Fixed-wing unmanned aerial vehicle rocket boosting take-off device

Abstract

The invention provides a fixed-wing unmanned aerial vehicle rocket boosting take-off device which comprises a launching support, a supporting assembly and a boosting assembly, a guide rail is arranged on the launching support, and the supporting assembly is arranged on the guide rail in a sliding mode and used for supporting an unmanned aerial vehicle; the boosting assembly comprises a moving mechanism and a mounting mechanism, the moving mechanism is slidably arranged on the guide rail, the front end of the moving mechanism abuts against the supporting assembly, the rear end of the moving mechanism abuts against the guide rail, and the moving mechanism is provided with a plurality of preset positions; the mounting mechanism is arranged on the moving mechanism and used for mounting the rocket booster, and the mounting mechanism is detachably assembled at any preset position so as to adjust the position of the mounting mechanism relative to the unmanned aerial vehicle; the boosting assembly is provided with the moving mechanism and the mounting mechanism, the mounting mechanism can be fixed to the moving mechanism in a position selectable mode, accurate butt joint of the rocket booster and the unmanned aerial vehicle is facilitated, and meanwhile the problem of matching of thrust lines of rocket boosters of different models and the mass center of the unmanned aerial vehicle is solved.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) launch device technology, and in particular to a rocket-assisted takeoff device for a fixed-wing UAV. Background Technology

[0002] The takeoff performance of fixed-wing UAVs directly determines their adaptability to operational scenarios and mission deployment efficiency. Currently, the mainstream takeoff methods can be divided into: runway takeoff, catapult takeoff, vertical takeoff, and rocket-assisted takeoff.

[0003] Runway takeoff is the most traditional takeoff method, relying on the landing gear to accelerate on flat surfaces such as airport runways and roads. It requires no additional auxiliary equipment, is low in cost, and boasts outstanding safety and reliability, making it suitable for various aircraft types. Its core component is a landing gear system adapted to the weight of the drone. While its structure is simple, it has stringent site requirements, poor maneuverability, and is difficult to meet the usage needs of scenarios without flat runways, such as in the field or complex terrain.

[0004] Catapult launch, through mechanical energy storage, electromagnetic, or power traction, enables UAVs to gain takeoff speed on a short track. The core components include the catapult body, trolley, guide rails, and control system. Mainstream spring-energy-storage catapult systems use 65Mn spring steel for energy storage, combined with steel guide rails and trolleys to achieve an initial takeoff speed of 15-25 m / s. However, the entire system weighs 8-10 kg and is approximately 2 m long, resulting in insufficient portability. Intelligent catapult systems adjust servo angles and motor speeds via a flight control module, allowing for installation on uneven terrain, but still suffer from long deployment and preparation times.

[0005] Vertical takeoff combines the advantages of fixed-wing aircraft and helicopters, achieving vertical takeoff and then transitioning to horizontal flight through a thrust reversal device, resulting in extremely low dependence on terrain. However, it requires additional tilting mechanisms or dedicated lift devices, leading to poor aerodynamic efficiency and economy. Furthermore, auxiliary equipment increases system complexity, impacting safety and reliability. Currently, optimization is underway towards miniaturized, high-efficiency propulsion systems.

[0006] Rocket-assisted takeoff is one of the mainstream launch methods for small and medium-sized unmanned aerial vehicles (UAVs). Its core components include a launch pad, a compatible rocket, and a thrust line alignment assembly. In this method, the UAV rapidly gains takeoff speed and a safe altitude using rocket thrust, after which the booster automatically separates. This launch method offers outstanding maneuverability and is particularly suitable for complex operating environments such as the field and ships. To ensure a successful launch, the rocket booster's thrust line must pass through the UAV's center of gravity; otherwise, yaw or pitch moments will occur, leading to launch failure. Therefore, the device design typically pre-sets the booster's installation position to meet the aforementioned thrust line alignment requirements after the UAV is mounted. However, various errors inevitably exist during actual manufacturing and assembly, potentially causing the thrust line to deviate from the UAV's center of gravity. Therefore, a launch device capable of adjusting the booster's mounting position on the support is needed. By adjusting the booster's spatial position relative to the UAV, manufacturing and assembly errors can be compensated for, thereby achieving precise docking between the rocket booster and the UAV. Summary of the Invention

[0007] The purpose of this application is to address the above problems by providing a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle, comprising: A launch bracket, on which a guide rail is provided; A support assembly is slidably disposed on the guide rail and is used to support the drone. The booster assembly includes a moving mechanism and an installation mechanism. The moving mechanism is slidably mounted on the guide rail, with its front end abutting against the support assembly and its rear end abutting against the guide rail. The moving mechanism has multiple preset positions. The installation mechanism is mounted on the moving mechanism and is used to install the rocket booster. The installation mechanism can be detachably mounted on any of the preset positions to adjust the position of the installation mechanism relative to the UAV.

