Intelligent catapult system of fixed-wing aircraft

Abstract

The invention discloses an intelligent catapult system for a fixed-wing aircraft. The intelligent catapult system comprises a catapult assembly, an aircraft and a control system. The catapult assembly comprises a catapult body, one end of the catapult body is movably connected with a supporting frame, a catapult unhooking hook is arranged at the top of the catapult body, and a hook matched with the catapult unhooking hook is arranged at the bottom end of the aircraft. The control system comprises an aircraft module, a catapult module and a remote control module. The aircraft module comprises a first radio frequency module and a flight control module. A consumer can place the catapult at will in an uneven outdoor place, and when the catapult is installed on the uneven ground, the angle of the fixed-wing aircraft installed on the catapult is not ideal, but the angles of the aileron steering engine module, the flap steering engine module, the elevator steering engine module and the rudder steering engine module, the rotating speed of the motor module and the like are adjusted through steering engines. And the aircraft is in an optimal ejection state.

Description

Technical Field

[0001] The present invention relates in particular to an intelligent catapult system for a fixed-wing aircraft. Background Art

[0002] Existing fixed-wing aircraft catapults for industrial and military use primarily mechanical energy storage or powered traction to achieve short-distance, high-speed launches. Their core purpose is to address the challenge of takeoff in runway-free conditions. The current mainstream spring-energy storage catapult system (the mainstream low-cost solution) uses a motor or manual winch to stretch a spring (tension or torsion spring), storing elastic potential energy in the spring. For example, in a spring-powered system, a wire rope connects the spring to the drone's pulley. A motor drives a lead screw to pull the tow hook, stretching the spring to a preset position. Once a trigger mechanism (such as an electromagnetic lock or mechanical lock) is released, the spring instantly rebounds, accelerating the pulley along a steel guide rail via a pulley system and wire rope. The pulley propels the drone to its takeoff speed (typically 15-25 m / s) and then releases the pulley and launches into the air. At the end of the steel guide rail, the pulley impacts a buffer, slowing the vehicle to a stop. However, due to the large amount of energy storage (the kinetic energy required for a 2kg drone to take off at an initial speed of 15m / s is 225 joules, and considering friction loss, the energy storage system needs to store more than 350 joules), the energy storage system (tension spring / torsion spring) mostly uses 65Mn spring steel, weighing more than 3kg. Together with the steel guide rails, pulleys, and steel outer frame, the total system mass is usually 8-10kg, and the length is about 2m, which is very unportable.

[0003] Currently, no effective solutions have been proposed for the problems in related technologies. Summary of the Invention

[0004] In response to the problems in the related art, the present invention proposes an intelligent catapult system for fixed-wing aircraft to overcome the above-mentioned technical problems existing in the existing related art.

[0005] To this end, the specific technical solutions adopted in the present invention are as follows:

[0006] An intelligent catapult system for a fixed-wing aircraft, comprising a catapult assembly, an aircraft, and a control system;

[0007] The ejection assembly includes an ejector body, one end of which is movably connected to a support frame, a ejector release hook provided on the top of the ejector body, and a hook adapted to the ejector release hook provided on the bottom of the aircraft;

[0008] The control system includes an aircraft module, a catapult module and a remote control module, wherein the aircraft module includes a radio frequency module 1 and a flight control module;

[0009] The catapult module includes a steering gear and a battery for driving the catapult to unhook;

[0010] The remote control module includes a remote controller, a second radio frequency module and a control module.

[0011] Preferably, the flight control module includes an electronic gyroscope and an optical flow sensor.

[0012] Preferably, the flight control module further includes an aileron servo module, a flap servo module, an elevator servo module, a rudder servo module and a motor module.

[0013] Preferably, a switch for controlling the unhooking of the catapult is provided on the catapult body.

[0014] Preferably, an inclined arc frame is provided on the top of the catapult body and on both sides of the catapult unhooking portion, and a roller is provided on the top of the arc frame.

[0015] Preferably, the remote controller is communicatively connected to the catapult body via a wired signal line.

[0016] Preferably, the catapult is unhooked to eject the aircraft through an ejection energy storage system.

[0017] Preferably, the ejection energy storage system includes but is not limited to one of a spring, a rubber band, an air pressure tank, and an electromagnetic force energy storage method.

[0018] The beneficial effects of the present invention are as follows: consumers can freely place the catapult outdoors on uneven ground. When installing on uneven ground, the angle of the fixed-wing aircraft installed on the catapult is not ideal. However, by adjusting the angles of the aileron servo module, the flap servo module, the elevator servo module, the rudder servo module and the speed of the motor module, the aircraft is placed in the optimal catapult state. The elevator / flaps / ailerons are proportionally adjusted in real time by the servo. The attitude information of the aircraft mainly refers to the angle between the aircraft and the ground. This information is sensed by sensors such as gyroscopes and ground optical flow, and the angle of attack of the wing can be determined.

