An aircraft launch system

Abstract

The present application relates to a kind of aircraft launching system, including ground base frame and the launching platform unit and swing bar unit arranged on ground base frame, ground base frame is made of multiple frame monomers splicing, ground base frame is fixed on ground by pressing plate and pre-buried threaded column, launching platform unit includes platform body installed on ground base frame by multiple lifting legs, platform body is provided with flow guide hole, platform body is installed with multiple support arms corresponding with aircraft support point on the periphery of flow guide hole, the lower side of platform body is provided with flow guide device installed on ground base frame in the position corresponding with flow guide hole, swing bar unit includes rotating shaft installed on ground base frame by two bearing seats, rotating shaft is fixed with truss type swing bar, one end of rotating shaft is equipped with rotary drive device.It has the advantages of simple structure, easy to disassemble and assemble, good mobility, strong practicality.

Description

Technical Field

[0001] This invention relates to aircraft launch technology, and more specifically to a mobile and flexible aircraft launch system. Background Technology

[0002] In the aerospace field, traditional aircraft launch pads are typically installed in fixed positions, with supporting launch towers, flow channels, and other fixed facilities to facilitate the laying of propellant pipelines and power cables, as well as the channeling of gas flow. This fixed-position installation method limits the specific location of aircraft launches, resulting in poor mobility and flexibility. Summary of the Invention

[0003] The purpose of this invention is to provide an aircraft launch system that has the advantages of simple structure, convenient assembly and disassembly, good mobility, and strong practicality.

[0004] To address the aforementioned problems in the prior art, this invention provides an aircraft launch system, comprising a foundation frame and a launch pad unit and a swing arm unit mounted on the foundation frame. The foundation frame is constructed from multiple frame units and is fixed to the ground by pressure plates and pre-embedded threaded columns. The launch pad unit includes a platform mounted on the foundation frame via multiple lifting outriggers. The platform has a flow guide hole, and multiple support arms corresponding to aircraft support points are installed around the flow guide hole. A flow guide mounted on the foundation frame is located on the lower side of the platform at a position corresponding to the flow guide hole. The swing arm unit includes a rotating shaft mounted on the foundation frame via two bearing seats. A truss-type swing arm is fixed on the rotating shaft, and a rotation drive device is provided at one end of the rotating shaft.

[0005] Furthermore, the present invention provides an aircraft launch system, wherein the support arm includes a support arm body and an actuating cylinder. The lower end of the support arm body is hinged to a first support fixed on a platform via a first pin. The actuating cylinder includes a cylinder body, the lower end of which is hinged to a second support fixed on a platform via a second pin. A piston is provided in the cylinder body, and a piston rod extending from the upper end of the cylinder body is coaxially fixed to the piston. The piston rod is hinged to a third support fixed on the support arm body via a third pin. A rubber shock absorber is provided on the lower side of the piston in the cylinder body. The rubber shock absorber has a vent hole connected to an inflation / deflation channel. A return spring sleeved on the piston rod is provided in the cylinder body on the upper side of the piston.

[0006] Furthermore, in an aircraft launch system of the present invention, the rubber shock absorber includes a rubber body, and the outer wall of the rubber body is provided with annular grooves distributed vertically at intervals, the groove opening width being greater than the groove bottom width, and the rubber body is provided with support rings that are alternately distributed with the annular grooves in the vertical direction, the outer edge thickness of the support rings being less than the inner edge thickness.

[0007] Furthermore, in the present invention, an aircraft launch system is provided, wherein the piston rod is provided with a sleeve that slides with it, the outer wall of the sleeve is provided with a retaining ring, and two return springs are provided, the upper and lower ends of the upper return spring pressing against the cylinder and the retaining ring respectively, and the upper and lower ends of the lower return spring pressing against the retaining ring and the piston respectively.

