CN111977009A

CN111977009A - Airplane take-off device and take-off method

Info

Publication number: CN111977009A
Application number: CN202010639740.5A
Authority: CN
Inventors: 李明祥; 何刚; 翟建武; 陈勇; 杨程丽
Original assignee: Xian Aircraft Industry Group Co Ltd
Current assignee: Xian Aircraft Industry Group Co Ltd
Priority date: 2020-07-06
Filing date: 2020-07-06
Publication date: 2020-11-24

Abstract

The application discloses a device for aircraft takes off, mainly by the fixed axle, the ring body, the swinging boom, aircraft supporting platform, the fixed cardboard of aircraft, the engine, hydraulic telescoping rod, the swinging boom bracing piece, hydraulic elevating platform, embrace the circle, the oil tank is constituteed, the device passes through fixed axle and ground fixed connection, swinging boom one end and ring body fixed connection, the other end is connected with aircraft supporting platform, the engine axle center is perpendicular with the swinging boom, light the engine and make aircraft supporting platform carry the aircraft and do the circular motion, hydraulic telescoping rod carries out the telescoping control according to the centrifugal force change of aircraft, ensure aircraft acceleration safety, when reaching the speed of taking off, the fixed cardboard of aircraft is opened, the aircraft flies from aircraft supporting platform, accomplish the operation of taking off, realize that the aircraft need not runway and walk away.

Description

Airplane take-off device and take-off method

Technical Field

The application relates to the technical field of unmanned aerial vehicle design and manufacture, in particular to a vertical take-off and landing variable wing cruising heavy-load unmanned aerial vehicle.

Background

The prior airplane assisted take-off has three modes: the aircraft adopts a slipping takeoff mode, an ejection takeoff mode and a vertical takeoff mode, wherein the slipping takeoff mode is to take off by providing extra lift force for the aircraft by an upwarping angle at the front end of a runway, the lift force of the aircraft and the thrust of an engine, and the aircraft cannot take off in a full-load state due to the limitation of the length of the runway, so that the performance of the aircraft is limited; the ejection type takeoff mode mainly depends on steam ejection and electromagnetic ejection, and the steam ejection device has large volume, occupies space, consumes a large amount of fresh water resources and has serious power waste; the existing vertical takeoff mode requires that the airplane has a vertical take-off and landing function, is complex to operate, but cannot take off in full load, and limits the performance of the airplane.

The airplane takeoff mode in the prior art can not achieve runway run-up, steam power assistance, electric power assistance and full-load takeoff at the same time, and the performance of the airplane is severely limited.

In order to solve the problems, a device which does not occupy limited space and can take off the airplane in a full load manner is needed, and the performance of the airplane is fully exerted.

Disclosure of Invention

The invention aims to solve the problems in the prior art and provides a take-off device and a take-off method for an airplane.

In order to achieve the purpose, the technical scheme adopted by the invention is as follows:

an aircraft takeoff device comprises a fixed shaft, an annular body, a rotating arm, an aircraft supporting platform, an aircraft fixing clamping plate, an engine, a hydraulic telescopic rod, a rotating arm supporting rod, a hydraulic lifting platform, a holding ring and an oil tank, wherein the fixed shaft is fixed on the ground and penetrates through the annular body, and the annular body is an inverted 'convex' type stepped ring structure and is sleeved on the fixed shaft. The fixed shaft is movably connected with the annular body through a ball bearing. One side of the annular body is fixedly connected with the rotating arm, the other side of the annular body is fixedly provided with an oil tank, the other end of the rotating arm is movably connected with the aircraft supporting platform through a rotating shaft, a rotating arm supporting rod is fixed at the bottom of the rotating arm, the bottom center position of the aircraft supporting platform is provided with an engine, the axis of the engine is vertical to the rotating arm, and an angle of 0-45 degrees is formed between the engine and the upper surface of the aircraft supporting platform, the bottom of the aircraft supporting platform is close to one side of the rotating arm and is movably connected with one end of the rotating arm supporting rod through a hydraulic telescopic rod, the inclination angle of the aircraft supporting platform is adjusted according to the change of centrifugal force, the hydraulic lifting platform is of an annular structure, the hydraulic lifting platform is sleeved on the annular body in a clearance fit mode, when the airplane drives to the airplane supporting platform, the airplane is fixed by the airplane fixing clamping plate.

An aircraft takeoff method comprising the steps of:

1, enabling the upper surfaces of the rotating arm and the airplane supporting platform to coincide with the ground surface, and enabling the annular body to be ejected out of the ground by the hydraulic lifting platform to ensure that the rotating arm can do an obstacle-free circular motion position around the fixed shaft;

2 igniting the engine to make the airplane supporting platform carry the airplane to do circular motion, the hydraulic telescopic rod performs telescopic control according to the change of the centrifugal force of the airplane to ensure the acceleration safety of the airplane, when the take-off speed of the airplane is reached, the airplane fixing clamping plate is opened, the airplane flies off the airplane supporting platform to complete the take-off operation,

and 3, braking the annular body through the holding turns to prepare for taking off of the next airplane.

Compared with the prior art, the invention has the advantages that: the aircraft take-off device takes the fixed shaft as the center, takes the rotating arm as the radius, takes the engine on the rotating arm as the main power to do circular variable speed motion, and the aircraft rotates and accelerates along with the rotating arm to reach the take-off speed, so that the aircraft does not need runway run-up, steam power assistance, electric power assistance and full load take-off, and the performance of the aircraft is effectively improved.

