An auxiliary take-off and landing module for emergency landing of aerospace vehicles

Abstract

This invention belongs to the field of aircraft takeoff and landing technology, and particularly relates to an auxiliary takeoff and landing module for emergency landing of aerospace vehicles. It includes: a takeoff and landing module, fixedly installed on a ground facility; two electromagnetic catapult tracks, respectively fixed to the inner top and bottom of the takeoff and landing module; a traction vehicle connected to the electromagnetic catapult tracks; and two airborne traction devices detachably connected to the traction vehicle via an onboard locking device. Two airborne traction devices are respectively installed on the aerospace vehicle, one located at the top of the aerospace vehicle and at the front end in the direction of travel, and the other located at the bottom of the aerospace vehicle and at the rear end in the direction of travel. This invention eliminates the need for landing gear during takeoff and landing, avoiding the problems of insufficient load-bearing capacity due to landing gear not deploying or excessive weight after deployment, and also eliminates the need to release fuel, improving safety during landing and emergency landings.

Description

Technical Field

[0001] This invention belongs to the field of aircraft takeoff and landing technology, and in particular relates to an auxiliary takeoff and landing cabin for emergency landing of aerospace vehicles. Background Technology

[0002] In the design and operation of aerospace vehicles, fuel capacity is a critical factor, directly affecting the takeoff weight and landing gear design standards. In emergency landing situations, it is usually necessary to exhaust the remaining fuel before attempting a landing. To address the issue of insufficient landing gear load-bearing capacity when fuel cannot be consumed during an emergency landing, this invention proposes an auxiliary takeoff and landing module for emergency landing of aerospace vehicles. Summary of the Invention

[0003] The purpose of this invention is to provide an auxiliary take-off and landing module for emergency landing of aerospace vehicles to solve the above-mentioned problems.

[0004] To achieve the above objectives, the present invention provides the following solution:

[0005] An auxiliary landing module for emergency landing of aerospace vehicles includes:

[0006] The takeoff and landing module is fixedly installed on ground facilities.

[0007] Two electromagnetic catapult tracks are provided. The two electromagnetic catapult tracks are respectively fixed to the inner side of the top of the take-off and landing cabin and the inner side of the bottom of the take-off and landing cabin. A tractor is driven and connected inside the electromagnetic catapult tracks. The tractor is detachably connected to the airborne traction device through the vehicle locking device.

[0008] The two airborne traction devices are respectively installed on the aerospace vehicle, one of which is located on the top of the aerospace vehicle and at the front end in the direction of travel, and the other airborne traction device is located at the bottom of the aerospace vehicle and at the rear end in the direction of travel.

[0009] Optionally, the ground facility may be a high ground or an elevated bridge.

[0010] Optionally, buffers are fixed to both ends of the electromagnetic catapult track.

[0011] Optionally, the airborne traction device includes a base fixed to the aerospace vehicle. One end of an actuating rod is rotatably connected to the base via a rotating shaft. The other end of the actuating rod is detachably connected to the traction vehicle via the vehicle-mounted locking device. The rotating shaft is the shaft of a motor, and the fixed end of the motor is fixed inside the base.

[0012] Optionally, the tractor unit includes:

[0013] The vehicle body is slidably connected to the electromagnetic catapult track via guide wheels;

[0014] The vehicle-mounted tow hook module has one end for hooking to the end of the actuating rod away from the base, and the other end of the vehicle-mounted tow hook module is mounted on the vehicle body;

[0015] The vehicle-mounted locking device is installed on the vehicle-mounted tow hook module, and the vehicle-mounted locking device is used to control the vehicle-mounted tow hook module to fix or release the actuating rod;

[0016] The vehicle-mounted buffer module is mounted on the vehicle body at one end, and the other end of the vehicle-mounted buffer module is connected to the vehicle-mounted towing hook module via a transmission connection.

[0017] Optionally, the vehicle-mounted tow hook module includes:

[0018] The vehicle-mounted tow hook base is fixed to the vehicle body;

[0019] The towing hook has one end rotatably connected to the vehicle-mounted towing hook base via a towing hook pivot. A connecting slider is slidably provided in the middle of the towing hook, and the connecting slider is drively connected to the vehicle-mounted buffer module. The other end of the towing hook is provided with a hook groove that hooks onto the end of the actuating rod away from the base.

[0020] Optionally, the vehicle locking device includes:

[0021] Lock the door panel and secure it to the towing hook;

[0022] A locking door is slidably disposed on one side of the locking door panel, and the locking door is used to control the opening and closing of the hook groove;

[0023] The drive unit has one end connected to the locking door panel and the other end connected to the locking door. The drive unit is used to drive the locking door to slide along the locking door panel.