[0008] According to the technical solutions provided in certain embodiments of this application, the moving mechanism includes: A first base, with first rollers rotatably connected to its four corners, the first rollers being able to roll in contact with the guide rail; A first mounting plate is disposed on the first base. The first mounting plate is provided with multiple sets of first mounting holes, each set of first mounting holes being used to fix the mounting mechanism.

[0009] According to the technical solutions provided in certain embodiments of this application, the installation mechanism includes: A second mounting plate is provided with a plurality of second mounting holes, which are respectively provided to correspond to each group of first mounting holes; the second mounting plate is fixed to the first mounting plate by fasteners, and the second mounting plate is provided with a mounting body; A support component, which is disposed on the mounting body, is used to place the rocket booster; Clamps, a plurality of said clamps are movably connected to said support member, said clamps being used to cooperate with said support member to radially fix the rocket booster; A fixing cap is movably connected to the support member and is used to cooperate with the support member to axially fix the rocket booster.

[0010] According to the technical solutions provided in certain embodiments of this application, the supporting component includes: The second base has two rollers rotatably connected to its four corners, and the rollers are able to roll in contact with the guide rail. The support frame body is mounted on the second base and has a support interface that is adapted to the connecting rod of the UAV.

[0011] According to the technical solutions provided in certain embodiments of this application, the launching bracket includes: The mounting frame has a first bracket hinged to its bottom and a second bracket fixedly connected thereto; the mounting frame is equipped with the guide rail. The telescopic component has two ends hinged to the mounting frame and the first bracket, respectively, and is used to adjust the angle between the mounting frame and the horizontal direction.

[0012] According to the technical solutions provided in certain embodiments of this application, the rear end of the second base is provided with a thrust beam, and the free end of the thrust beam abuts against the booster assembly.

[0013] According to the technical solutions provided in some embodiments of this application, the support interface is a thrust transmission surface, and the height of the thrust transmission surface gradually decreases along the launch direction of the UAV.

[0014] According to the technical solutions provided in certain embodiments of this application, the fixing cap includes a main body, a first connecting part, and a second connecting part. The main body is used to abut against one end of the rocket booster to cooperate with the support member to axially limit the rocket booster. The first connecting part is used to be fixedly connected to the support member, and the second connecting part is used to be fixedly connected to the rocket booster.

[0015] According to the technical solutions provided in certain embodiments of this application, the main body is provided with a plurality of clearance holes.

[0016] According to the technical solutions provided in certain embodiments of this application, the support member is provided with a fixing part, which is used to abut against the end of the rocket booster away from the fixing cap, so as to cooperate with the fixing cap to axially limit the rocket booster. The fixing part is also provided with a through hole.

[0017] Compared with the prior art, the beneficial effects of this application are as follows: This application provides a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle (UAV), including a launch bracket, a support assembly, and a booster assembly. The launch bracket is provided with a guide rail, and the support assembly is slidably mounted on the guide rail to support the UAV. The booster assembly includes a moving mechanism and a mounting mechanism. The moving mechanism is slidably mounted on the guide rail, with its front end abutting against the support assembly and its rear end abutting against the guide rail. The moving mechanism has multiple preset positions. The mounting mechanism is mounted on the moving mechanism and is used to mount the rocket booster. The mounting mechanism can be detachably mounted on any preset position to adjust the position of the mounting mechanism relative to the UAV. By setting the booster assembly as a moving mechanism and a mounting mechanism, and with the mounting mechanism detachably connected to the moving mechanism and optionally fixed to the moving mechanism, the position of the rocket booster relative to the UAV can be adjusted. This facilitates precise docking of the rocket booster and the UAV within a limited space and solves the problem of matching the thrust lines of different types of rocket boosters with the center of mass of the UAV, ensuring stable launch of the UAV.