[0008] Furthermore, in the present invention, an aircraft launch system is provided, wherein the lower half of the support arm is a through cavity structure, and a limiting baffle fixedly connected to the two side walls is provided in the cavity. The first support is provided with a limiting block that cooperates with the limiting baffle. After the support arm is erected into position, the limiting baffle and the limiting block abut against each other. The top of the support arm is provided with a support platform, and a support plate is fixed on the support platform by bolts. A tie rod pad for supporting the aircraft is rotatably mounted on the support plate through a threaded hole. The tie rod pad is provided with a light hole for installing a windproof tie rod.

[0009] Furthermore, the present invention provides an aircraft launch system, wherein the cylinder body includes a cylinder barrel and an upper cylinder cap and a lower cylinder cap screwed onto the upper and lower ends of the cylinder barrel respectively by threads. A sealing ring is provided between the lower cylinder cap and the cylinder barrel. The bottom of the lower cylinder cap is provided with a lower support lug that is hinged to a second support. The piston rod passes through the upper cylinder cap and the two slide together. The end of the piston rod is provided with an upper support lug that is hinged to a third support.

[0010] Furthermore, in an aircraft launch system of the present invention, the lower support lug is provided with a shaft hole for mounting a second pin, the inner wall of the shaft hole is provided with a first air passage communicating with a vent hole, the second pin is provided with an annular air groove along the circumference at a position corresponding to the first air passage, a sealing ring is installed on the second pin on both sides of the annular air groove through a sealing groove, and an inflation head is installed at one end of the second pin. The inflation head communicates with the annular air groove through the second air passage provided in the second pin. The inflation / deflation channel refers to a channel formed by the first air passage, the annular air groove, the second air passage and the inflation head being connected in sequence.

[0011] Furthermore, the present invention provides an aircraft launch system in which the lifting outriggers include a column and a worm gear lift fixedly connected together. The lower end of the column is connected to a ball joint fixed to a foundation frame via a ball joint. The worm gear lift is fixedly connected to a bracket mounted on a platform. The flow guide includes a roof-shaped flow guide body with flow guide baffles at both ends. The bottom of the flow guide body and the flow guide baffles are provided with mounting seats fixedly connected to the foundation frame.

[0012] Furthermore, the present invention provides an aircraft launch system in which a takeoff contact bracket is installed on the platform. The takeoff contact bracket includes a sleeve with its lower end fixed to the platform. A support rod is provided in the sleeve. A handle for locking the support rod is screwed onto the sleeve through a threaded hole. A support plate is fixed to the upper end of the support rod. An adjusting plate is fixed to the support plate by two screws. The screws are located in the elongated holes of the adjusting plate. A tray is fixed to the adjusting plate.

[0013] Furthermore, in an aircraft launch system of the present invention, the rotary drive device includes a gear coaxially fixed on a rotating shaft, a rack meshing with the lower side of the gear, the rack being hinged to a drive cylinder fixed on a foundation frame, and a roller mounted on the foundation frame on the lower side of the rack; a limit plate is also fixed on the rotating shaft, the limit plate having a forward rotation limit hole and a reverse rotation limit hole, the limit plate being located between two support plates fixed on the foundation frame, and a knob plunger cooperating with the forward rotation limit hole and the reverse rotation limit hole is installed on the support plate; the upper half of the swing arm is connected to two traction steel wire ropes, the lower ends of which are fixedly connected to the foundation frame.