[0024] Optionally, the drive unit includes:

[0025] A primary robotic arm has one end rotatably connected to the locking door panel via a primary pivot, and the other end of the primary robotic arm is hinged to one end of a secondary robotic arm via a secondary pivot. The other end of the secondary robotic arm is hinged to the locking door via a tertiary pivot.

[0026] The locking door is limited by the movable end of an electric actuator, and the fixed end of the electric actuator is fixed to the locking door panel.

[0027] Optionally, the on-board buffer module includes:

[0028] A piston rod, one end of which is rotatably connected to the connecting slider;

[0029] The high-pressure air chamber shell is fixedly connected to the vehicle body, and the air inlet end of the high-pressure air chamber shell is connected to a high-pressure air source, which is fixedly connected to the vehicle body.

[0030] A liquid buffer housing is slidably disposed inside the high-pressure gas chamber housing. A gas chamber pressure relief valve is fixedly connected to the liquid buffer housing. One end of the gas chamber pressure relief valve is connected to the inner cavity of the high-pressure gas chamber housing, and the other end of the gas chamber pressure relief valve is connected to the outside.

[0031] The other end of the piston rod is slidably disposed in an oil cavity opened inside the liquid buffer housing, and a plurality of oil release holes are opened at the end of the piston rod away from the connecting slider.

[0032] Optionally, the buffer includes:

[0033] A buffer housing, wherein one end of a piston is slidably connected inside the buffer housing, and the other end of the piston is used to contact the corresponding tractor vehicle;

[0034] A spring is disposed inside the buffer housing, one end of the spring being fixedly connected to one end of the piston, and the other end of the spring being fixedly connected to the inner wall of the buffer housing.

[0035] The piston is located at one end of the pressure relief chamber and the rebound valve inside the buffer housing, and the pressure relief valve is provided at the inlet end of the pressure relief chamber.

[0036] Compared with the prior art, the present invention has the following advantages and technical effects:

[0037] In use, the takeoff and landing module is fixedly installed on ground facilities. The top and bottom of the spacecraft are connected to the electromagnetic catapult track via a tractor. Through the detachable cooperation of the vehicle-mounted locking device and the airborne traction device, the electromagnetic catapult track pushes the tractor to bring the spacecraft to takeoff speed during takeoff. During landing or emergency landing, the electromagnetic catapult track is closed, and the spacecraft is connected to the vehicle-mounted locking device via the airborne traction device. The tractor's own braking system can be used to decelerate the spacecraft for landing or emergency landing. No landing gear is needed during takeoff and landing, avoiding the problem of insufficient load-bearing capacity caused by the landing gear not being able to deploy or the excessive weight of the airframe after deployment. Also, no fuel needs to be released, improving safety during landing and emergency landing. Attached Figure Description

[0038] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0039] Figures 1 to 4 This is a schematic diagram of the takeoff phase of the aerospace vehicle of the present invention;

[0040] Figure 5 This is a schematic diagram of the acceleration of the aerospace vehicle and tractor of the present invention;

[0041] Figure 6 This is a schematic diagram of the airborne traction device of the present invention;

[0042] Figures 7 to 8 This is a schematic diagram of the operation of the tractor unit of the present invention;

[0043] Figure 9 This is a schematic diagram of the vehicle-mounted towing hook module structure of the present invention;

[0044] Figures 10 to 12 This is a schematic diagram of the vehicle-mounted buffer module of the present invention during takeoff;

[0045] Figures 13 to 14 This is a schematic diagram of the vehicle-mounted buffer module of the present invention during landing;

[0046] Figures 15 to 17 This is a schematic diagram of the vehicle-mounted locking device of the present invention;

[0047] Figures 18 to 20 This is a schematic diagram of the landing phase of the aerospace vehicle of the present invention;

[0048] Figure 21 This is a schematic diagram illustrating an emergency landing in the event of power loss according to the present invention;

[0049] Figure 22 This is a schematic diagram of the track end buffer of the present invention;

[0050] Among them, 1. Spacecraft; 2. Airborne traction device; 3. Base; 4. Actuating rod; 5. Rotating shaft; 6. Traction vehicle; 7. Vehicle body; 8. Guide wheel; 9. Vehicle-mounted locking device; 10. Locking door panel; 11. Locking door; 12. First-stage rotating shaft; 13. First-stage robotic arm; 14. Second-stage rotating shaft; 15. Second-stage robotic arm; 16. Third-stage rotating shaft; 17. Electric actuator; 19. Vehicle-mounted traction hook base; 20. Traction hook rotation. 21. Shaft; 22. Towing hook; 23. Onboard buffer module; 24. High-pressure air source; 25. High-pressure air chamber housing; 26. Air chamber pressure relief valve; 27. Liquid buffer housing; 28. Oil release hole; 29. ​​Piston rod; 30. Launch bay; 31. Electromagnetic catapult track; 32. Buffer; 33. Piston; 34. Pressure relief valve; 35. Rebound valve; 36. Buffer housing; 37. High ground; 38. Viaduct; 39. Connecting slider. Detailed Implementation