[0018] It should be understood that the descriptions of technical features, technical solutions, beneficial effects, or similar language in this application do not imply that all features and advantages can be achieved in any single embodiment. Rather, it is understood that the description of a feature or beneficial effect means that a specific technical feature, technical solution, or beneficial effect is included in at least one embodiment. Therefore, the descriptions of technical features, technical solutions, or beneficial effects in this specification do not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions, and beneficial effects described in this embodiment can be combined in any suitable manner. Those skilled in the art will understand that embodiments can be implemented without one or more specific technical features, technical solutions, or beneficial effects of a particular embodiment. In other embodiments, additional technical features and beneficial effects may be identified in specific embodiments that do not embody all embodiments. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying 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.

[0020] Figure 1 A schematic diagram of a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in this application embodiment; Figure 2 A schematic diagram of the structure of a guide rail for a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in this application embodiment; Figure 3 A schematic diagram of the structure of a support assembly for a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in this application embodiment; Figure 4 A schematic diagram of the structure of a booster assembly of a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in this application embodiment; Figure 5 A schematic diagram of the moving mechanism of a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in this application embodiment; Figure 6 A schematic diagram of the installation mechanism of a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in this application embodiment; Figure 7 This is a schematic diagram of the structure of the fixed cap of a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle provided in an embodiment of this application.

[0021] The text labels in the image represent: 1. Launch bracket; 2. Support assembly; 3. Boost assembly; 4. Guide rail; 11. Mounting frame; 12. First bracket; 13. Second bracket; 14. Telescopic component; 21. Second base; 22. Support frame body; 23. Second roller; 24. Thrust beam; 25. Support plate; 31. First base; 32. First mounting plate; 33. Second mounting plate; 34. First roller; 35. Mounting body; 36. Support component; 37. Clamp; 38. Fixing cap; 41. First lug; 111. Second lug; 361. Third lug; 362. Fourth lug; 363. Fixing part; 381. Main body; 382. First connecting part; 383. Second connecting part. Detailed Implementation

[0022] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. The descriptions in this section are merely illustrative and explanatory, and should not be construed as limiting the scope of protection of this application. Specifically, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this invention.

[0023] It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0024] As mentioned in the background section, in order to solve the problems existing in the prior art, this embodiment provides a rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle, comprising: Launch bracket 1, with guide rail 4 mounted on it; Support component 2 is slidably mounted on guide rail 4 and is used to support the drone. The booster assembly 3 includes a moving mechanism and an installation mechanism. The moving mechanism is slidably mounted on the guide rail 4. The front end of the moving mechanism abuts against the support assembly 2, and the rear end abuts against the guide rail 4. The moving mechanism has multiple preset positions. The installation mechanism is mounted on the moving mechanism and is used to install the rocket booster. The installation mechanism can be detachably assembled and disassembled at any preset position to adjust the position of the installation mechanism relative to the UAV.

[0025] like Figure 1-7 As shown, the launch support 1, as the main load-bearing structure of the takeoff device, is approximately a triangular frame structure. The top of the launch support 1 has a load-bearing plane, on which a guide rail 4 is fixed. The guide rail 4 is made of Q235-A steel to ensure sufficient rigidity. The guide rail 4 includes two channel steels, which are welded together with reinforcing plates to form a frame structure, improving longitudinal bending resistance and lateral torsional resistance. First lugs 41 are welded to the opposite sides of the two channel steels, and multiple first lugs 41 are distributed along the length of the channel steels. The channel steels can be fixed to the launch support 1 via the first lugs 41. The support assembly 2 supports the front end of the UAV, mainly bearing the weight of the front half of the UAV. When the rocket booster ignites, the support assembly 2 supports the UAV and moves forward together on the guide rail 4. The booster assembly 3 has a moving mechanism and a mounting mechanism. The moving mechanism abuts against the rear end of the support assembly 2 and can move on the guide rail 4. The mounting mechanism is used to fix the rocket booster. The booster assembly 3 supports the entire weight of the rocket booster and the rear end of the UAV and bears various loads caused during launch. By adjusting the fixed position of the mounting mechanism on the moving mechanism, it can be ensured that the thrust line of the rocket booster passes accurately through the center of mass of the UAV. Furthermore, the guide rail 4 is provided with a limiting structure, which abuts against the rear end of the moving mechanism to limit the moving mechanism in one direction and prevent the booster assembly 3 from slipping off the guide rail.