[0014] Compared with existing technologies, the aircraft launch system of this invention has the following advantages: This invention establishes a foundation frame and launch platform units and swing arm units mounted on the foundation frame. The foundation frame is constructed from multiple frame units and fixed to the ground by pressure plates and pre-embedded threaded columns. The launch platform unit consists of a platform mounted on the foundation frame via multiple lifting legs. A flow guide hole is provided on the platform, and multiple support arms corresponding to the aircraft support points are installed on the platform and around the flow guide hole. A flow guide is installed on the foundation frame at a position on the lower side of the platform corresponding to the flow guide hole. The swing arm unit consists of a rotating shaft mounted on the foundation frame via two bearing seats. A truss-type swing arm is fixed on the rotating shaft, and a rotation drive device is provided at one end of the rotating shaft. This constitutes an aircraft launch system that is simple in structure, easy to assemble and disassemble, highly mobile, and practical. In practical applications, after placing the aircraft on the multiple support arms and laying the propellant loading pipeline and power supply cable on the swing arm, propellant loading, ignition, and other launch procedures can be performed. This invention improves the convenience of disassembly, assembly, and transportation by adopting a modular structure for the foundation frame, launch pad unit, and swing arm unit. It can be installed at non-fixed locations as needed, improving the maneuverability and flexibility of the aircraft launch. The foundation frame ensures the stability of the launch area, the lifting outriggers improve the convenience of adjusting the platform, the support arm improves the safety and reliability of supporting the aircraft, the guide holes and guide vanes facilitate the smooth flow of exhaust gas, and the pivot and swing arm improve the ease of laying refueling pipelines and power cables. The refueling pipelines and power cables are equipped with refueling connectors and cable plugs for docking with the aircraft. Before ignition and takeoff, the swing arm swings away from the aircraft to quickly detach the refueling connectors and cable plugs from the aircraft by pulling.

[0015] The following detailed description of an aircraft launch system according to the present invention, with reference to the accompanying drawings, illustrates a specific embodiment. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of an aircraft launch system according to the present invention;

[0017] Figure 2 This is a front view of a launch pad unit in an aircraft launch system according to the present invention;

[0018] Figure 3 This is a top view of a launch pad unit in an aircraft launch system according to the present invention;

[0019] Figure 4 This is a left view of a launch pad unit in an aircraft launch system according to the present invention;

[0020] Figure 5This is an isometric view of a launch pad unit in an aircraft launch system according to the present invention;

[0021] Figure 6 This is a front view of a support arm in an aircraft launch system according to the present invention;

[0022] Figure 7 This is a left view of a support arm in an aircraft launch system according to the present invention;

[0023] Figure 8 This is an isometric view of a support arm in an aircraft launch system according to the present invention;

[0024] Figure 9 for Figure 6 AA direction view;

[0025] Figure 10 for Figure 7 BB view in the middle;

[0026] Figure 11 This is a diagram showing the state of the support arm in the aircraft launch system of the present invention when it is tilted outwards;

[0027] Figure 12 This is a front view of the actuator cylinder in an aircraft launch system according to the present invention;

[0028] Figure 13 for Figure 12 CC view in the middle;

[0029] Figure 14 This is a cross-sectional view of a rubber shock absorber in an aircraft launch system according to the present invention;

[0030] Figure 15 This is a front view of the lifting legs in an aircraft launch system according to the present invention;

[0031] Figure 16 This is an isometric view of the lifting legs in an aircraft launch system according to the present invention;

[0032] Figure 17 This is a front view of a flow deflector in an aircraft launch system according to the present invention;

[0033] Figure 18 This is an isometric view of a guide vane in an aircraft launch system according to the present invention;

[0034] Figure 19 This is an isometric view of a takeoff contact bracket in an aircraft launch system according to the present invention;

[0035] Figure 20 This is a front view of a lever unit in an aircraft launch system according to the present invention;

[0036] Figure 21This is an isometric view of a pendulum unit in an aircraft launch system according to the present invention. Detailed Implementation

[0037] First, it should be noted that the directional terms such as up, down, left, right, front, and back used in this invention are merely descriptions based on the accompanying drawings for ease of understanding, and are not intended to limit the technical solution or the scope of protection claimed in this invention.

