Aerospace transport plane auxiliary lifting system

Abstract

The invention relates to the technical field of aviation systems, and discloses an air-sky transport plane auxiliary lifting system which comprises an air-sky transport plane, a cold launching device, a rocket sled and a curve track, the curve track is arranged on a high ground, the rocket sled is arranged in the curve track in a sliding mode, and the cold launching device is arranged on the rocket sled. And the cold emission device is movably connected with an aerial conveyor. The method is an efficient, safe and economical take-off and landing strategy capable of meeting the take-off and landing stage requirements of the aerospace transporter at the same time, the weight change, take-off and landing performance, safety and economical efficiency of the aerospace transporter are comprehensively considered, meanwhile, the lift force characteristic of the aerospace transporter is fully utilized, an energy conversion and buffering mechanism in the take-off and landing process is optimized, and the takeoff and landing efficiency is improved. And a more efficient, safer and more economical take-off and landing process is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation systems, and in particular to an auxiliary take-off and landing system for an aerospace transport aircraft. Background Art

[0002] For aerospace transport aircraft with significant take-off and landing weight differences, existing take-off and landing strategies have obvious limitations. Traditional take-off and landing schemes generally rely on wheeled autonomous horizontal take-off and landing, but this method faces many challenges on aerospace transport aircraft. The design of wheeled landing gear becomes complicated and costly due to the dramatic weight changes during the take-off and landing phases caused by fuel consumption. The tires, landing gear and braking systems required for large transport aircraft are not only bulky, but also expensive to manufacture, which not only increases the weight but also reduces the payload of the transport aircraft. In addition, during landing, there is a lack of sufficient adjustment time in the case of long taxiing distances and emergency landings, making it difficult for these schemes to meet the comprehensive needs of the two stages of take-off and landing. Although the combination of horizontal assisted take-off and conventional landing is suitable for the take-off of heavy aerospace transport aircraft, in the case of take-off failure and emergency landing, the transport aircraft lacks sufficient emergency handling time to ensure a safe landing. On the other hand, although the vertical take-off and conventional landing scheme can solve the above problems, it fails to fully utilize the lift generated by the aerospace transport aircraft's own wing profile, and at the same time has extremely high performance requirements for aircraft engines.

[0003] Therefore, although the solution of horizontal assisted takeoff combined with conventional landing is considered to be a superior option under the current circumstances, the problem of insufficient emergency response time after the assisted takeoff fails still needs to be solved. In previous technologies, a rocket sled combined with a mechanical locking mechanism was used to assist takeoff, but there is still a risk of damage to the airframe of the aerospace transport aircraft during load separation. In order to overcome the limitations of the existing solutions, further research and innovation are needed to develop an efficient, safe and economical take-off and landing strategy that can simultaneously meet the take-off and landing needs of the aerospace transport aircraft. Summary of the invention

[0004] The purpose of the present invention is to provide an auxiliary take-off and landing system for an aerospace transport aircraft to solve the problems existing in the above-mentioned prior art and to meet the requirements of the take-off and landing stages of the aerospace transport aircraft in an efficient, safe and economical manner.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] The present invention provides an auxiliary take-off and landing system for an aerospace transport aircraft, comprising an aerospace transport aircraft, a cold launch device, a rocket sled and a curved track, wherein the curved track is arranged on a high ground, the rocket sled is slidably arranged in the curved track, the cold launch device is arranged on the rocket sled, and the aerospace transport aircraft is movably connected to the cold launch device.

[0007] Preferably, the cold launch device includes an ejection rod, an ejection mechanism and a launch tube, the upper end of the ejection rod is fixedly connected to the bottom of the aerospace transport aircraft, and the lower end is movably mounted in the launch tube, a telescopic rod is provided on the side wall of the launch tube, and an ejection hole is provided on the bottom, the ejection mechanism is connected to the ejection hole, a locking hole is provided on the ejection rod, the telescopic rod and the locking hole are arranged in a one-to-one correspondence, and the telescopic rod can be inserted into the locking hole after being extended.