[0026] In use, adjust the position of the mounting mechanism on the moving mechanism so that the thrust line of the rocket booster is aligned with the center of mass of the UAV, and fix the mounting mechanism and the moving mechanism; install the UAV and rocket booster onto the takeoff device. When the takeoff command is received, the rocket booster ignites to provide thrust and initial velocity. The rocket booster drives the UAV and booster assembly 3 to move on the guide rail 4, while the booster assembly 3 pushes the support assembly 2 to move together; when the support assembly 2 separates from the front end of the guide rail 4, the support assembly 2 is only affected by gravity and will move along a parabola to separate from the UAV. At this time, the rocket booster continues to push the UAV and booster assembly 3 to accelerate along the thrust line; after the internal fuel of the rocket booster is completely burned, the thrust disappears, and the rocket booster and booster assembly 3 detach from the UAV. At this time, the UAV has gained a certain control speed and completes the entire takeoff process by doing work with the engine at the tail.

[0027] By setting the booster assembly 3 as a moving mechanism and an installation mechanism, the installation mechanism is detachably connected to the moving mechanism and can be fixed to the moving mechanism in an optional position, thereby adjusting the position of the rocket booster relative to the UAV. This facilitates precise docking of the rocket booster and the UAV in a limited space, and also solves the problem of matching the thrust lines of different types of rocket boosters with the center of mass of the UAV, ensuring that the UAV can be launched stably.

[0028] In a preferred embodiment, the moving mechanism includes: The first base 31 has four corners rotatably connected to first rollers 34, which can roll in contact with the guide rail 4. The first mounting plate 32 is disposed on the first base 31. The first mounting plate 32 is provided with multiple sets of first mounting holes, each set of first mounting holes being used to fix the mounting mechanism.

[0029] like Figure 4-6As shown, the first base 31 is mainly used to support the remaining structure of the booster assembly 3 to move on the guide rail 4. The first base 31 is a rectangular frame composed of a first crossbeam and a first longitudinal beam. The first base 31 is welded from aluminum profile rectangular tubes to ensure that the first base 31 has sufficient rigidity and strength. The first roller 34 is made of PEEK (polyetheretherketone) material. PEEK material has the advantages of heat resistance, wear resistance, self-lubrication, high strength, and lightweight. The ends of the two first crossbeams are respectively welded with aluminum blocks with a thickness of 10mm and threaded holes are provided so that the first roller 34 can be installed on the guide rail 4 by bolts. On a base 31, a first mounting plate 32 is a rectangular plate whose length direction is the launch direction of the UAV. The first mounting plate 32 is welded to two first crossbeams. Multiple first mounting holes are respectively located at both ends of the width direction of the first mounting plate 32 and are equally spaced along the length direction of the first mounting plate 32. The mounting mechanism can optionally be fixed to the first mounting plate 32 through some of the first mounting holes, thereby changing the fixed position of the mounting mechanism relative to the first mounting plate 32 in the launch direction of the UAV, thereby adjusting the relative position of the rocket booster and the UAV, and ensuring that the thrust line of the rocket booster passes through the center of mass of the UAV.

[0030] Furthermore, the installation mechanism includes: The second mounting plate 33 has multiple second mounting holes, which are respectively set to correspond to each group of first mounting holes; the second mounting plate 33 is fixed to the first mounting plate 32 by fasteners, and the second mounting plate 32 has a mounting body 35. Support member 36 is provided on the mounting body 35 and is used to place the rocket booster. Clamps 37, multiple clamps 37 are movably connected to the support member 36, and the clamps 37 are used to cooperate with the support member 36 to radially fix the rocket booster; The fixing cap 38 is movably connected to the support member 36 and is used to cooperate with the support member 36 to axially fix the rocket booster. For details, please refer to Figure 4-6The second mounting plate 33 has the same structure as the first mounting plate 32. The second mounting plate 33 has three sets of second mounting holes distributed along its length, with two holes in each set. The second mounting plate 33 can move along its own length on the first mounting plate 32, aligning the second mounting holes with different first mounting holes, and is fixed by fasteners passing through the corresponding second and first mounting holes. Furthermore, the fasteners can be bolts and nuts, ensuring that at least four second mounting holes correspond to the first mounting holes when the relative positions of the second mounting plate 33 and the first mounting plate 32 are changed, thus guaranteeing a stable connection between the second mounting plate 33 and the first mounting plate 32. The mounting body 35 is entirely made of welded aluminum material and is fixed to the second mounting plate 33. A support member 36, made of aluminum tubing, is fixed above it and used to hold the rocket booster. The booster and the support member 36 have multiple third lugs 361 fixed on both radial sides. The third lugs 361 can cooperate with the clamp 37 to make the clamp 37 hold the rocket booster tightly and fix the rocket booster radially. The support member 36 has a fourth lug 362 at one axial end. The fourth lug 362 can be fixed with the fixing cap 38 by bolts so that the fixing cap 38 abuts against the front end of the rocket booster and fixes the rocket booster axially. Optionally, the first mounting plate 32 can also have multiple first mounting holes distributed along its width at both ends in the length direction. The number of the two sets of second mounting holes at both ends in the length direction of the second mounting plate 33 can be appropriately increased to ensure that at least four second mounting holes can correspond to the first mounting holes respectively. This allows the fixing position of the second mounting plate 33 and the first mounting plate 32 to be adjusted in the width direction of the second mounting plate 33, further ensuring that the thrust line of the rocket booster passes accurately through the center of mass of the UAV.