[0038] like Figures 1 to 21 The embodiment of an aircraft launch system of the present invention shown includes a foundation frame and a launch pad unit and a swing arm unit mounted on the foundation frame. The foundation frame is constructed from multiple frame units 1 assembled together for ease of assembly, disassembly, and transportation. The foundation frame is fixed to the ground by pressure plates and pre-embedded threaded posts. The launch pad unit is mounted on the foundation frame as a platform 3 via multiple lifting legs 2. A flow guide hole 31 is provided on the platform 3. Multiple support arms 4, corresponding to aircraft support points, are installed on the platform 3 around the flow guide hole 31. A flow guide 5 is mounted on the foundation frame at a position on the lower side of the platform 3 corresponding to the flow guide hole 31. The swing arm unit is mounted on the foundation frame as a rotating shaft 7 via two bearing seats 6. A truss-type swing arm 8 is fixed on the rotating shaft 7 for laying refueling pipelines and power cables. A rotation drive device is provided at one end of the rotating shaft 7 to drive the rotating shaft 7 to rotate, thereby causing the swing arm 8 to swing.

[0039] The above structural configuration constitutes a simple, easy-to-assemble, highly mobile, and practical aircraft launch system. In practical applications, after placing the aircraft on multiple support arms 4 and laying the propellant loading pipeline and power supply cable on the swing arm 8, the propellant loading, ignition, and launch procedures can be carried out. This invention improves the convenience of disassembly, assembly, and transportation by adopting a modular structure for the foundation frame, launch pad unit, and swing arm unit. It allows for installation at non-fixed locations as needed, enhancing the maneuverability of the aircraft launch. The foundation frame ensures the stability of the launch area and prevents ground erosion. The lifting outriggers 2 improve the convenience of adjusting the platform body 3. The support arm 4 enhances the safety and reliability of supporting the aircraft. The guide holes 31 and guide vanes 5 facilitate the smooth flow of exhaust gases. The rotating shaft 7 and swing arm 8 improve the ease of laying refueling pipelines and power cables. The refueling pipelines and power cables are equipped with refueling connectors and cable plugs for docking with the aircraft. Before ignition and takeoff, the swing arm 8 swings away from the aircraft, allowing the refueling connectors and cable plugs to be quickly detached from the aircraft through pulling. It should be noted that the structure of the refueling connectors and cable plugs and their connection method with the aircraft are well known to those skilled in the art and will not be described further here. In practical applications, the frame unit 1 is a steel frame to ensure structural strength and support stability. During the assembly of the foundation frame, adjacent frame units 1 are fixed together using double-ended bolts and matching nuts. After assembly, the foundation frame is fixed to the ground by setting pressure plates on the foundation frame and fixing the pressure plates to the pre-embedded threaded columns. The structure and connection method of the pressure plates and pre-embedded threaded columns are conventional technical means in this field.