[0008] Preferably, the telescopic rod is an electric push rod, a hydraulic rod or a pneumatic rod.

[0009] Preferably, the ejection mechanism includes a high-pressure gas source tank, the ejection hole is connected to the high-pressure gas source tank via a pipeline, a solenoid valve is provided on the pipeline, and the solenoid valve is communicatively connected to the control unit; the launch tube and the high-pressure gas source tank can be detachably connected to the rocket sled, and two groups of the high-pressure gas source tank and the launch tube are provided.

[0010] Preferably, the rocket sled includes a rocket sled body, wheels and a rocket engine, the rocket engine is plugged into the rocket sled body, two pairs of wheels are provided at the bottom of the rocket sled body, and the wheels are rollingly connected to the bottom surface of the curved track.

[0011] Preferably, front wings and rear wings are symmetrically arranged at both ends of the rocket sled body, and side guide wheels are arranged on the front wings and the rear wings, and the side guide wheels are rollingly connected to the side surfaces of the curved track.

[0012] Preferably, the curved track is an arc track with a radius of at least 350m and a central angle of 90° to 110°, and the cross-section of the curved track is U-shaped.

[0013] Preferably, the side of the starting end of the curved track is open and the side of the terminal end is closed, and a buffer is provided at the terminal end of the curved track, and the buffer can buffer the residual kinetic energy of the rocket sled body.

[0014] Preferably, the buffer includes a piston housing, a piston, a piston rod, a return spring and a closed air chamber, the piston is slidably arranged in the piston housing, one end of the piston rod passes through the piston housing and is connected to a pressure plate, and the other end is provided with the closed air chamber, the return spring is sleeved on the piston rod between the pressure plate and the piston housing, a flow hole is provided on the piston ring, a pressure relief valve is slidingly and sealably connected in the closed air chamber, one end of the pressure relief valve is provided with a convex column matching the flow hole, and the other end is provided with a limiting column, the length of the limiting column is 1mm-5mm, gas is sealed in the closed air chamber, and the piston housing seals and contains oil.

[0015] Preferably, the high ground is a rectangular block and the upper surface is at least 2000m from the ground.

[0016] Compared with the prior art, the present invention has achieved the following technical effects:

[0017] The present invention effectively solves the problem of long taxiing distance caused by the heavy weight of the aerospace transport aircraft, improves the take-off and landing efficiency, and reduces the requirements for airport infrastructure; through the introduction of cold launch technology, it effectively avoids the potential damage to the aerospace transport aircraft body during the load separation process of the traditional mechanical locking mechanism, thereby significantly improving the safety of the take-off phase; the use of a curved track optimizes the take-off process, effectively reducing the straight-line distance required for assisted take-off, thereby reducing dependence on specific terrain conditions and the difficulty of selection; the natural height difference of the terrain is used to provide the necessary time and space for the aerospace transport aircraft to reduce the descent rate and speed by circling. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 The structure of the auxiliary take-off and landing system of the aerospace transport aircraft in the embodiment of the present invention is shown in FIG. Figure 1 ;

[0020] Figure 2 The structure of the auxiliary take-off and landing system of the aerospace transport aircraft in the embodiment of the present invention is shown in FIG. Figure 2 ;

[0021] Figure 3 It is a schematic diagram of the structure of the cold emission device in an embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of the assembly structure of a rocket sled in an embodiment of the present invention;

[0023] Figure 5 Schematic diagram of the internal structure of a rocket sled in an embodiment of the present invention;

[0024] Figure 6 A schematic diagram of the structure of a buffer in an embodiment of the present invention;

[0025] Figure 7 A schematic diagram of the landing process of an air-space transport aircraft in an embodiment of the present invention;

[0026] In the figure: 1-aerospace transport aircraft, 2-ejection rod, 3-cold launch device, 4-ejection mechanism, 5-telescopic rod, 6-launching tube, 7-ejection hole, 8-rocket sled, 9-rocket sled body, 10-wheel, 11-front wing, 12-rear wing, 13-side guide wheel, 14-rocket engine, 15-high pressure gas source tank, 16-pipeline, 17-solenoid valve, 18-curved track, 19-buffer, 20-piston rod, 21-pressure relief valve, 22-buffer housing, 23-reset spring, 24-high ground. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] The purpose of the present invention is to provide an auxiliary take-off and landing system for an aerospace transport aircraft to solve the problems existing in the prior art and to meet the requirements of the take-off and landing stages of the aerospace transport aircraft in an efficient, safe and economical manner.