[0031] Furthermore, the fixing cap 38 includes a main body 381, a first connecting part 382, ​​and a second connecting part 383. The main body 381 is used to abut against one end of the rocket booster to cooperate with the support member 36 to axially limit the rocket booster. The main body 381 is provided with a plurality of clearance holes. The first connecting part 382 is used to be fixedly connected to the support member 36, and the second connecting part 383 is used to be fixedly connected to the rocket booster. The support member 36 is provided with a fixing part 363, which is used to abut against the end of the rocket booster away from the fixing cap 38, so as to cooperate with the fixing cap 38 to axially limit the rocket booster. The fixing part 363 is also provided with a through hole. For details, please refer to Figure 7The fixing cap 38 is used to withstand the forward force when the rocket booster ignites and to transmit the thrust to the entire booster assembly 3. The fixing cap 38 includes a main body 381, a first connecting part 382, ​​and a second connecting part 383. The main body 381 is fastened to the front end of the rocket booster and has multiple clearance holes to prevent interference between the main body 381 and the end structure of the rocket booster when the fixing cap 38 is connected to the support member 36. The first connecting part 382 is the fifth lug and can be fixedly connected to the fourth lug 362 on the support member 36 by bolts. The second connecting part 383 is approximately cylindrical in shape, and the front end of the rocket booster can be connected to the second connecting part. The second connecting part 383 has multiple connecting holes on its side wall, allowing it to be fixedly connected to the rocket booster. The support member 36 has a fixing part 363 at its end away from the fixing cap 38. The fixing part 363 has a through hole and an annular protrusion near the through hole. This annular protrusion is used to limit the rocket booster's position. When the rocket booster is placed on the support member 36, its rear end passes through the through hole, and its main body abuts against the annular protrusion. At this time, the fixing cap 38 and the fixing part 363 cooperate to axially fix the rocket booster.

[0032] In a preferred embodiment, the support component 2 includes: The second base 21 has two second rollers 23 rotatably connected to its four corners, and the second rollers 23 can roll in contact with the guide rail 4. The support frame body 22 is mounted on the second base 21. The support frame body 22 is provided with a support interface, which is adapted to the connecting rod of the UAV.

[0033] like Figure 3 As shown, the support component 2 is used to support the front end of the drone, mainly supporting the weight of the front half of the drone. The second base 21 is a rectangular frame composed of the second crossbeam and the second longitudinal beam. The second base 21 is welded from aluminum profile rectangular tubes. The second roller 23 is also made of PEEK (polyether ether ketone) material, and the connection method between the second roller 23 and the second base 21 is the same as the connection method between the first roller 34 and the first base 31, which will not be described again here. The support frame body 22 is made of aluminum profile rectangular tubes and angle aluminum welded together. The overall structure is approximately a triangular prism. The top of the support frame body 22 is provided with a support plate 25. The top of the support plate 25 is provided with a support interface. The support interface is adapted to the connecting rod of the drone, so that the support component 2 can support the drone. The support plate 25 is made of 6061 aluminum material and is manufactured by welding and machining. The support plate 25 is connected to the top of the support frame body 22 by bolts. The support plate 25 can also be adapted to different drones to form a support interface that can meet the needs of various drones.