Drawings

FIG. 1 installation profile of the device on the ground

FIG. 2 is a schematic illustration of a structure of a pre-launch loader aircraft

FIG. 3 is a schematic view of the structure of the ground after being started

The numbering in the figures illustrates: 1. a ground surface; 2. a takeoff device; 3. an aircraft; 4. a fixed shaft; 5. an annular body; 6. a rotating arm; 7. an aircraft support platform; 8. an airplane fixing clamping plate; 9. an engine; 10. a hydraulic telescopic rod; 11. a rotating arm support bar; 12. a hydraulic lifting platform; 13. looping; 14. oil tank

Detailed Description

As shown in fig. 1-3, an aircraft takeoff device 2 comprises a fixed shaft 4, an annular body 5, a rotating arm, an aircraft supporting platform 7, an aircraft fixing clamping plate 8, an engine 9, a hydraulic telescopic rod 10, a rotating arm supporting rod 11, a hydraulic lifting platform 12, a holding ring 13 and an oil tank 14, wherein the fixed shaft 4 is fixed on the ground 1 and penetrates through the annular body 5, and the annular body 5 is an inverted 'convex' type stepped ring structure and is sleeved on the fixed shaft 4. The fixed shaft 4 is movably connected with the annular body 5 through a ball bearing. One side of a ring body 5 is fixedly connected with a rotating arm 6, the other side of the ring body is fixedly provided with an oil tank 14, the other end of the rotating arm 6 is movably connected with an airplane supporting platform 7 through a rotating shaft, a rotating arm supporting rod 11 is fixed at the bottom of the rotating arm 6, an engine 9 is arranged at the central position of the bottom of the airplane supporting platform 7, the axis of the engine 9 is vertical to the rotating arm 6, and is adjustable at an angle of 0-45 degrees with the upper surface of the airplane supporting platform 7, the bottom of the airplane supporting platform 7 is close to one side of the rotating arm 6 and is movably connected with one end of the rotating arm supporting rod 11 through a hydraulic telescopic rod 10, the inclination angle of the airplane supporting platform 7 is adjusted according to the change of centrifugal force, a hydraulic lifting platform 12 is of a ring structure, is sleeved on the ring body 5 in a, the device is used for generating friction force with the annular body 5 to realize speed reduction of the device, and the airplane 3 is fixed by the airplane fixing clamping plate 8 when driving onto the airplane supporting platform 7.

An aircraft takeoff method comprising the steps of:

1, the upper surfaces of a rotating arm 6 and an airplane supporting platform 7 are superposed with the ground surface, and a hydraulic lifting platform 12 pushes an annular body 5 out of the ground surface to ensure that the rotating arm 6 can do an obstacle-free circular motion position around a fixed shaft 4;

2, igniting an engine 9 to enable the airplane supporting platform 7 to carry the airplane 3 to do circular motion, carrying out telescopic control by a hydraulic telescopic rod 10 according to the centrifugal force change of the airplane 3 to ensure the acceleration safety of the airplane 3, opening an airplane fixing clamping plate 8 when the takeoff speed of the airplane 3 is reached, enabling the airplane to fly away from the airplane supporting platform 7 to finish the takeoff operation,

and 3, braking the annular body 5 through the holding turns 13 to prepare for taking off of the next airplane.

Claims

1. An aircraft take-off device is characterized by comprising a fixed shaft, an annular body, a rotary arm, an aircraft supporting platform, an aircraft fixing clamping plate, an engine, a hydraulic telescopic rod, a rotary arm supporting rod, a hydraulic lifting platform, a holding ring and an oil tank, wherein the fixed shaft is fixed on the ground and penetrates through the annular body, one side of the annular body is fixedly connected with the rotary arm (6), the other side of the annular body is fixedly provided with the oil tank, the other end of the rotary arm is movably connected with the aircraft supporting platform through a rotating shaft, the rotary arm supporting rod is fixed at the bottom of the rotary arm, the engine is arranged at the center of the bottom of the aircraft supporting platform, the axis of the engine is vertical to the rotary arm and can be adjusted at an angle of 0-45 degrees with the upper surface of the aircraft supporting platform, the bottom of the, the hydraulic lifting platform is of an annular structure, the hydraulic lifting platform is sleeved on the annular body in a clearance fit mode, the bottom of the hydraulic lifting platform is fixed on the ground, the top of the hydraulic lifting platform is movably connected with the bottom of the annular body through a needle bearing, the inner ring surface of the hydraulic lifting platform is provided with an embracing turn for generating friction force with the annular body to realize speed reduction of the device, and when the airplane runs to the airplane supporting platform, the airplane is fixed by the airplane fixing clamping plate.

2. An aircraft take-off device as claimed in claim 1, wherein the annular body is of an inverted "convex" stepped ring configuration fitted over the fixed shaft.

3. An aircraft take-off device as claimed in claim 2, wherein the fixed shaft is movably connected to the annular body by a ball bearing.

4. An aircraft takeoff method is characterized by comprising the following steps:

4-1, enabling the upper surfaces of the rotating arm and the airplane supporting platform to coincide with the ground surface, and enabling the annular body to be ejected out of the ground by the hydraulic lifting platform, so as to ensure that the rotating arm can do an obstacle-free circular motion position around the fixed shaft;

4-2, igniting the engine to enable the airplane supporting platform to carry the airplane to do circular motion, performing telescopic control by the hydraulic telescopic rod according to the change of the centrifugal force of the airplane to ensure the acceleration safety of the airplane, opening the airplane fixing clamping plate when the takeoff speed of the airplane is reached, enabling the airplane to fly away from the airplane supporting platform to finish the takeoff operation,

and 4-3, braking the annular body through the embracing turns to prepare for taking off of the next airplane.