[0051] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0052] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0053] Reference Figures 1 to 22 This invention discloses an auxiliary take-off and landing module for emergency landing of aerospace vehicles, comprising:

[0054] The takeoff and landing module 29 is fixedly installed on ground facilities;

[0055] Two electromagnetic catapult tracks 30 are provided. The two electromagnetic catapult tracks 30 are respectively fixed to the inner side of the top of the take-off and landing cabin 29 and the inner side of the bottom of the take-off and landing cabin 29. A tractor 6 is connected to the electromagnetic catapult track 30. The tractor 6 is detachably connected to the on-board tractor 2 through the vehicle-mounted locking device 9.

[0056] Two airborne traction devices 2 are respectively installed on the aerospace vehicle 1. One airborne traction device 2 is located on the top of the aerospace vehicle 1 and at the front end in the direction of travel, and the other airborne traction device 2 is located at the bottom of the aerospace vehicle 1 and at the rear end in the direction of travel.

[0057] In use, the takeoff and landing module 29 is fixedly installed on the ground facilities. The top and bottom of the spacecraft 1 are connected to the electromagnetic catapult track 30 via the towing vehicle 6. Through the detachable cooperation of the vehicle-mounted locking device 9 and the airborne towing device 2, the electromagnetic catapult track 30 pushes the towing vehicle 6 to bring the spacecraft 1 to takeoff speed during takeoff. During landing or emergency landing, the electromagnetic catapult track 30 is closed. After the spacecraft 1 is connected to the vehicle-mounted locking device 9 via the airborne towing device 2, the braking system of the towing vehicle 6 can be used to decelerate and land or make an emergency landing. No landing gear is needed during takeoff and landing, avoiding the problem of insufficient load-bearing capacity caused by the landing gear not being able to deploy or the excessive weight of the airframe after deployment. Also, no fuel needs to be released, improving safety during landing and emergency landing.

[0058] As an alternative implementation, the ground facility is either a raised ground 36 or an elevated bridge 37.

[0059] As an optional implementation, buffers 31 are fixed to both ends of the electromagnetic catapult track 30.

[0060] As an optional implementation, the airborne traction device 2 includes a base 3, which is fixedly connected to the aerospace vehicle 1. One end of the actuating rod 4 is rotatably connected to the base 3 via a rotating shaft 5. The other end of the actuating rod 4 is detachably connected to the traction vehicle 6 via a vehicle-mounted locking device 9. The rotating shaft 5 is the shaft of the motor, and the fixed end of the motor is fixedly connected inside the base 3.

[0061] Two airborne traction devices 2 are provided. The airborne traction device 2 includes a base 3, an actuating rod 4 and a rotating shaft 5.

[0062] One of the bases is fixedly connected to the top of the fuselage of the aerospace vehicle 1 at its lower end;

[0063] The lower end of the other base is fixedly connected to the belly of the aerospace vehicle 1;

[0064] Rotating shaft 5 is the rotating shaft of the motor built into the base 3;

[0065] The lower part of the actuator 4 is provided with a hole and is fixedly connected to the rotating shaft 5, so that they rotate synchronously.

[0066] As an optional implementation, the tractor unit 6 includes:

[0067] The vehicle body 7 is slidably connected to the electromagnetic catapult track 30 via guide wheels 8;

[0068] The vehicle-mounted tow hook module has one end for hooking to the end of the actuator 4 away from the base 3, and the other end of the vehicle-mounted tow hook module is installed on the vehicle body 7.

[0069] The vehicle-mounted locking device 9 is installed on the vehicle-mounted tow hook module. The vehicle-mounted locking device 9 is used to control the vehicle-mounted tow hook module to fix or release the actuator 4.

[0070] The vehicle-mounted buffer module 22 is mounted on the vehicle body 7 at one end, and the other end of the vehicle-mounted buffer module 22 is connected to the vehicle-mounted towing hook module via a transmission.

[0071] The tractor unit 6 includes a vehicle body 7, guide wheels 8, on-board towing hook module, on-board locking device 9, and on-board buffer module 22;

[0072] The guide wheel 8 is fixedly connected to the vehicle body 7 by a connecting rod and can maintain the smooth rotation of the wheel.

[0073] As an optional implementation, the vehicle-mounted towing hook module includes:

[0074] The vehicle-mounted towing hook base 19 is fixed to the vehicle body 7;

[0075] The towing hook 21 has one end rotatably connected to the vehicle towing hook base 19 via the towing hook shaft 20. A connecting slider 38 is slidably provided in the middle of the towing hook 21. The connecting slider 38 is connected to the vehicle buffer module 22 in a transmission manner. The other end of the towing hook 21 is provided with a hook groove that hooks to the end of the actuating rod 4 away from the base 3.