[0034] Furthermore, a thrust beam 24 is provided at the rear end of the second base 21, and the free end of the thrust beam 24 abuts against the booster assembly 3. For details, please refer to Figure 3 Two thrust beams 24 are provided on the side of the second base 21 near the first base 31. The free ends of the thrust beams 24 abut against the front end of the first base 31. When the rocket booster ignites and drives the booster assembly 3 and the UAV to move along the guide rail 4, the first base 31 transmits the thrust to the second base 21 through the thrust beams 24, and pushes the support assembly 2 to move along the guide rail 4 together. By setting the thrust beams 24 to make the support assembly 2 abut against the booster assembly 3, compared with the traditional method of fixing the support assembly 2 to the guide rail 4 with explosive bolts or pull pins, the launch operation steps are simplified, and the launch failure problem caused by the accidental release of the above-mentioned fixing structure is avoided.

[0035] Furthermore, the support interface is a thrust transmission surface, the height of which gradually decreases along the launch direction of the UAV.

[0036] For details, please refer to Figure 3 The top of the support plate 25 has a first protrusion and a second protrusion along the length of the guide rail 4. The first protrusion is located on the side of the second protrusion closer to the launch direction of the UAV. A support interface is formed between the first protrusion and the second protrusion. The height of the first protrusion on the support frame body 22 is lower than the height of the second protrusion. When the UAV is installed, its connecting rod is placed in the support interface, and the second protrusion abuts against the connecting rod. When the rocket booster is ignited, the rocket booster drives the UAV and the booster assembly 3 to move on the guide rail 4. At the same time, the booster assembly 3 pushes the support assembly 2 to move together through the thrust beam 24. At this time, the support assembly 2 can also push the front of the UAV through the second protrusion. When the support assembly 2 separates from the front end of the guide rail 4, the support assembly 2 will move along a parabola under the influence of gravity. Due to the design that the first protrusion is lower than the second protrusion, the connecting rod of the UAV can naturally detach from the support interface, ensuring a clean and efficient separation sequence during the launch of the UAV and avoiding separation interference.

[0037] In a preferred embodiment, the launch bracket 1 includes: Mounting frame 11, with a first bracket 12 hinged to the bottom of mounting frame 11 and a second bracket 13 fixedly connected thereto; guide rail 4 is provided on mounting frame 11. The telescopic component 14 has two ends that are hinged to the mounting frame 11 and the first bracket 12, respectively. The telescopic component 14 is used to adjust the angle between the mounting frame 11 and the horizontal direction.

[0038] like Figure 1As shown, the mounting frame 11 is also made of Q235-A steel. A second lug 111 is welded to the mounting frame 11 corresponding to the first lug 41. The guide rail 4 can be fixed to the mounting frame 11 via the first lug 41 and the second lug 111. The first bracket 12 and the second bracket 13 are both located at the bottom of the mounting frame 11. One end of the first bracket 12 is supported on the ground, and the other end is hinged to the mounting frame 11. One end of the second bracket 13 is supported on the ground and fixedly connected to the mounting frame 11 via a support rod; the other end is fixed to the support frame. The structure is a triangular frame. A telescopic member 14 is provided between the first support 12 and the mounting frame 11. The telescopic member 14 can be a hydraulic telescopic rod or a pneumatic telescopic rod in the prior art. In this embodiment, there are two telescopic members 14. The bottom of the telescopic member 14 is hinged to the first support 12, and its telescopic end is hinged to the mounting frame 11. The telescopic member 14 adjusts the angle between the mounting frame 11 and the ground by telescopic adjustment, thereby changing the extension direction of the guide rail 4, so that the UAV can be launched within the pitch angle range of 30°-48° to adapt to different take-off conditions.

[0039] Working principle: In use, adjust the position of the second mounting plate 33 on the first mounting plate 32 so that the thrust line of the rocket booster is aligned with the center of mass of the UAV, and fix the second mounting plate 33 and the first mounting plate 32 with fasteners; install the UAV and rocket booster on the takeoff device. When the takeoff command is received, the rocket booster ignites to provide thrust and initial velocity. The rocket booster drives the UAV and booster assembly 3 to move on the guide rail 4. At the same time, the booster assembly 3 pushes the support assembly 2 to move together through the thrust beam 24. At this time, the support assembly 2 can also push the front of the UAV through the second protrusion; when the support assembly 2 separates from the front end of the guide rail 4, the support assembly 2 is only affected by gravity and will move along a parabola to separate from the UAV. At this time, the rocket booster continues to push the UAV and booster assembly 3 to accelerate along the thrust line; after the internal fuel of the rocket booster is completely burned, the thrust disappears, the rocket booster and booster assembly 3 separate from the UAV. At this time, the UAV has gained a certain control speed and completes the entire takeoff process by doing work with the engine at the tail.