[0040] As an optimization, this specific embodiment adopts the following structure for the support arm 4: a support arm body 41 and an actuating cylinder 42 are provided, and the lower end of the support arm body 41 is hinged to the first support 44 fixed on the platform 3 via a first pin 43; the actuating cylinder 42 is provided with a cylinder body 421, and the lower end of the cylinder body 421 is hinged to the second support 46 fixed on the platform 3 via a second pin 45; a piston 422 is provided in the cylinder body 421, and the piston 422 is coaxially fixedly extended out of the cylinder. The piston rod 423 at the upper end of the body 421 is hinged to the third support 48 fixed on the support arm body 41 via the third pin 47; a rubber shock absorber 424 is provided in the cylinder 421 and below the piston 422, and a vent hole 4241 is provided on the rubber shock absorber 424 to connect to the inflation / deflation channel; and a return spring 425 is provided in the cylinder 421 above the piston 422 and sleeved on the piston rod 423. This structure is designed so that when arranging the support arm 4, the actuator cylinder 42 is positioned on the side of the support arm 41 away from the aircraft, i.e., on the outer side centered on the aircraft. Before placing the aircraft, the actuator cylinder 42 is inflated through the inflation / deflation channel and the vent 4241 of the rubber shock absorber 424. This causes the piston rod 423 to extend and the support arm 41 to be erected by the piston 422 compressing the return spring 425. Then, the aircraft is placed on multiple support arms 41. Before ignition and launch, the actuator cylinder 42 is deflated through the inflation / deflation channel and the vent 4241 of the rubber shock absorber 424. When ignition and takeoff occur, the piston rod 423 will retract rapidly under the action of the return spring 425, causing the support arm 41 to tilt outward, i.e., tilt away from the aircraft. This avoids interference and collision between the aircraft and the support arm 41 due to lateral drift caused by wind, thus improving safety. This invention utilizes a rubber shock absorber 424 located below the piston 422 in the actuator cylinder 42. This provides a buffering function, preventing damage to the actuator cylinder 42 from impacts, and reduces rebound, ensuring the effectiveness and reliability of the outward tilting of the support arm 41. In practical applications, to ensure that the support arm 41 can still support the aircraft after the actuator cylinder 42 is deflated, this invention incorporates a through-cavity structure in the lower half of the support arm 41. A limiting baffle 411, fixedly connected to both side walls, is installed within this cavity. Simultaneously, a limiting block 441, cooperating with the limiting baffle 411, is installed on the first support 44. When the support arm 41 is upright, the limiting baffle 411 abuts against the limiting block 441. This arrangement, after the actuator cylinder 42 is deflated, ensures that the support arm 41 continues to provide stable support to the aircraft by blocking the limiting baffle 411 with the limiting block 441 and in conjunction with the aircraft's gravity. Meanwhile, in this specific embodiment, a support platform 412 is provided on the top of the support arm body 41, and a support plate 413 is fixed on the support platform 412 by bolts. A tie rod pad 49 for supporting the aircraft is installed on the support plate 413 through threaded holes, and a light hole 491 for installing the windproof tie rod is provided on the tie rod pad 49.The support platform 412 ensures the stability of the support, the support plate 413 keeps the support arm 41 as far away from the aircraft as possible, the tie rod pad 49 reduces the contact area with the aircraft and allows for height adjustment by rotation, and the windproof tie rod is installed and fixed to the aircraft through the light hole 491, which can effectively prevent the aircraft from overturning due to wind. It should be noted that the windproof tie rod is a threaded rod, and the windproof tie rod between the aircraft and the tie rod pad 49 should be removed before ignition and firing; to ensure that the support arm 41 can be smoothly tilted outward, the first pin 43, the second pin 45 and the third pin 47 should be parallel to each other.

[0041] In a specific embodiment, the present invention employs the following structure for the rubber shock absorber 424: a rubber body 4242 is provided, and annular grooves 4243 are provided on the outer wall of the rubber body 4242 at vertical intervals, with the opening width of the annular grooves 4243 being greater than the bottom width; simultaneously, a support ring 4244 is provided within the rubber body 4242, with the support ring 4244 and the annular grooves 4243 alternating in the vertical direction, and the outer edge thickness of the support ring 4244 being less than the inner edge thickness. This structure improves the buffering performance of the rubber shock absorber 424 through the annular grooves 4243, improves the strength of the rubber shock absorber 424 through the support rings 4244, and enhances the buffering effect of the rubber shock absorber 424 through the alternating cooperation of the annular grooves 4243 and the support rings 4244, reducing the rebound force of the rubber shock absorber 424, further ensuring the effectiveness of the outward tilt of the support arm 41, and enhancing safety and reliability. In a specific embodiment, the present invention provides a sleeve 4231 that slides on the piston rod 423, a retaining ring 4232 on the outer wall of the sleeve 4231, and two return springs 425. The upper and lower ends of the upper return spring 425 press against the cylinder 421 and the retaining ring 4232 respectively, while the upper and lower ends of the lower return spring 425 press against the retaining ring 4232 and the piston 422 respectively. Compared with a single spring structure, this structure not only reduces the manufacturing difficulty and improves the reset capability and action sensitivity, but also allows the two return springs 425 to act synchronously through the sliding of the sleeve 4231, thus improving adaptability.

