a propeller in front of it, and the auxiliary aero-engine is equipped with a propeller.

Preferably, the front and rear parts of the rotor cabin are respectively equipped with rotors with opposite rotation directions and corresponding automatic positioning devices for the rotors, rotor shafts, reducers, automatic positioning devices for the rotor shafts, rotor shaft expansion devices, transmission shafts, and aero engines. , the vertical tail is installed downwards.

The rotor structure of the upper part of the vertical take-off and landing aircraft fuselage is a coaxial double-rotor, the rotor shaft is a coaxial reversing rotor shaft, the front part of the aero-engine is connected with the propeller through the clutch and the transmission shaft, and the rear is driven by the clutch and the transmission shaft. Connected to the reducer, the rear of the fuselage is equipped with an adjustable rotor fixed rod.

Because of the above technical solution, the utility of the vertical take-off and landing aircraft provided by the invention has the advantages of simple and reliable structure, and the use efficiency of the aero-engine is greatly improved. The lift generated by the rotor at the same power during vertical take-off and landing is the existing other form of vertical take-off and landing aircraft. Several times or even ten times, the vertical take-off and landing can be easily achieved. When the plane is turned into the plane, the rotor can be retracted into the rotor cabin to make it fly normally at the same speed as a normal airplane. If necessary, the flight speed can reach or exceed. The speed of sound without having to add significantly to the aero engine power. DRAWINGS

1 is a schematic structural view of a first embodiment of the present invention;

2 is a schematic structural view of a second embodiment of the present invention;

Figure 3 is a schematic structural view of a third embodiment of the present invention; 4 is a schematic structural view of a fourth embodiment of the present invention; FIG. 5 is a schematic structural view of a fifth embodiment of the present invention;

Figure 6 is a schematic view showing the structure of a sixth embodiment of the present invention.

In the picture: Driving 1 Rotorcraft 2 Rotor shaft 3 Rotor automatic positioning device 4 Rotor 5 Vertical tail 6 Horizontal tail 7 Steering vector tail nozzle 8 Wing 9 Aeroengine 10 Transmission shaft 11 Clutch 12 Reducer 13 Rotor shaft telescopic device 14 Rotor axis automatic positioning device 15 fuselage 16 auxiliary aero engine 17 propeller 18 adjustable rotor fixing rod 19 steerable vertical tail 20

The invention will now be further described with reference to the accompanying drawings.

In Fig. 1, the vertical take-off and landing aircraft is composed of a driving compartment 1, a fuselage 16, an aero engine 10, a wing 9, a horizontal tail 7, a vertical tail 6 and a control system, and the upper part of the fuselage 16 is equipped with a rotor 5, a rotor 5 The rotor automatic positioning device 4 is mounted thereon, the rotor 5 is connected with the rotor shaft 3, the rotor shaft 3 is connected with the speed reducer 13 and the rotor shaft expansion device 14, and the rotor shaft 3 is equipped with a rotor shaft automatic positioning device 15, and the top of the fuselage 16 is equipped with The aerodynamic engine 10 is connected to the reducer 13 via a transmission shaft 11, a clutch 12, and a steering vector tail pipe 8 at the rear of the aircraft engine 10. The shape design of the aircraft is basically similar to that of a normal aircraft design. At the top of the aircraft, there is an openable and rotatable rotor cabin 2. When the aircraft moves up and down, the rotor cabin 2 is opened, and the rotor shaft expansion device 14 connects the rotor shaft 3 with the rotor shaft. The rotor 5 extends out of the rotor cabin 2, and the left and right rotor wing covers of the rotor cabin 2 can be folded and folded to the left and right when opened, and the rotor hatch of the rotor cabin 2 is opened, so that the gathered rotor 5 can be extended or Indented into the rotor cabin 2, when the plane is flying flat, the rotor 5 gathers and retracts into the rotor cabin, and the left and right rotor cabin covers are closed toward the middle to close the rotor cabin 2. In the figure, the rotor shaft 3 is a retractable spline shaft transmission structure. The aero engine 10 is operated, and the rotor shaft 3 and the rotor 5 connected to the rotor shaft 3 are rotated by the transmission shaft 11, the clutch 12, and the speed reducer 13, and the rotor 5 is coupled to the rotor shaft 3 The two ends are symmetrically arranged and connected to each other, and two sets of symmetrically arranged rotor blades are arranged. The corresponding two rotors are equipped with a rotor automatic positioning device 4, and the rotor automatic positioning device 4 is composed of an elastic member and a limiting member. , that is, the rotor automatic positioning device 4 is composed of a spring between two rotors corresponding to the rotor 5 and a limiting member positioned at a position parallel to the fuselage when the corresponding two rotors are folded, the limiting component can The positioning block may also be a positioning bayonet. When the rotor is stationary, the elastic component and the limiting component of the rotor automatic positioning device 4 automatically gather the rotor 5 to be positioned rearwardly parallel to the fuselage 16. When the rotor 5 rotates, due to the powerful The centrifugal force is greater than the contraction force of the elastic component of the automatic positioning device 4, so that the rotor 5 rotates in an X shape. When the rotor 5 rotates, it generates a rising force, which drives the aircraft to take off and land vertically, and generates a reaction force to the aircraft. The reaction is detected by a snail. Force, and thereby control the balance of the reaction vector tail nozzle 8 in the opposite direction of the reaction force and the reaction force generated by the downward jet, stabilizing the aircraft Ascending and advancing, the counteracting force can also be offset by the steering vector tail pipe 8 to the left or right of the front, depending on the reaction force generated by the rotation direction of the rotor 5, and a controllable closed nozzle is provided through The snail controls the thrust of the auxiliary nozzle to counteract this reaction force. When the aircraft is flying flat, the auxiliary nozzle is closed. With this structure, the steering vector tail nozzle 8 only needs to generate thrust downward and backward without having to (left or right) The left and right thrusts are generated. When the airplane is raised to a certain level and turned to level flight, the speed reducer 13 is disconnected from the transmission shaft 11 via the clutch 12, and the steering vector tail nozzle 8 is turned rearward to propel the aircraft to accelerate flight, the speed reducer 13 and the transmission. After the shaft 11 is disconnected, the rotor 5 stops rotating, the rotor 5 loses centrifugal force, the rotor automatic positioning device 4 automatically closes the rotor 5, the rotor shaft automatic positioning device 15 is composed of a positioning member and a locking member, and the rotor shaft automatic positioning device 15 rotates the rotor The shaft 3 is fixed at a position parallel to the rotor cabin 2 after the rotor 5 is closed, and then the rotor cabin 2 is opened, and the rotor shaft expansion device 14 causes the rotor shaft 3 and the rotor 5 to contract into the rotor 2, the rotor cabin 2 is closed, the aircraft enters a normal level flight state, the rotor shaft expansion device 14 is composed of a hydraulic expansion member and its related components, the telescopic and torque transmission is a spline transmission structure, and the rotor 5 and the rotor shaft 3 are horizontally hinged. And vertical hinge The chain connection, the horizontal hinge connection and the helicopter rotor are connected to the rotor shaft in the same way to prevent the aircraft from shaking. The vertical hinge is for the rotor 5 to be automatically deployed and automatically positioned and folded.