[0076] The vehicle-mounted tow hook module includes a vehicle-mounted tow hook base 19, a tow hook shaft 20, a tow hook 21, and a connecting slider 38;

[0077] The vehicle-mounted tow hook base 19 is fixedly connected to the vehicle body 7;

[0078] The towing hook shaft 20 is fixedly connected to the through hole of the vehicle towing hook base 19;

[0079] The lower through hole of the traction hook 21 is coaxially connected to the traction hook shaft 20;

[0080] The connecting slider 38 is coaxial with the traction hook 21 and can move up and down.

[0081] As an optional implementation, the vehicle-mounted locking device 9 includes:

[0082] Lock the door panel 10 and fix it to the towing hook 21;

[0083] Locking door 11 is slidably disposed on one side of locking door panel 10. Locking door 11 is used to control the opening and closing of hook groove.

[0084] The drive unit is connected at one end to the locking door panel 10 and at the other end to the locking door 11. The drive unit is used to drive the locking door 11 to slide along the locking door panel 10.

[0085] As an optional implementation, the drive unit includes:

[0086] One end of the first-level robotic arm 13 is rotatably connected to the locking door panel 10 via a first-level rotating shaft 12. The other end of the first-level robotic arm 13 is hinged to one end of the second-level robotic arm 15 via a second-level rotating shaft 14. The other end of the second-level robotic arm 15 is hinged to the locking door 11 via a third-level rotating shaft 16.

[0087] The locking door 11 is limited by the movable end of the electric actuator 17, and the fixed end of the electric actuator 17 is fixedly connected to the locking door plate 10.

[0088] The vehicle-mounted locking device 9 includes a locking door panel 10, a locking door 11, a primary rotating shaft 12, a primary robotic arm 13, a secondary rotating shaft 14, a secondary robotic arm 15, a tertiary rotating shaft 16, and an electric actuator 17.

[0089] The locking door panel 10 has a built-in motor controlled by a speed sensor, and the motor shaft is the primary shaft 12;

[0090] The primary rotating shaft 12 is fixedly connected to the primary robotic arm 13 and rotates synchronously.

[0091] The primary robotic arm 13 is coaxially connected to the secondary rotating shaft 14;

[0092] The secondary rotating shaft 14 is coaxially connected to the secondary robotic arm 15;

[0093] The secondary robotic arm 15 is coaxially connected to the tertiary rotating shaft 16;

[0094] The locking door panel 10 is fixedly connected to the traction hook 21;

[0095] The electric actuator 17 is fixedly connected to the locking door panel 10;

[0096] The movable end of the electric actuator 17 is engaged with the locking door 11 for limiting.

[0097] As an optional implementation, the on-board buffer module 22 includes:

[0098] Piston rod 28, one end of which is rotatably connected to connecting slider 38;

[0099] The high-pressure air chamber shell 24 is fixedly connected to the vehicle body 7. The air inlet end of the high-pressure air chamber shell 24 is connected to a high-pressure air source 23, which is fixedly connected inside the vehicle body 7.

[0100] The liquid buffer housing 26 is slidably disposed inside the high-pressure gas chamber housing 24. The liquid buffer housing 26 is fixedly connected to the gas chamber pressure relief valve 25. One end of the gas chamber pressure relief valve 25 is connected to the inner cavity of the high-pressure gas chamber housing 24, and the other end of the gas chamber pressure relief valve 25 is connected to the outside.

[0101] The other end of the piston rod 28 is slidably disposed in the oil cavity opened inside the liquid buffer housing 26, and a number of oil release holes 27 are opened at the end of the piston rod 28 away from the connecting slider 38.

[0102] The vehicle-mounted buffer module 22 includes a high-pressure air source 23, a high-pressure air chamber housing 24, an air chamber pressure relief valve 25, a liquid buffer housing 26, an oil release hole 27, and a piston rod 28.

[0103] The piston rod 28 has a through hole at the top, which is coaxially connected to the rotating shaft provided on the connecting slider 38;

[0104] The high-pressure air source 23 is fixedly connected inside the vehicle body 7;

[0105] The high-pressure air chamber outer shell 24 is fixedly connected to the vehicle body 7;

[0106] The bottom of the high-pressure air chamber shell 24 is provided with a hole and is connected to the high-pressure air source 23;

[0107] A pressure relief valve 25 for the air chamber is provided at the bottom of the liquid buffer housing 26;

[0108] The liquid buffer housing 26 is installed inside the high-pressure gas chamber housing 24;

[0109] A large gap exists at the mating point between the liquid buffer housing 26 and the inner side of the high-pressure gas chamber housing 24 to ensure that the gas can be discharged smoothly.