[0042] In a specific embodiment, the present invention employs a split structure for the cylinder 421 as follows: it includes a cylinder 4211 and an upper cap 4212 and a lower cap 4213 screwed onto the upper and lower ends of the cylinder 4211 respectively. A sealing ring is provided between the lower cap 4213 and the cylinder 4211. A lower lug 4214, hinged to a second support 46, is provided at the bottom of the lower cap 4213, allowing the piston rod 423 to pass through the upper cap 4212 and slide together. An upper lug 4233, hinged to a third support 48, is provided at the end of the piston rod 423. This configuration of the cylinder 421 features a simple structure and convenient disassembly and maintenance. In a specific embodiment, the present invention provides a shaft hole 4215 for mounting a second pin 45 on the lower support lug 4214. A first air passage 4216 communicating with a vent hole 4241 is provided on the inner wall of the shaft hole 4215. An annular air groove 451 is provided circumferentially on the second pin 45 at a position corresponding to the first air passage 4216. Sealing rings are installed on the second pins 45 on both sides of the annular air groove 451 via sealing grooves 452. An inflation head 453 is installed at one end of the second pin 45, and the inflation head 453 communicates with the annular air groove 451 through a second air passage 454 provided in the second pin 45. The inflation / deflation channel refers to a channel formed by the sequential connection of the first air passage 4216, the annular air groove 451, the second air passage 454, and the inflation head 453. This configuration allows for inflation / deflation of the actuator 42 by connecting an inflation pipe and an air source to the inflation head 453, enabling remote control operation and ensuring personnel safety.

[0043] In a specific embodiment, the present invention employs the following structure for the lifting outrigger 2: a column 21 and a worm gear lift 22 are fixedly connected to each other; the lower end of the column 21 is connected to a ball joint 23 fixed on the foundation frame via a ball joint; and the worm gear lift 22 is fixedly connected to a transfer frame 32 mounted on the platform 3. This configuration of the lifting outrigger 2 features a simple structure, convenient operation, and strong adaptability. In another specific embodiment, the present invention provides a roof-shaped flow guide body 51 for the flow guide 5, with flow guide baffles 52 at both ends of the flow guide body 51, and mounting seats 53 fixedly connected to the foundation frame at the bottom of the flow guide body 51 and the flow guide baffles 52. This configuration of the flow guide 5 allows the gas flow to quickly flow to both sides through the two arc-shaped inclined surfaces of the flow guide body 51, featuring a simple structure, convenient assembly and disassembly, and good flow guiding efficiency. For ease of detection and control, this specific embodiment also includes a takeoff contact bracket 9 installed on the platform 3. The structure of the takeoff contact bracket 9 is as follows: it includes a sleeve 91 with its lower end fixed to the platform 3; a support rod 92 is provided in the sleeve 91; a handle 911 for locking the support rod 92 is screwed onto the sleeve 91 through a threaded hole; a support plate 93 is fixed to the upper end of the support rod 92; an adjusting plate 94 is fixed to the support plate 93 by two screws, with the screws located in the elongated holes 941 of the adjusting plate 94; and a tray 95 is fixed to the adjusting plate 94. This takeoff contact bracket 9, with its simple structure, convenient adjustment, and strong adaptability, allows for rotation and height adjustment through the cooperation of the sleeve 91 and the support rod 92, and lateral distance adjustment through the cooperation of the support plate 93 and the adjusting plate 94. In practical applications, the tray 95 is brought into contact with the takeoff detection sensor at the bottom of the aircraft. When the aircraft takes off, the takeoff detection sensor will leave the tray 95 and trigger a signal.