In Figure 2, the rotor 5 of the vertical take-off and landing aircraft mounted on the upper part of the fuselage 16 is in the form of a coaxial double-rotor, and the rotor shaft 3 is a coaxial reverse-rotating rotor shaft. The reaction force generated by the rotor is due to the use of the coaxial reversing double-rotor. They cancel each other out, so that the aircraft can smoothly take off and land smoothly. At this time, the steering vector tail pipe 8 only needs to turn downward and rear to provide auxiliary lift and forward thrust for the aircraft.

In Fig. 3, the speed reducer 13 can be coupled to a plurality of aero engines, the aero engine 10 is coupled to the clutch 12, and the steerable vertical tail 20 is provided with an auxiliary aero engine 17, via the corresponding two transmission shafts 11, clutch 12 and The two aero engines 10 are arranged in parallel, and the clutches 12 are respectively mounted on the two aero engines 10. The vertical working principle of the lifting and lowering is the same as that of FIG. 1, and the reaction force generated by the rotor 5 is detected by the snail and controlled thereby. The auxiliary aeroengine 17 (thrust and direction) on the traversable vertical tail 20 is controlled to balance and generate forward thrust. After the airplane is leveled, the auxiliary aeroengine 17 nozzle mounted on the steerable vertical tail 20 is adjusted. The thrust is then generated to assist the aircraft in advancing, and steering the direction of the auxiliary aeroengine 17 mounted on the steerable vertical tail 20 also assists in steering the aircraft.

In Fig. 4, the front side of the four aeroengines 10 are provided with a propeller 18, and the auxiliary aeroengine 17 is provided with a propeller 18 at the rear, and the working principle of vertical take-off and landing, leveling and the embodiment shown in Fig. 3 Similarly, in the figure, the rotor 5 is composed of six rotors that are symmetrically placed up and down. If the number of rotor blades is increased, it must be increased in pairs so that the rotors can be staggered when folded.

In FIG. 5, the rotor cabin 2 of the vertical take-off and landing aircraft is respectively provided with two sets of rotors 5 having opposite rotation directions and rotor automatic positioning devices 4 corresponding to the rotors 5, a rotor shaft expansion device 14, a speed reducer 13, a transmission shaft 11, and Clutch 12, aero engine 10, aero engine 10 are divided into two groups, the former group is two parallel aero engines 10, providing the front rotor 5 vertical take-off and landing power and front flying power, followed by a single aero engine 10 installed at the rear of the aircraft, providing the rear rotor 5 vertical take-off and landing power and front flying power, the front and rear rotors 5 due to the opposite direction of rotation, The reaction forces generated by the front and rear rotors 5 cancel each other out, so that the vertical take-off and landing aircraft can smoothly take off and land. Since the rotor 5 is rearward, the vertical tail 6 is installed downward.