[0110] The bottom radius of the liquid buffer housing 26 is consistent with and matches the inner diameter of the high-pressure gas chamber housing 24, ensuring that a sealed gas chamber can be formed when the gas chamber pressure relief valve 25 is closed.

[0111] As an optional implementation, buffer 31 includes:

[0112] The buffer housing 35 has one end of a piston 32 slidably connected inside the buffer housing 35, and the other end of the piston 32 is used to contact the corresponding tractor 6.

[0113] A spring is disposed inside the buffer housing 35. One end of the spring is fixedly connected to one end of the piston 32, and the other end of the spring is fixedly connected to the inner wall of the buffer housing 35.

[0114] The piston 32 is located in the pressure relief chamber and the rebound valve 34 at one end inside the buffer housing 35, and the pressure relief valve 33 is provided at the inlet end of the pressure relief chamber.

[0115] There are 29 takeoff and landing cabins in total, one built on a high ground and the other erected on a flat ground in the form of an elevated structure;

[0116] The launch and landing module 29 includes an electromagnetic catapult track 30 and a buffer 31;

[0117] There are two electromagnetic catapult tracks 30, one above the other, including the tracks and the electromagnetic catapult, with the electromagnetic catapult installed beside the tracks.

[0118] The buffer 31 is installed at the end of the track and includes a piston 32, a pressure relief valve 33, a rebound valve 34, a spring, and a buffer housing 35.

[0119] This invention also discloses an auxiliary takeoff and landing system for aerospace transport aircraft based on a safe altitude and its working principle, including the following processes:

[0120] The auxiliary landing module 29 is built on a platform with a certain height, while the emergency landing module for power loss is built on a separate elevated platform with a lower height to facilitate a safe landing.

[0121] During takeoff, the spacecraft 1 is accelerated by two sets of tractors 6 on the electromagnetic catapult track 30. The tractors 6 are connected to the actuation rod 4 of the spacecraft 1 via an onboard locking device 9 on their tow hooks 21, locking and accelerating the spacecraft 1. The onboard buffer module 22 inside the tractor 6 is connected to the tow hook 21 via the top of the piston rod 28, while the high-pressure air source 23 continuously supplies air to the high-pressure chamber inside the high-pressure chamber shell 24 to provide necessary support and control the pitch angle of the spacecraft 1. When the spacecraft 1 reaches the predetermined level flight speed, the onboard locking device 9 on the tow hook 21 automatically unlocks, and the spacecraft 1 then propels itself using its own engines. At this time, the tractors 6 automatically decelerate on the electromagnetic catapult track 30 and, after contacting the buffer 31 at the end of the electromagnetic catapult track 30, bounce and slide to the designated position controlled by the limit switch to stop.

[0122] During the landing phase, the electromagnetic catapult track 30 will cease operation, and the flight control system will precisely control the spacecraft 1 within a specific level flight altitude, ensuring that the onboard actuation sticks 4 of the spacecraft 1 can be accurately hooked by the towing hook 21 of the towing vehicle 6 within the auxiliary landing bay 29, thereby connecting the spacecraft 1 to the towing vehicle 6. The towing vehicle 6 will then begin to decelerate using its own braking system, and control the pitch angle of the spacecraft 1 during deceleration by adjusting the depressurization of the high-pressure chamber within the high-pressure chamber shell 24 and setting the damping coefficient. Furthermore, the spacecraft 1 can also utilize its own wing surfaces for deceleration to improve overall deceleration efficiency.

[0123] When the spacecraft 1 needs to make an emergency landing after losing power, the flight control system controls the spacecraft 1 to glide to a set altitude and maintain a speed sufficient for level flight at that altitude, and then aligns it with the emergency landing capsule 29 built on the elevated platform for landing. Two sets of towing vehicles 6 are prepared in advance, positioned near the hatch of the emergency landing capsule 29 and maintaining a consistent distance from the actuation stick 4 of the spacecraft 1. Other landing procedures are the same as in the case where power has not been lost.

[0124] The present invention has the following technical effects:

[0125] 1. Compared with traditional aerospace vehicle take-off and landing schemes, this invention avoids excessive reliance on landing gear design standards. The auxiliary take-off and landing cabin in this invention can support the take-off and landing processes simultaneously, significantly improving take-off and landing efficiency and optimizing the overall operation process.