[0019] Before ejection, the aircraft's power system can be turned on, that is, the motor drives the propeller to rotate and provide pulling force. In this state, the ejection distance can be reduced and the power output of the energy storage system can be reduced;

[0020] The rollers are used to support the balance of the aircraft's main wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0022] Figure 1 is a schematic structural diagram of an intelligent catapult system for a fixed-wing aircraft according to an embodiment of the present invention;

[0023] Figure 2 2. It is a schematic diagram of a takeoff state of a fixed-wing aircraft intelligent catapult system according to an embodiment of the present invention;

[0024] Figure 3 1 is a schematic diagram of a fixed-wing aircraft intelligent catapult system according to an embodiment of the present invention.

[0025] In the picture:

[0026] 1. Ejection assembly; 2. Aircraft; 3. Catapult body; 4. Support frame; 5. Catapult release; 6. Hook; 7. Aircraft module; 8. Catapult module; 9. Remote control module; 10. Radio frequency module 1; 11. Flight control module; 12. Servo; 13. Battery; 14. Remote control; 15. Radio frequency module 2; 16. Control module; 17. Electronic gyroscope; 18. Optical flow sensor; 19. Aileron servo module; 20. Flap servo module; 21. Elevator servo module; 22. Rudder servo module; 23. Motor module; 24. Switch; 25. Arc frame; 26. Roller. DETAILED DESCRIPTION

[0027] To further illustrate each embodiment, the present invention provides drawings, which are part of the disclosure of the present invention. They are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. By referring to these contents, ordinary technicians in this field should be able to understand other possible implementation methods and advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are generally used to represent similar components.

[0028] According to an embodiment of the present invention, a fixed-wing aircraft intelligent catapult system is provided.

[0029] Example 1:

[0030] like Figure 1-3 As shown, the fixed-wing aircraft intelligent catapult system according to an embodiment of the present invention includes a catapult assembly 1, an aircraft 2 and a control system;

[0031] The ejection assembly 1 includes an ejection body 3, one end of which is movably connected to a support frame 4, a ejection release hook 5 is provided on the top of the ejection body 3, and a hook 6 adapted to the ejection release hook 5 is provided at the bottom end of the aircraft 2;

[0032] The control system includes an aircraft module 7, a catapult module 8 and a remote control module 9. The aircraft module 7 includes a radio frequency module 10 and a flight control module 11;

[0033] The catapult module 8 includes a steering gear 12 and a battery 13 for driving the catapult unhooking 5;

[0034] The remote control module 9 includes a remote controller 14 , a radio frequency module 2 15 and a control module 16 .

[0035] Example 2:

[0036] like Figure 1-3 As shown, the flight control module 11 includes an electronic gyroscope 17 and an optical flow sensor 18 .

[0037] The flight control module 11 further includes an aileron servo module 19 , a flap servo module 20 , an elevator servo module 21 , a rudder servo module 22 and a motor module 23 .

[0038] The ejector body 3 is provided with a switch 24 for controlling the ejector unhooking 5 .

[0039] Example 3:

[0040] like Figure 1-3 As shown, an inclined arc frame 25 is provided at the top of the catapult body 3 and on both sides of the catapult unhooking 5 , and a roller 26 is provided at the top of the arc frame 25 .

[0041] The remote controller 14 is communicatively connected to the catapult body 3 via a wired signal line.

[0042] The ejector unhooking 5 ejects the aircraft 2 through the ejection energy storage system.

[0043] The ejection energy storage system includes but is not limited to one of a spring, a rubber band, an air pressure tank, and an electromagnetic force energy storage method.

[0044] This system eliminates the spring energy storage system and instead uses a brushless motor (which can also be driven through a gear train) to directly drive a rigid chain that propels the trolley. The brushless motor's electronic driver has a brake function that controls the motor to brake when the trolley approaches the end, thereby braking the trolley and rapidly decelerating it, minimizing impact on the buffer and outer frame. The buffer can even be eliminated. A sensor (e.g., a photoelectric sensor or pressure sensor) is installed near the end of the guide rail. When the trolley reaches this position, the sensor sends a signal to the electronic driver, which activates the motor to brake. This system is low-cost, lightweight, and portable. The elimination of the energy storage system and the minimal impact of the brake function on the outer frame significantly reduce the strength requirements of the catapult system, allowing the use of aluminum components or even high-strength engineering plastics, resulting in a low cost and lightweight design. The weight can be kept under 3 kg. The catapult is foldable, less than 1 meter in length when folded, and can be loaded horizontally into a car trunk. There is no internal power supply. To improve reliability and reduce charging hassles for the user, the catapult is powered by aircraft batteries. Users can directly plug one or more aircraft batteries into the power supply slot to power the system. The launcher offers a variety of triggering methods. It can be triggered by the electronic button on the launcher itself or by connecting it to a smart remote control via a wired connection. Expandable. The rear of the smart launcher features multiple ports for attaching various accessories, such as cup holders, phone holders, and parasol holders, optimizing the outdoor user experience. The launch angle is adjustable. The two front support legs can be manually adjusted in length, and a spirit level is included to ensure the launch system is level.