In Fig. 6, the rotor 5 of the vertical take-off and landing aircraft mounted on the upper part of the fuselage 16 is in the form of a coaxial double-rotor, and the rotor shaft 3 is a coaxial reversing rotor shaft. The reaction of the rotor is caused by the use of the coaxial reversing double rotor. The forces cancel each other out, allowing the aircraft to smoothly take off and land vertically. The front part of the aero engine 10 is connected to the propeller 18 via the clutch 12 and the transmission shaft 11. The rear part is connected to the reducer 13 via the clutch 12 and the transmission shaft 11. The adjustable rotor support rod 19 is mounted on the top of the fuselage 16 and the adjustable rotor The fixed rod 19 is retracted when the vertical take-off and landing aircraft is vertically taken off and landing, and protrudes at the rear of the fixed rotor 5 when the aircraft is flying flat, so that the rotor 5 does not swing when the aircraft is flying flat.

Claims

1. A vertical take-off and landing aircraft, including a cockpit (1), a fuselage (16), an aeroengine (10), a wing (9), a horizontal tail (7), a vertical tail (6), a reducer (13) And the control system, the aero engine (10) is connected to the reducer (13) via the transmission shaft (11), the clutch (12), and the steering vector tail nozzle is mounted on the rear of the aeroengine (10)

(8), the upper part of the fuselage (16) is equipped with a rotor (5), and the rotor (5) is connected with a rotor shaft (3), and the vertical take-off and landing aircraft is further provided with a rotor shaft expansion device (14) and can accommodate An openable and rotatable rotor cabin (2) of the gathered rotor, the openable and rotatable rotor cabin (2) is disposed on the top of the fuselage (16), the rotor shaft (3) and the speed reducer (13) The rotor shaft telescopic device (14) is connected, the rotor (5) is equipped with a rotor automatic positioning device (4), and the rotor shaft (3) is provided with a rotor shaft automatic positioning device (15).

2. The VTOL aircraft according to claim 1, wherein the rotor automatic positioning device (4) is composed of an elastic member and a limiting member for automatically positioning the rotor (5) in a position with the body. 16 parallel positions.

3. The VTOL aircraft according to claim 1, wherein the rotor shaft automatic positioning device (15) is composed of a positioning component and a locking component, and when the rotor (5) is gathered, the The rotor shaft (3) is fixed at a position where the gathered rotor (5) is parallel to the rotor cabin (2).

4. The VTOL aircraft according to claim 1, wherein the rotor shaft expansion device (14) comprises a hydraulic expansion member for extending the rotor shaft (3) and the rotor (5) The rotorcraft (2) is either retracted into the rotorcraft (2).

5. The VTOL aircraft according to claim 1, wherein the rotor cabin (2) is provided with a rotor hatch cover, and when the aircraft moves up and down vertically, the rotor wing cover is folded to the left and right sides. So that the gathered rotor can extend or retract into the rotor cabin

(2) inside, when the plane is flying flat, the rotor (5) gathers and retracts into the rotor cabin (2), The rotor pod cover is closed toward the middle to close the rotor pod (2).

6. The vertical takeoff and landing aircraft according to claim 1, wherein the rotor (5) structure is a coaxial reversing double rotor, and the rotor shaft (3) is a coaxial reversing rotor shaft.

7. The VTOL aircraft according to claim 1, wherein the speed reducer (13) is connectable to a plurality of aircraft engines, the aircraft engine (10) is coupled to the clutch (12), and the steerable vertical tail (20) is mounted. There are auxiliary aviation engines (17).

8. A VTOL aircraft according to claim 1 or 7, characterized in that the aero-engine (10) is provided with a propeller (18) at the front and a propeller (18) at the rear of the auxiliary aeroengine (17).

9. The vertical take-off and landing aircraft according to claim 1 or 7, characterized in that the front and rear portions of the rotor cabin (2) are respectively equipped with a rotor (5) and a corresponding rotor shaft (3), and the rotor is automatically positioned. The device (4), the speed reducer (13), the rotor shaft automatic positioning device (15), the rotor shaft telescopic device (14), the drive shaft (11), the aeroengine (10), and the vertical tail (6) are mounted downward.

10. The vertical take-off and landing aircraft according to claim 1 or 2, characterized in that the rotor (5) on the upper part of the fuselage (16) is a coaxial double-rotor, and the rotor shaft (3) is a coaxial reverse-rotor axis. The front part of the aeroengine (10) is connected to the propeller (18) via the clutch (12), the drive shaft (11), and the rear is connected to the reducer (13) via the clutch (12) and the transmission shaft (11). 16) Adjustable rotor retaining rod (19) at the top rear.