[0126] 2. Compared with traditional aerospace vehicle take-off and landing schemes, the auxiliary take-off and landing module of this invention has both auxiliary take-off and auxiliary landing capabilities, resulting in higher efficiency;

[0127] 3. Compared to the takeoff and landing scheme of aerospace vehicles equipped with landing gear, this invention provides higher safety, considering emergency landing situations in case of power loss, and ensures safe landing in emergency situations. The two towing vehicles 6 are located at the front and rear ends of the aerospace vehicle 1, respectively. Through the coordinated action of the vehicle-mounted towing device, the airborne towing device 2, and the vehicle-mounted locking device 9, the vehicle is secured in its initial position.

[0128] Let's take one application example as an illustration:

[0129] Once the electromagnetic catapult track 30 is activated, the tractor 6 accelerates forward, simultaneously towing the spacecraft 1 through a corresponding acceleration process. The high-pressure air source 23 inside the tractor 6 continuously supplies air to the high-pressure air chamber of the onboard buffer module 22 to ensure that the onboard and airborne towing devices 2 provide necessary support to the spacecraft 1 and prevent it from pitching up during acceleration. When the spacecraft 1 reaches the preset level flight speed, the locking door 11, fixedly connected to the onboard and airborne towing devices 2, opens, and the tractor 6 begins braking, causing the airborne towing device 2 to separate from the onboard locking device 9, completing the unlocking process. The spacecraft then continues its level flight away from the takeoff and landing cabin 29, marking the successful completion of the takeoff process.

[0130] The actuating lever 4 in the airborne traction device 2 can be retracted under the control of the rotating shaft 5, thereby reducing the aerodynamic drag of the spacecraft 1 in level flight. Subsequently, the traction vehicle 6 decelerates and contacts the buffer 31 located at the end of the electromagnetic catapult track 30, then rebounds and slides under the control of the in-vehicle control system to a predetermined position controlled by the limit switch for final braking, awaiting the return of the spacecraft 1 and its landing mission. The high-pressure air source 23 in the traction vehicle 6 stops supplying air to the high-pressure air chamber of the on-board buffer module 22 and opens the air chamber pressure relief valve 25, making the high-pressure air chamber a compressible buffer air chamber.

[0131] The vehicle-mounted buffer module 22 supports the vehicle-mounted towing device and the airborne towing device 2 during takeoff, and performs a cushioning function during landing. During takeoff, the high-pressure air source 23 installed inside the vehicle continuously sprays air into the cavity between the high-pressure air chamber shell 24 and the bottom of the liquid buffer shell 26.

[0132] Furthermore, the bottom of the liquid buffer housing 26 is designed with an umbrella-shaped structure, the outer diameter of which matches the high-pressure air chamber housing 24, allowing it to act as a piston within the cavity. During this process, the air chamber relief valve 25 on the liquid buffer housing 26 remains closed, causing the cavity to form a high-pressure air chamber, and the gas pressure pushes the liquid buffer housing 26 to its highest point. The oil release hole 27 on the piston rod 28 is equipped with a valve. During the takeoff phase, the valve of the oil release hole 27 remains closed, allowing the components of the vehicle-mounted buffer module to remain in an outward expansion state, and transmitting the supporting force to the tow hook 21 through the connection between the connecting slider 38 and the piston rod 28.

[0133] The vehicle-mounted tow hook base 19 is designed to allow the tow hook 21 to rotate only within the range of 0-90 degrees. Therefore, when the connecting slider 38 transmits pressure to the tow hook 21, the tow hook 21 will maintain a 90-degree attitude, while bearing the drag of the aerospace vehicle brought by the actuator 4, and maintaining the pitch angle of the aerospace vehicle 1 to prevent it from pitching up and disrupting its level flight state. During the landing phase, the valves of the air chamber pressure relief valve 25 and the oil release hole 27 are opened in advance. When the tow hook 21 bears the landing pressure, the liquid in the liquid buffer is squeezed by the piston rod 28 and flows rapidly through the oil release hole 27, while the gas in the high-pressure air chamber flows rapidly through the air hole, producing a damping effect. The vehicle-mounted buffer module 22 is designed with an appropriate damping coefficient, so that the tow hook 21 can only be squeezed and rotated to a predetermined angle, thereby maintaining the pitch angle of the aerospace vehicle 1 within a suitable range and ensuring the smoothness and safety of the landing process.

[0134] During takeoff, a pair of precise positioning holes are designed below the locking door 11. The pins inside the two electric actuators 17 remain extended and inserted into the holes. The locking door plate 10 has a specially designed door groove to realize the locking mechanism of the locking door 11. When the aerospace vehicle 1 reaches the preset release speed, the speed sensor triggers a control signal, instructing the pins inside the electric actuators 17 to retract. The locking door plate 10 is embedded with a motor, and the motor shaft is the primary rotating shaft 12. As the primary rotating shaft 12 rotates, the locking door 11 is raised through the sequential transmission of the primary robotic arm 13, the secondary rotating shaft 14, the secondary robotic arm 15, and the tertiary rotating shaft 16, completing the unlocking action. During landing, the pressure sensor senses the squeezing force of the airborne traction device 2 on the towing hook 21 and controls the primary rotating shaft 12 to reverse. Similarly, through the coordinated action of the primary robotic arm 13, the secondary rotating shaft 14, the secondary robotic arm 15, and the tertiary rotating shaft 16, the locking door 11 is released until it contacts the lower edge of the door groove. Subsequently, the pressure sensor inside the lower edge of the door slot receives the contact signal, controls the electric actuator 17 to release the latch, completes the locking process of the locking door 11, and ensures the safety and stability of the entire landing mechanism.