[0029] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0030] Embodiment 1

[0031] like Figures 1 to 7 As shown, in this embodiment, an auxiliary take-off and landing system for an aerospace transport aircraft 1 is provided, including an aerospace transport aircraft 1, a cold launch device 3, a rocket sled 8 and a curved track 18. The curved track 18 is arranged on a high ground 24. A rocket sled 8 is slidably arranged in the curved track 18. The rocket sled 8 is provided with a cold launch device 3, and the aerospace transport aircraft 1 is movably connected to the cold launch device 3. This embodiment is an efficient, safe and economical take-off and landing strategy that can simultaneously meet the take-off and landing requirements of the aerospace transport aircraft 1. It comprehensively considers the weight change, take-off and landing performance, safety and economy of the aerospace transport aircraft 1, and fully utilizes the lift characteristics of the aerospace transport aircraft 1 itself, optimizes the energy conversion and buffer mechanism during the take-off and landing process, and realizes a more efficient, safe and economical take-off and landing process. In this embodiment, the curved track 18 is preferably cast with reinforced concrete, and the high ground 24 is preferably on a flat ground on the top of a mountain with a drop to reduce construction costs.

[0032] As an optional solution, the cold launch device 3 in this embodiment includes a launch rod 2, a launch mechanism 4 and a launch tube 6. The upper end of the launch rod 2 is fixedly connected to the bottom of the aerospace transport aircraft 1, and the lower end is movably sleeved in the launch tube 6. A telescopic rod 5 is provided on the side wall of the launch tube 6, and an ejection hole 7 is provided at the bottom. The ejection mechanism 4 is connected to the ejection hole 7. A locking hole is provided on the launch rod 2. The telescopic rod 5 is arranged one-to-one with the locking hole. The telescopic rod 5 can be inserted into the locking hole after being extended. Compared with the take-off and landing scheme of the aerospace transport aircraft 1 with landing gear, the cold launch device 3 in this embodiment avoids the complexity of the design of key components such as the landing gear, tires, and brakes caused by the huge weight change before and after the take-off and landing of the aerospace transport aircraft 1, greatly reduces the manufacturing cost, and also significantly improves the effective carrying capacity of the aerospace transport aircraft 1, enhancing its commercial competitiveness and practicality; at the same time, it also effectively solves the problem of long taxiing distance caused by the heavy weight of the aerospace transport aircraft 1, improves the take-off and landing efficiency, and reduces the requirements for airport infrastructure.

[0033] As an optional solution, the telescopic rod 5 in this embodiment is an electric push rod, a hydraulic rod or a pneumatic rod. If the aerospace transport aircraft 1 does not reach the predetermined take-off speed, the telescopic rod 5 will continue to play its locking and shock-absorbing role to ensure that the aerospace transport aircraft 1 can perform stable auxiliary acceleration during the ground stage; conversely, once the aerospace transport aircraft 1 reaches the predetermined take-off speed, the speed sensor immediately activates the telescopic rod 5 controlled by the electronic control system, causing its front end to quickly retract into the actuator cylinder, thereby automatically unlocking the ejection rod 2. At this time, the ejection mechanism 4 controlled by the speed sensor is started, and the aerospace transport aircraft 1 is ejected to a certain height, allowing the aerospace transport aircraft 1 to perform the take-off action. Figure 2 As shown, the cold launch device 3 is designed to be reusable.