[0044] In a specific embodiment, the present invention employs the following structure for the rotation drive device of the swing arm unit: a gear 71 is coaxially fixed on the rotating shaft 7, a rack 72 meshing with the gear 71 is provided on the lower side of the gear 71, the rack 72 is hinged to the drive cylinder 73 fixed on the foundation frame, and a roller 74 mounted on the foundation frame is provided on the lower side of the rack 72. This configuration drives the rotating shaft 7 to rotate and rotate the swing arm 8 by driving the rack 72 to move linearly through the drive cylinder 73. It features a simple structure, strong adaptability, and remote control capability, thus improving safety. To precisely control the rotation angle and position of the swing arm 8, this specific embodiment fixes a limiting plate 75 on the rotating shaft 7. The limiting plate 75 is provided with a forward rotation positioning limit hole and a reverse rotation positioning limit hole, and the limiting plate 75 is positioned between two support plates 76 fixed on the foundation frame. A knob plunger 77 that mates with the forward rotation positioning limit hole and the reverse rotation positioning limit hole is installed on the support plate 76. After the pendulum arm 8 reaches its forward and reverse rotation positions, the rotary plunger 77 is inserted into the corresponding forward and reverse rotation limit holes on the limit plate 75. This not only enhances the stability of the structure but also effectively reduces the load on the drive cylinder 73. Furthermore, this embodiment connects two tension steel cables 81 to the upper part of the pendulum arm 8, and fixes the lower ends of the tension steel cables 81 to the foundation frame. This allows the tension steel cables 81 to limit the pendulum arm 8 after it reaches its forward rotation position, further enhancing structural stability and safety. Forward rotation refers to the pendulum arm 8 flipping towards the side closer to the aircraft, while reverse rotation refers to the pendulum arm 8 flipping away from the aircraft.

[0045] The above embodiments are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Various modifications made by those skilled in the art based on the technical solutions of the present invention without departing from the design concept of the present invention should fall within the scope of protection defined by the claims of the present invention.

Claims

1. An aircraft launch system, characterized in that, The system includes a foundation frame and a launch pad unit and a swing arm unit mounted on the foundation frame. The foundation frame is constructed by splicing multiple frame units (1) and is fixed to the ground by pressure plates and pre-embedded threaded columns. The launch pad unit includes a platform (3) mounted on the foundation frame by multiple lifting outriggers (2). The platform (3) is provided with a flow guide hole (31). Multiple support arms (4) corresponding to the aircraft support points are installed around the flow guide hole (31) on the platform (3). The lower side of the platform (3) is provided with a support arm mounted on the ground at a position corresponding to the flow guide hole (31). The guide (5) on the base frame, the swing arm unit includes a rotating shaft (7) mounted on the base frame via two bearing seats (6), a truss-type swing arm (8) fixed on the rotating shaft (7), and a rotation drive device provided at one end of the rotating shaft (7); the support arm (4) includes a support arm body (41) and an actuating cylinder (42), the lower end of the support arm body (41) is hinged to a first support (44) fixed on the platform (3) via a first pin (43), the actuating cylinder (42) includes a cylinder body (421), the lower end of the cylinder body (421) is connected to a second pin (45). Hinged to the second support (46) fixed on the platform (3), the cylinder (421) is provided with a piston (422), and the piston (422) is coaxially fixed with a piston rod (423) extending from the upper end of the cylinder (421). The piston rod (423) is hinged to the third support (48) fixed on the support arm (41) through the third pin (47). A rubber shock absorber (424) is provided on the lower side of the piston (422) in the cylinder (421). The rubber shock absorber (424) is provided with a vent hole (4241), and the vent hole (4241) is connected to an inflation / deflation channel. A return spring (425) sleeved on the piston rod (423) is provided in the cylinder (421) on the upper side of the piston (422); the rubber shock absorber (424) includes a rubber body (4242), and the outer wall of the rubber body (4242) is provided with annular grooves (4243) distributed vertically and horizontally. The groove opening width of the annular groove (4243) is greater than the groove bottom width. The rubber body (4242) is provided with support rings (4244) that are alternately distributed with the annular grooves (4243) in the vertical direction. The outer edge thickness of the support ring (4244) is less than the inner edge thickness.

2. The aircraft launch system according to claim 1, characterized in that, The piston rod (423) is provided with a short tube (4231) that slides with it. A retaining ring (4232) is provided on the outer wall of the short tube (4231). There are two return springs (425). The upper and lower ends of the upper return spring (425) press against the cylinder (421) and the retaining ring (4232) respectively. The upper and lower ends of the lower return spring (425) press against the retaining ring (4232) and the piston (422) respectively.