[0135] During the landing phase, the control system precisely regulates the descent of the spacecraft 1 to the predetermined altitude and accurately aligns it with the landing position of the takeoff and landing module, while maintaining level flight and releasing the actuator stick 4 to the vertical position. When the actuator stick 4 in the airborne towing device 2 is successfully intercepted by the tow hook 21, the pressure sensor triggers the vehicle-mounted locking device 9 to lock. This action effectively transfers the kinetic energy of the spacecraft to the towing vehicle 6, which then pulls the spacecraft forward. The towing vehicle 6 uses its built-in braking system to decelerate, causing the spacecraft 1 to tend to pitch up. To control this tendency, the damping coefficient of the vehicle-mounted buffer system limits the rotation angle of the tow hook 21 under the action of the spacecraft 1's kinetic energy to a preset safe range, thereby ensuring that the pitch angle of the spacecraft 1 remains within a reasonable range. At the same time, the spacecraft 1 can also use its own wing surfaces for aerodynamic deceleration to improve overall deceleration efficiency. This process not only improves landing safety but also optimizes the smoothness of the landing operation. When an aircraft needs to make an emergency landing after losing power, the flight control system guides the aircraft to glide to a set altitude with a speed sufficient for level flight at that altitude, and then aligns it with the emergency landing capsule, which is built on the elevated platform 37 at a lower altitude, for landing. Two sets of towing vehicles are prepared in advance at the position near the hatch of the emergency landing capsule, maintaining the same distance from the aerospace vehicle's actuator stick. Other landing procedures are the same as in the case where power has not been lost.

[0136] The buffer 31 consists of key components such as the piston 32, pressure relief valve 33, rebound valve 34, and buffer housing 35, forming a high-precision damping system. The bottom of the buffer 31 is rigidly connected to the track surface, ensuring the high stability of the entire system. When the piston 32 contacts the tractor 6, it forms the power transmission path of the system. The pressure relief valve 33 is equipped with a precision-controlled valve located at the convergence point of the oil holes inside the piston 32. Its function is to activate when the internal pressure reaches a preset threshold, rapidly opening the oil holes to release high-pressure oil. The rebound valve 34 is also equipped with a control valve, remaining closed when the system is not under pressure. The space between the piston 32 and the buffer housing 35 is filled with special oil, forming a sealed hydraulic environment. When the tractor 6 impacts the piston 32, the piston 32 is compressed, triggering the pressure relief valve 33 to open, achieving rapid oil release. As the oil is further compressed, the rebound valve 34 opens due to increased pressure, while the pressure relief valve 33 closes, allowing the piston rod to rebound. The compression and flow of the oil effectively converts kinetic energy into heat energy or other forms of energy, achieving a damping effect. This energy conversion not only effectively slows down the movement speed of the tractor 6, but also gives the tractor a rebound effect, allowing it to move to the predetermined position and prepare for the next stage of operation.

[0137] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0138] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. An auxiliary takeoff and landing module for emergency landing of aerospace vehicles, characterized in that, include: The takeoff and landing cabin (29) is fixedly installed on the ground facilities; Two electromagnetic catapult tracks (30) are provided. The two electromagnetic catapult tracks (30) are respectively fixed to the inner side of the top of the take-off and landing cabin (29) and the inner side of the bottom of the take-off and landing cabin (29). A tractor (6) is connected to the electromagnetic catapult track (30) through transmission. The tractor (6) is detachably connected to the airborne traction device (2) through the vehicle-mounted locking device (9). Two airborne traction devices (2) are respectively installed on the aerospace vehicle (1), one of the airborne traction devices (2) is located on the top of the aerospace vehicle (1) and at the front end in the direction of travel, and the other airborne traction device (2) is located at the bottom of the aerospace vehicle (1) and at the rear end in the direction of travel.

2. The auxiliary take-off and landing module for emergency landing of aerospace vehicles according to claim 1, characterized in that: The ground facility is either a high ground (36) or an elevated bridge (37).

3. The auxiliary take-off and landing module for emergency landing of aerospace vehicles according to claim 1, characterized in that: Buffers (31) are fixed at both ends of the electromagnetic catapult track (30).