[0040] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are merely preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle, characterized in that, include: Launching bracket (1), on which a guide rail (4) is provided; Support component (2), which is slidably disposed on the guide rail (4), is used to support the UAV; The booster assembly (3) includes a moving mechanism and an installation mechanism. The moving mechanism is slidably mounted on the guide rail (4). The front end of the moving mechanism abuts against the support assembly (2), and the rear end abuts against the guide rail (4). The moving mechanism has multiple preset positions. The installation mechanism is mounted on the moving mechanism and is used to install the rocket booster. The installation mechanism can be detachably mounted on any of the preset positions to adjust the position of the installation mechanism relative to the UAV.

2. The fixed-wing unmanned aerial vehicle rocket-assisted takeoff device according to claim 1, characterized in that, The moving mechanism includes: The first base (31) has first rollers (34) rotatably connected to its four corners, and the first rollers (34) can roll in contact with the guide rail (4). The first mounting plate (32) is disposed on the first base (31). The first mounting plate (32) is provided with multiple sets of first mounting holes, each set of first mounting holes being used to fix the mounting mechanism.

3. The fixed-wing unmanned aerial vehicle rocket-assisted takeoff device according to claim 2, characterized in that, The installation mechanism includes: The second mounting plate (33) is provided with a plurality of second mounting holes, which are respectively provided with corresponding first mounting holes in each group; the second mounting plate (33) is fixed to the first mounting plate (32) by fasteners, and the second mounting plate (33) is provided with a mounting body (35). Support (36), the support (36) is provided on the mounting body (35), the support (36) is used to place the rocket booster; Clamps (37), a plurality of clamps (37) are movably connected to the support (36), the clamps (37) being used to cooperate with the support (36) to radially fix the rocket booster; A fixing cap (38) is movably connected to the support member (36) and is used to cooperate with the support member (36) to axially fix the rocket booster.

4. The fixed-wing unmanned aerial vehicle rocket-assisted takeoff device according to claim 1, characterized in that, The support component (2) includes: The second base (21) has two second rollers (23) rotatably connected to its four corners. The second rollers (23) can roll in contact with the guide rail (4). The support frame body (22) is located on the second base (21). The support frame body (22) is provided with a support interface, which is adapted to the connecting rod of the UAV.

5. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle according to claim 1, characterized in that, The launch bracket (1) includes: The mounting frame (11) has a first bracket (12) hinged to its bottom and a second bracket (13) fixedly connected thereto; the mounting frame (11) is provided with the guide rail (4). Telescopic component (14), the two ends of which are hinged to the mounting frame (11) and the first bracket (12) respectively, the telescopic component (14) is used to adjust the angle between the mounting frame (11) and the horizontal direction.

6. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle according to claim 4, characterized in that, The second base (21) has a thrust beam (24) at its rear end, and the free end of the thrust beam (24) abuts against the booster assembly (3).

7. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle according to claim 4, characterized in that, The support interface is a thrust transmission surface, and the height of the thrust transmission surface gradually decreases along the launch direction of the UAV.

8. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle according to claim 3, characterized in that, The fixing cap (38) includes a main body (381), a first connecting part (382), and a second connecting part (383). The main body (381) is used to abut against one end of the rocket booster to cooperate with the support member (36) to axially limit the rocket booster. The first connecting part (382) is used to be fixedly connected to the support member (36), and the second connecting part (383) is used to be fixedly connected to the rocket booster.

9. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle according to claim 8, characterized in that, The main body (381) is provided with a plurality of clearance holes.

10. A rocket-assisted takeoff device for a fixed-wing unmanned aerial vehicle according to claim 3, characterized in that, The support member (36) is provided with a fixing part (363), which is used to abut against the end of the rocket booster away from the fixing cap (38) to cooperate with the fixing cap (38) to axially limit the rocket booster. The fixing part (363) is also provided with a through hole.

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