A fixed-wing aircraft intelligent catapult system

Abstract

The utility model discloses a fixed wing aircraft intelligence catapult system, including ejector assembly, aircraft and control system, the ejector assembly includes ejector main part, one end swing joint of ejector main part has the support frame, and the top of ejector main part is equipped with ejector unhooking, and the bottom of aircraft is equipped with the hook of with ejector unhooking adapts, control system includes aircraft module, ejector module and remote control module, and aircraft module includes radio frequency module no.

Description

Technical Field

[0001] Specifically, this utility model relates to an intelligent catapult system for fixed-wing aircraft. Background Technology

[0002] Existing industrial or military fixed-wing aircraft catapults primarily achieve short-distance, high-speed catapult takeoffs of fixed-wing aircraft through mechanical energy storage or powered traction, with the core challenge being runway-less takeoff. Currently, the mainstream spring-energy storage catapult system (a mainstream low-cost solution) stores elastic potential energy in a spring (tension or torsion spring) by stretching it with a motor or manual winch. For example, a tension spring-powered system connects the spring to the UAV trolley via a steel cable. A motor drives a screw to pull the traction hook, stretching the spring to a preset position. After the trigger mechanism (such as an electromagnetic or mechanical lock) unlocks, the spring instantly rebounds, pulling the trolley along a steel guide rail via a pulley system and steel cable. The UAV, propelled by the trolley, reaches takeoff speed (typically 15-25 m / s) and then detaches from the trolley to ascend. The trolley then strikes a buffer at the end of the steel guide rail to decelerate and stop. However, due to the large amount of energy required (the kinetic energy required for a 2kg drone to take off at an initial velocity 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) is mostly made of 65Mn spring steel, weighing more than 3kg. In addition to the steel guide rail, trolley, and steel frame, the total system weight is usually 8-10kg, and the length is about 2m, making it very inconvenient to carry.

[0003] No effective solutions have yet been proposed to address the problems in the relevant technologies. Utility Model Content

[0004] In view of the problems in the related technologies, this utility model proposes an intelligent catapult system for fixed-wing aircraft to overcome the above-mentioned technical problems existing in the existing related technologies.

[0005] Therefore, the specific technical solution adopted by this utility model is as follows:

[0006] A smart catapult system for a fixed-wing aircraft includes 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, the top of which is provided with an ejector release hook, and the bottom of the aircraft is provided with a hook adapted to the ejector release hook.

[0008] The control system includes an aircraft module, a catapult module, and a remote control module. The aircraft module includes a radio frequency module and a flight control module.

[0009] The catapult module includes a servo motor and a battery for driving the catapult to disengage;

[0010] The remote control module includes a remote controller, a 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, the catapult body is provided with a switch for controlling the catapult to disengage.

[0014] Preferably, the top of the catapult body and the two sides of the catapult release hook are provided with inclined arc-shaped frames, and the top of the arc-shaped frames are provided with rollers.

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

[0016] Preferably, the catapult releases the aircraft via an energy storage system.

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

[0018] The beneficial effects of this utility model are as follows: Consumers can place the catapult anywhere outdoors on uneven ground. When installing on uneven ground, the angle of the fixed-wing aircraft on the catapult may not be ideal. However, by adjusting the angles of the aileron servo module, flap servo module, elevator servo module, and rudder servo module, as well as the speed of the motor module, the aircraft can be placed in the optimal catapult state. The elevator / flaps / alilerons are adjusted proportionally in real time by the servo. The attitude information of the aircraft, mainly the angle information between the aircraft and the ground, is sensed by sensors such as gyroscopes and ground-to-ground optical flow sensors, which can determine the angle of attack of the wing.

[0019] Before ejection, the aircraft's power system can be activated, i.e., the motor drives the propeller to rotate and provide thrust. In this state, the ejection distance can be reduced and the power output of the energy storage system can be reduced.

[0020] Rollers are used to support the balance of the aircraft's main wing. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

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

[0023] Figure 2 This is a schematic diagram of the takeoff state in an intelligent catapult system for a fixed-wing aircraft according to an embodiment of the present utility model;

[0024] Figure 3 This is a schematic diagram of a smart catapult system for a fixed-wing aircraft according to an embodiment of the present utility model.

[0025] In the picture:

[0026] 1. Catapult assembly; 2. Aircraft; 3. Catapult body; 4. Support frame; 5. Catapult release hook; 6. Hook; 7. Aircraft module; 8. Catapult module; 9. Remote control module; 10. Radio frequency module one; 11. Flight control module; 12. Servo; 13. Battery; 14. Remote controller; 15. Radio frequency module two; 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. Curved frame; 26. Roller. Detailed Implementation

[0027] To further illustrate the various embodiments, the present invention provides accompanying drawings, which are part of the disclosure of the present invention. These drawings 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. With reference to these contents, those skilled in the art should be able to understand other possible implementation methods and the advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are usually used to represent similar components.