[0045] In order to facilitate understanding of the above technical solutions of the present invention, the working principle or operation mode of the present invention in actual process is described in detail below.

[0046] In actual use, the remote controller 14 and the aircraft 2 communicate using 2.4G wireless radio frequency signals (or other wireless information channels such as 5.8G). The remote controller 14 has a one-touch ejection mode lever (or button). After the remote controller 14 sends the ejection signal, the catapult 5 is unhooked and the aircraft 2 is ejected through the ejection energy storage system. Before ejection, the power system of the aircraft 2 can be turned on, that is, the motor drives the propeller to rotate to provide pulling force. In this state, the ejection distance and the power output of the energy storage system can be reduced. The roller 26 is used to support the balance of the main wing of the aircraft 2. The angles of the aileron servo module 19, the flap servo module 20, the elevator servo module 21, and the rudder servo module 22 and the speed of the motor module 23 are adjusted by the servo to ensure that the aircraft 2 is in the optimal ejection state. The elevator, flaps, and ailerons are adjusted proportionally and in real time by the servo. The attitude information of the aircraft 2 mainly refers to the angle between the aircraft and the ground. This information is sensed by sensors such as gyroscopes and ground optical flow, and the angle of attack of the wing can be determined.

[0047] In summary, with the help of the above-mentioned technical solution of the present invention, consumers can place the catapult at will outdoors on uneven ground. When installed on uneven ground, the angle of the fixed-wing aircraft installed on the catapult is not ideal. However, the angles of the aileron servo module 19, the flap servo module 20, the elevator servo module 21, the rudder servo module 22 and the speed of the motor module 23 are adjusted by the servo to put the aircraft 2 in the best catapult state. The elevator / flaps / ailerons are adjusted proportionally in real time by the servo. The attitude information of the aircraft 2 mainly refers to the angle information between the aircraft and the ground. This information is sensed by sensors such as gyroscopes and ground optical flow, and the angle of attack of the wing can be determined. Before catapult, the power system of the aircraft 2 can be turned on, that is, the motor drives the propeller to rotate to provide pulling force. In this state, the catapult distance can be reduced and the power output of the energy storage system can be reduced. The roller 26 is used to support the balance of the main wing of the aircraft 2.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A fixed-wing aircraft intelligent catapult system, characterized in that: It includes a ejection assembly (1), an aircraft (2) and a control system; The ejection assembly (1) includes an ejector body (3), one end of the ejector body (3) is movably connected to a support frame (4), the top of the ejector body (3) is provided with an ejector release hook (5), and the bottom end of the aircraft (2) is provided with a hook (6) adapted to the ejector release hook (5); The control system includes an aircraft module (7), a catapult module (8) and a remote control module (9), wherein the aircraft module (7) includes a radio frequency module (10) and a flight control module (11); The catapult module (8) includes a steering engine (12) and a battery (13) for driving the catapult to unhook (5); The remote control module (9) comprises a remote controller (14), a second radio frequency module (15) and a control module (16).

2. The fixed-wing aircraft intelligent catapult system according to claim 1, characterized in that: The flight control module (11) includes an electronic gyroscope (17) and an optical flow sensor (18).

3. The fixed-wing aircraft intelligent catapult system according to claim 1, characterized in that: The flight control module (11) further comprises an aileron servo module (19), a flap servo module (20), an elevator servo module (21), a rudder servo module (22) and a motor module (23).

4. The fixed-wing aircraft intelligent catapult system according to claim 1, characterized in that: The ejector body (3) is provided with a switch (24) for controlling the ejector to unhook (5).

5. The fixed-wing aircraft intelligent catapult system according to claim 1, characterized in that: An obliquely arranged arc frame (25) is provided on the top of the catapult main body (3) and on both sides of the catapult unhooking (5), and a roller (26) is provided on the top of the arc frame (25).

6. The fixed-wing aircraft intelligent catapult system according to claim 1, characterized in that: The remote controller (14) is communicatively connected to the catapult body (3) via a wired signal line.

7. The fixed-wing aircraft intelligent catapult system according to claim 1, characterized in that: The ejector unhooking (5) ejects the aircraft (2) through an ejection energy storage system.

8. The fixed-wing aircraft intelligent catapult system according to claim 7, characterized in that: The ejection energy storage system includes but is not limited to one of a spring, a rubber band, an air pressure tank, and an electromagnetic force energy storage method.

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