3. The aircraft launch system according to claim 2, characterized in that, The lower half of the support arm (41) is a through cavity structure. The cavity is provided with a limiting baffle (411) that is fixedly connected to the two side walls. The first support (44) is provided with a limiting block (441) that cooperates with the limiting baffle (411). After the support arm (41) is erected, the limiting baffle (411) and the limiting block (441) abut against each other. The top of the support arm (41) is provided with a support platform (412). A support plate (413) is fixed on the support platform (412) by bolts. A tie rod pad (49) for supporting the aircraft is rotatably mounted on the support plate (413) through a threaded hole. The tie rod pad (49) is provided with a light hole (491) for installing the windproof tie rod.

4. The aircraft launch system according to claim 3, characterized in that, The cylinder (421) includes a cylinder (4211) and an upper cap (4212) and a lower cap (4213) screwed onto the upper and lower ends of the cylinder (4211) by threads. A sealing ring is provided between the lower cap (4213) and the cylinder (4211). The bottom of the lower cap (4213) is provided with a lower support lug (4214) that is hinged to the second support (46). The piston rod (423) passes through the upper cap (4212) and the two slide together. The end of the piston rod (423) is provided with an upper support lug (4233) that is hinged to the third support (48).

5. The aircraft launch system according to claim 4, characterized in that, The lower support ear (4214) is provided with a shaft hole (4215) for installing a second pin (45). The inner wall of the shaft hole (4215) is provided with a first air passage (4216) that communicates with the vent hole (4241). The second pin (45) is provided with an annular air groove (451) in the circumferential direction at the position corresponding to the first air passage (4216). On the second pin (45) on both sides of the annular air groove (451), sealing rings are respectively installed through sealing grooves (452). An inflation head (453) is installed at one end of the second pin (45). The inflation head (453) communicates with the annular air groove (451) through the second air passage (454) set in the second pin (45). The inflation and deflation channel refers to the channel formed by the first air passage (4216), the annular air groove (451), the second air passage (454), and the inflation head (453) connected in sequence.

6. The aircraft launch system according to claim 1, characterized in that, The lifting outrigger (2) includes a fixedly connected column (21) and a worm gear lift (22). The lower end of the column (21) is connected to a ball socket (23) fixed on the foundation frame through a ball head. The worm gear lift (22) is fixedly connected to a transfer frame (32) set on the platform (3). The flow guide (5) includes a roof-shaped flow guide body (51). The two ends of the flow guide body (51) are provided with flow guide baffles (52). The bottom of the flow guide body (51) and the flow guide baffles (52) are provided with mounting seats (53) fixedly connected to the foundation frame.

7. The aircraft launch system according to claim 1, characterized in that, The platform (3) is equipped with a takeoff contact bracket (9). The takeoff contact bracket (9) includes a sleeve (91) with its lower end fixed on the platform (3). A support rod (92) is provided in the sleeve (91). A handle (911) for locking the support rod (92) is screwed onto the sleeve (91) through a threaded hole. A support plate (93) is fixed to the upper end of the support rod (92). An adjusting plate (94) is fixed to the support plate (93) by two screws. The screws are located in the elongated hole (941) of the adjusting plate (94). A tray (95) is fixed to the adjusting plate (94).

8. The aircraft launch system according to claim 1, characterized in that, The rotary drive device includes a gear (71) coaxially fixed on the rotating shaft (7), a rack (72) meshing with the lower side of the gear (71), the rack (72) being hinged to a drive cylinder (73) fixed on the foundation frame, and a roller (74) mounted on the foundation frame on the lower side of the rack (72); a limit plate (75) is also fixed on the rotating shaft (7), the limit plate (75) is provided with a forward rotation limit hole and a reverse rotation limit hole, the limit plate (75) is located between two support plates (76) fixed on the foundation frame, and a knob plunger (77) that cooperates with the forward rotation limit hole and the reverse rotation limit hole is installed on the support plate (76); the upper half of the swing rod (8) is connected to two pulling steel wire ropes (81), and the lower end of the pulling steel wire ropes (81) is fixedly connected to the foundation frame.

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