[0028] According to an embodiment of the present invention, an intelligent catapult system for fixed-wing aircraft 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 ejector body 3, one end of which is movably connected to a support frame 4, the top of which is provided with an ejector release hook 5, and the bottom of the aircraft 2 is provided with a hook 6 that is adapted to the ejector release hook 5.

[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 servo motor 12 and a battery 13 for driving the catapult release hook 5.

[0034] The remote control module 9 includes a remote controller 14, a radio frequency module 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 also 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 catapult body 3 is provided with a switch 24 for controlling the catapult unhooking 5.

[0039] Example 3:

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

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

[0042] The catapult release 5 launches the aircraft 2 through the catapult's energy storage system.

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

[0044] This system eliminates the spring energy storage system, employing a brushless motor to directly drive (or via gear reduction) a rigid chain that propels the trolley. The brushless motor's electronic driver has a braking function, controlling the trolley to brake as it approaches the end, rapidly reducing impact on the buffer and outer frame, and potentially eliminating the buffer altogether. A sensor (either photoelectric or pressure sensor) is installed near the end of the guide rail; when the trolley reaches this position, the sensor signals the electronic driver, which then brakes the motor. Low cost, lightweight, and portable. Because the energy storage system is eliminated and the braking function minimizes impact on the outer frame, the strength requirements of this catapult system are greatly reduced, allowing the use of aluminum components or even high-strength engineering plastics, resulting in low cost and lightweight design. The weight can be kept below 3kg. This catapult is foldable, with a folded length of less than 1m, allowing it to be stored horizontally in a car trunk. There is no built-in power supply. To improve reliability and reduce user charging inconvenience, this catapult is powered by the aircraft's batteries. Users can directly insert one or more aircraft batteries into the power supply slot to power the system. The launcher offers multiple triggering methods. It can be triggered via the built-in electronic button on the launcher itself, or via a wired connection to a smart remote control. It is also highly expandable, with multiple connection ports at the rear for attaching various accessories such as cup holders, phone holders, and umbrella stands, optimizing the outdoor user experience. The launch angle is adjustable. The two front support legs can be manually adjusted in length, and a level ensures the launch system is level.

[0045] To facilitate understanding of the above-mentioned technical solutions of this utility model, the working principle or operation method of this utility model in actual process will be described in detail below.

[0046] In practical applications, 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-button ejection mode lever (or button). After the remote controller 14 sends an ejection signal, the ejector release hook 5 ejects the aircraft 2 through the ejection energy storage system. Before ejection, the power system of the aircraft 2 can be turned on, i.e., the motor drives the propeller to rotate to provide thrust. In this state, the ejection 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. The angles of the aileron servo module 19, flap servo module 20, elevator servo module 21, and rudder servo module 22, as well as the speed of the motor module 23, are adjusted by the servo to put the aircraft 2 in the optimal ejection state. The elevator / flaps / alilerons 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 sensors, which can determine the angle of attack of the wings.

[0047] In summary, with the help of the above-mentioned technical solution of this utility model, consumers can place the catapult anywhere outdoors on uneven ground. When installed on uneven ground, the angle of the fixed-wing aircraft on the catapult may not be ideal. However, by adjusting the angles of the aileron servo module 19, flap servo module 20, elevator servo module 21, and rudder servo module 22, as well as the rotation speed of the motor module 23, the aircraft 2 can be placed in the optimal catapult state. The elevator / flaps / alilerons are adjusted proportionally in real time by the servo motors. The attitude information of the aircraft 2 mainly refers to the angle information between the aircraft and the ground, which is sensed by sensors such as gyroscopes and ground-to-ground optical flow sensors, and the angle of attack of the wings can be determined. Before catapult launch, the power system of the aircraft 2 can be turned on, that is, the motor drives the propeller to rotate to provide thrust. 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 utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

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

2. The intelligent catapult system for a fixed-wing aircraft 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 intelligent catapult system for a fixed-wing aircraft according to claim 1, characterized in that, The flight control module (11) also 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).

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

5. The intelligent catapult system for a fixed-wing aircraft according to claim 1, characterized in that, An inclined arc-shaped frame (25) is provided on the top of the catapult body (3) and on both sides of the catapult release hook (5), and a roller (26) is provided on the top of the arc-shaped frame (25).

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

7. The intelligent catapult system for a fixed-wing aircraft according to claim 1, characterized in that, The catapult release (5) ejects the aircraft (2) through the catapult's energy storage system.

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

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