4. The auxiliary take-off and landing module for emergency landing of aerospace vehicles according to claim 1, characterized in that: The airborne traction device (2) includes a base (3), which is fixedly connected to the aerospace vehicle (1). One end of the actuating rod (4) is rotatably connected to the base (3) via a rotating shaft (5). The other end of the actuating rod (4) is detachably connected to the traction vehicle (6) via the vehicle-mounted locking device (9). The rotating shaft (5) is the rotating shaft of the motor, and the fixed end of the motor is fixedly connected to the base (3).

5. An auxiliary takeoff and landing module for emergency landing of aerospace vehicles according to claim 4, characterized in that, The tractor (6) includes: The vehicle body (7) is slidably connected to the electromagnetic catapult track (30) via guide wheels (8); The vehicle-mounted towing hook module has one end for hooking to the end of the actuating rod (4) away from the base (3), and the other end of the vehicle-mounted towing hook module is installed on the vehicle body (7); The vehicle-mounted locking device (9) is installed on the vehicle-mounted tow hook module. The vehicle-mounted locking device (9) is used to control the vehicle-mounted tow hook module to fix or release the actuating rod (4). The vehicle-mounted buffer module (22) is mounted on the vehicle body (7) at one end, and the other end of the vehicle-mounted buffer module (22) is connected to the vehicle-mounted towing hook module via transmission.

6. An auxiliary take-off and landing module for emergency landing of aerospace vehicles according to claim 5, characterized in that, The vehicle-mounted towing hook module includes: The vehicle-mounted towing hook base (19) is fixed to the vehicle body (7); The towing hook (21) has one end rotatably connected to the vehicle towing hook base (19) via a towing hook shaft (20). A connecting slider (38) is slidably provided in the middle of the towing hook (21). The connecting slider (38) is connected to the vehicle buffer module (22) in a transmission manner. The other end of the towing hook (21) is provided with a hook groove that hooks to the end of the actuating rod (4) away from the base (3).

7. An auxiliary takeoff and landing module for emergency landing of aerospace vehicles according to claim 6, characterized in that, The vehicle-mounted locking device (9) includes: Lock the door panel (10) and fix it to the traction hook (21); A locking door (11) is slidably disposed on one side of the locking door panel (10), and the locking door (11) is used to control the opening and closing of the hook groove; The drive unit has one end connected to the locking door panel (10) and the other end connected to the locking door (11). The drive unit is used to drive the locking door (11) to slide along the locking door panel (10).

8. An auxiliary take-off and landing module for emergency landing of aerospace vehicles according to claim 7, characterized in that, The drive unit includes: A first-level robotic arm (13) is rotatably connected to the locking door panel (10) at one end via a first-level rotating shaft (12). The other end of the first-level robotic arm (13) is hinged to one end of a second-level robotic arm (15) via a second-level rotating shaft (14). The other end of the second-level robotic arm (15) is hinged to the locking door (11) via a third-level rotating shaft (16). The locking door (11) is limited by the movable end of the electric actuator (17), and the fixed end of the electric actuator (17) is fixed to the locking door plate (10).

9. An auxiliary takeoff and landing module for emergency landing of aerospace vehicles according to claim 6, characterized in that, The vehicle-mounted buffer module (22) includes: A piston rod (28), one end of which is rotatably connected to the connecting slider (38); The high-pressure air chamber shell (24) is fixedly connected to the vehicle body (7), and the air inlet end of the high-pressure air chamber shell (24) is connected to a high-pressure air source (23), which is fixedly connected inside the vehicle body (7). The liquid buffer housing (26) is slidably disposed inside the high-pressure gas chamber housing (24). The liquid buffer housing (26) is fixedly connected to a gas chamber pressure relief valve (25). One end of the gas chamber pressure relief valve (25) is connected to the inner cavity of the high-pressure gas chamber housing (24), and the other end of the gas chamber pressure relief valve (25) is connected to the outside. The other end of the piston rod (28) is slidably disposed in the oil chamber opened inside the liquid buffer housing (26), and a plurality of oil release holes (27) are opened at the end of the piston rod (28) away from the connecting slider (38).

10. An auxiliary take-off and landing module for emergency landing of aerospace vehicles according to claim 3, characterized in that, The buffer (31) includes: A buffer housing (35) has one end of a piston (32) slidably connected inside the buffer housing (35), and the other end of the piston (32) is used to contact the corresponding tractor (6); A spring is disposed inside the buffer housing (35), one end of the spring is fixedly connected to one end of the piston (32), and the other end of the spring is fixedly connected to the inner wall of the buffer housing (35). The piston (32) is located in the pressure relief chamber and rebound valve (34) inside the buffer housing (35), and the pressure relief chamber is provided with a pressure relief valve (33) at its inlet end.

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