[0034] As an optional solution, the ejection mechanism 4 in this embodiment includes a high-pressure gas source tank 15, and the ejection hole 7 is connected to the high-pressure gas source tank 15 through a pipeline 16. The pipeline 16 is provided with a solenoid valve 17, and the solenoid valve 17 is communicatively connected to the control unit; the launch tube 6 and the high-pressure gas source tank 15 can be detachably connected to the rocket sled 8, and two groups of high-pressure gas source tanks 15 and launch tubes 6 are provided. Among them, when it is necessary to eject the aerospace transport aircraft 1, the control unit activates the solenoid valve 17 to allow the high-pressure gas source tank 15 to transport high-pressure gas to the ejection hole 7 for ejection. The ejection high-pressure gas source is about 50MPA, which can play an instant ejection boosting role for the ejection rod 2.

[0035] As an optional solution, the rocket sled 8 in this embodiment includes a rocket sled 8 body, wheels 10 and rocket engines 14. Several rocket engines 14 are plugged into the rocket sled 8 body. Several pairs of wheels 10 are arranged at the bottom of the rocket sled 8 body, and the wheels 10 are rollingly connected to the bottom surface of the curved track 18. In this embodiment, during the take-off stage of the aerospace transport aircraft 1, the rocket engine 14 is ignited, which can provide the rocket sled 8 with centripetal force to run on the curved track 18 and maintain the directional stability of the rocket sled 8; the rocket sled 8 has efficient short-distance acceleration capability, which is particularly suitable for taking off the aerospace transport aircraft 1 with a large load, avoiding the sacrifice of the load capacity of the aerospace transport aircraft 1. When the aerospace transport aircraft 1 reaches the predetermined take-off speed, the speed sensor controls the high-pressure gas source tank 15 to deliver high-pressure gas, which is transmitted to the interface 7 through the pipeline 16 to provide the required gas source for the operation of the cold launch device 3. When the aerospace transport aircraft 1 completes the takeoff process, the rocket engine 14 will be shut down, and the rocket sled 8 will continue to consume the remaining kinetic energy through the rolling of the guide wheels 10 and the side guide wheel group 13 until its front end contacts the buffer 19 set at the end of the curved track 18 to achieve a safe stop; through the introduction of cold launch technology, the potential damage to the body of the aerospace transport aircraft 1 during the load separation process of the mechanical locking mechanism is effectively avoided, thereby significantly improving the safety of the takeoff phase. Compared with the previous auxiliary takeoff technology using the rocket sled 8 combined with the load separation of the mechanical locking mechanism, this improvement not only ensures the integrity of the transport aircraft structure, but also reduces the safety risks caused by mechanical failures, providing a more reliable and safe technical guarantee for the takeoff of air transport aircraft.

[0036] As an optional solution, in this embodiment, front wings 11 and rear wings 12 are symmetrically arranged at both ends of the rocket sled 8 body, and side guide wheels 13 are arranged on the front wings 11 and the rear wings 12. The side guide wheels 13 are rollingly connected to the side of the curved track 18 to avoid friction damage between the rocket sled 8 body and the side of the curved track 18.

[0037] As an optional solution, the curved track 18 in this embodiment is an arc track with a radius of at least 350m and a central angle of 90° to 110°. The cross section of the curved track 18 is U-shaped, which provides necessary support and guidance for the rocket sled 8. In this embodiment, the curved track 18 is used. Compared with the previous use of the straight track assisted takeoff technology, this design optimizes the takeoff process and effectively reduces the straight-line distance required for assisted takeoff, thereby reducing the dependence on specific terrain conditions and the difficulty of selection; under the requirements of the pulley structure strength, the curvature of the curved track 18 is designed to reduce the requirements for the plane space size as much as possible. In this embodiment, the width of the track is not less than 7m, the inner diameter of the radius of the curved track 18 is preferably 382m, the width of the rocket sled 8 is 4m, and the length is not more than 36m; the predetermined takeoff speed is set for the aircraft to have insufficient lift to drive the rocket sled 8 with considerable mass off the ground before reaching the takeoff speed, and even if it has just reached it, it cannot carry the weight of the rocket sled 8 to cause jumping and derailment, and the vertical friction generated by four groups of 8 lateral guide wheels is sufficient to keep it on track.

[0038] As an optional solution, in this embodiment, the side of the starting end of the curved track 18 is open and the side of the terminal end is sealed. A buffer 19 is provided at the terminal end of the curved track 18, and the buffer 19 can buffer the residual kinetic energy of the rocket sled 8. When the piston rod 20 of the buffer 19 is pressed inward, the oil hole is opened by the pressure relief valve 21, which is pressed into the enclosed gas air, that is, the space of this section of the sealed air is compressed, so that the flow hole becomes larger.

[0039] As an optional scheme, the buffer 19 in this embodiment includes a piston housing, a piston, a piston rod 20, a return spring 23 and a closed air chamber, a piston is slidably arranged in the piston housing, one end of the piston rod 20 passes through the piston housing and is connected to a pressure plate, and the other end is provided with a closed air chamber, a return spring 23 is sleeved on the piston rod 20 between the pressure plate and the piston housing, a flow hole is provided on the piston ring, a pressure relief valve 21 is slidably and sealably connected in the closed air chamber, a convex column matching the flow hole is provided at one end of the pressure relief valve 21, and a limiting column is provided at the other end, the length of the limiting column is 1mm-5mm, gas is sealed in the closed air chamber, and oil is sealed in the piston housing to form a closed hydraulic system. In this embodiment, the pressure plate and the piston rod 20 are squeezed, causing the pressure relief valve 21 to slide into the closed air chamber, thereby opening the flow hole, thereby quickly releasing the internal high-pressure oil into the closed air chamber, producing a damping effect. Through this energy conversion process, the buffer 19 can effectively absorb the kinetic energy of the rocket sled 8 body and achieve its safe stop, which not only improves the take-off efficiency, but also ensures the safety and reliability of the entire take-off process.

[0040] As an optional solution, the high ground 24 in this embodiment is a rectangular block and the upper surface is at least 2000m from the ground. Compared with the traditional take-off and landing scheme of the aerospace transport aircraft 1, this embodiment fully considers the complexity of emergency landing, introduces the design of terrain height, and allows the use of the natural height difference of the terrain in the face of an emergency to ensure that the aerospace transport aircraft 1 is provided with sufficient space and time to adjust the flight attitude and hover and land, so as to enhance the safety and reliability of the system. The height design of the high ground 24 comprehensively considers a variety of emergency situations. This design not only significantly improves the survivability of the aerospace transport aircraft 1 in the face of an emergency, but also improves the efficiency and accuracy of the aerospace transport aircraft 1 during normal landing. It also greatly enhances the response capability and safety guarantee in emergency situations, reflecting the foresight, adaptability and comprehensiveness of the system design.

[0041] Embodiment 2

[0042] like Figure 7 As shown, this embodiment provides an auxiliary take-off and landing operation method for an aerospace transport aircraft 1 based on a cold launch system, and its specific working principle and process are as follows:

[0043] During the take-off phase, the ignition of the rocket engine 14 triggers the generation of kinetic energy of the rocket sled 8. During this process, the precisely designed guide wheel system maintains close contact with the curved track 18, and the rolling of the side guide wheel group and the side wall of the track ensures the stable forward movement and directional stability of the rocket sled 8. At the same time, the cold launch device 3 with a locking function firmly locks the aerospace transport aircraft 1 on the rocket sled 8 to achieve synchronous acceleration.

[0044] When the transport aircraft reaches the predetermined take-off speed, the speed sensor automatically triggers the telescopic rod 5 in the cold launch device 3 to unlock, and the high-pressure gas source tank 15 is immediately started. The high-pressure gas enters the ejection mechanism 4 through the pipeline 16, triggering the ejection mechanism, so that the aerospace transport aircraft 1 is separated from the rocket sled 8 and ejected to a certain height to perform the take-off action. After completing its boosting mission, the rocket sled 8 turns off the rocket engine 14 and continues to move forward to release the remaining kinetic energy until the front end contacts the pressure plate of the buffer 19 at the end of the track. At this time, the piston rod 20 is compressed to produce high-pressure oil. As the pressure of the high-pressure oil increases, the pressure relief valve 21 opens, and then the internal high-pressure oil is quickly released. Through this energy conversion process, a damping effect is produced, and the buffer 19 effectively absorbs the kinetic energy of the rocket sled 8 to achieve its safe stop.

[0045] When the aerospace transport aircraft 1 needs to make an emergency landing during takeoff, the terrain height difference of the high ground 24 can provide the aerospace transport aircraft 1 with sufficient time and space to hover and adjust the descent rate and speed. This design ensures that the aerospace transport aircraft 1 can achieve a smooth landing after reaching a safe landing speed.

[0046] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An auxiliary take-off and landing system for an aerospace transport aircraft, characterized in that: It includes an aerospace transport aircraft, a cold launch device, a rocket sled and a curved track. The curved track is set on a high ground. The rocket sled is slidably set in the curved track. The cold launch device is set on the rocket sled. The aerospace transport aircraft is movably connected to the cold launch device.

2. The aerospace transport aircraft auxiliary take-off and landing system according to claim 1, characterized in that: The cold launch device includes an ejection rod, an ejection mechanism and a launch tube. The upper end of the ejection rod is fixedly connected to the bottom of the aerospace transport aircraft, and the lower end is movably mounted in the launch tube. A telescopic rod is provided on the side wall of the launch tube, and an ejection hole is provided at the bottom. The ejection mechanism is connected to the ejection hole. A locking hole is provided on the ejection rod. The telescopic rod and the locking hole are arranged in a one-to-one correspondence. The telescopic rod can be inserted into the locking hole after being extended.

3. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 2, characterized in that: The telescopic rod is an electric push rod, a hydraulic rod or a pneumatic rod.

4. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 2, characterized in that: The ejection mechanism includes a high-pressure gas source tank, the ejection hole is connected to the high-pressure gas source tank via a pipeline, a solenoid valve is provided on the pipeline, and the solenoid valve is communicatively connected to the control unit; the launch tube and the high-pressure gas source tank can be detachably connected to the rocket sled, and two groups of the high-pressure gas source tank and the launch tube are provided.

5. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 1, characterized in that: The rocket sled includes a rocket sled body, wheels and a rocket engine. The rocket engine is plugged into the rocket sled body. Two pairs of wheels are arranged at the bottom of the rocket sled body. The wheels are rollingly connected to the bottom surface of the curved track.

6. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 5, characterized in that: Front wings and rear wings are symmetrically arranged at both ends of the rocket sled body, and side guide wheels are arranged on the front wings and the rear wings, and the side guide wheels are rollingly connected to the side surfaces of the curved track.

7. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 1, characterized in that: The curved track is an arc track with a radius of at least 350m and a center angle of 90° to 110°, and the cross section of the curved track is U-shaped.

8. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 1, characterized in that: The side of the starting end of the curved track is open, and the side of the terminal end is closed. A buffer is arranged at the terminal end of the curved track, and the buffer can buffer the residual kinetic energy of the rocket sled body.

9. The aerospace transport aircraft assisted take-off and landing system according to claim 8, characterized in that: The buffer includes a piston housing, a piston, a piston rod, a return spring and a closed air chamber, the piston housing is slidably provided with the piston, one end of the piston rod passes through the piston housing and is connected to a pressure plate, the other end is provided with the closed air chamber, the piston rod between the pressure plate and the piston housing is sleeved with the return spring, the piston ring is provided with a flow hole, the closed air chamber is slidingly and sealably connected with a pressure relief valve, one end of the pressure relief valve is provided with a convex column matching the flow hole, the other end is provided with a limiting column, the length of the limiting column is 1mm-5mm, gas is sealed in the closed air chamber, and the piston housing seals and contains oil.

10. The auxiliary take-off and landing system for aerospace transport aircraft according to claim 1, characterized in that: The high ground is a rectangular block and the upper surface is at least 2000m from the ground.

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