Impact buffering structure and brake control method of launch canister ejection device

Abstract

The invention provides an impact buffering structure of a launch canister ejection device, which realizes efficient buffering braking of the ejection device after an unmanned aerial vehicle is launched, reduces impact force in a braking process and improves braking safety of the ejection device based on elastic-plastic deformation of a thin-wall expansion ring structure and a friction energy absorption principle. Comprising a buffer cylinder, a main cylinder and an ejection device, a guide groove is formed in the rear end of the buffer cylinder, and a guide cone is arranged at the front end of the ejection device. The relationship among the inner diameter A of the buffer cylinder, the outer diameter B of the aircraft and the outer diameter C of the ejection device is that B < A < C. By changing the structural size between the outer diameter C of the ejection device and the inner diameter A of the buffer cylinder, the magnitude of interference between the ejection device and the buffer cylinder can be efficiently adjusted, and rapid adjustment of the buffer efficiency and efficient conversion application in different products are achieved. And the product development efficiency is improved. The device has the technical advantages of being simple in structure, small in axial impact force in the buffering process, high in safety, high in transportability and the like.

Description

Technical Field

[0001] The present invention belongs to the technical field of buffering and braking of unmanned aerial vehicle launch systems, and in particular, relates to an impact buffering structure and a braking control method of a launch tube ejection device. Background Art

[0002] The buffering and braking structure is an important component of the launch tube. When launching an unmanned aerial vehicle, it is necessary to perform high-reliability and high-safety buffering and braking of the ejection device to achieve safe launch and separation of the aircraft. A survey of domestic related buffering and braking technologies for ejection devices was conducted. Patent document with publication number CN116336866A discloses a curling buffer, which achieves buffering and braking by plastically curling its two legs when subjected to external force. Patent document with publication number CN116907273A discloses an embedded baffle buffer. When the movable base hits the buffer, it absorbs energy through plastic deformation through the multiple baffles provided on the buffer, achieving buffering and braking of the movable base.

[0003] While the aforementioned buffers can achieve buffered braking for the ejection device, they all achieve this by directly impacting the ejection device axially and then utilizing their own elastic-plastic deformation. This results in significant braking impact forces, posing a safety hazard to the launch and separation of the aircraft. Therefore, developing a novel impact buffer structure for the launch tube ejection device is of great significance. Summary of the Invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a launch tube ejection device impact buffer structure and a braking control method.

[0005] According to the present invention, a launch tube ejection device impact buffer structure is provided, comprising: a buffer tube 1, a main tube body 2 and an ejection device 4; the buffer tube 1 and the main tube body 2 are connected as a whole by fasteners and fixed as a whole in the launch device; the ejection device 4 is located at the rear end inside the main tube body 2 and is coaxially arranged with the main tube body 2; an aircraft 3 is installed in the buffer tube 1 and the main tube body 2, and the rear end surface of the aircraft 3 is in contact with the ejection device 4.

[0006] Preferably, the buffer tube 1 is a thin-walled expansion ring structure. The relationship between the inner diameter A of the buffer tube 1 and the outer diameter C of the ejection device 4 is A<C; when the ejection device 4 performs buffer braking, an interference fit is formed with the buffer tube 1.

[0007] Preferably, the rear end of the buffer tube 1 is provided with a guide groove 101; the front end of the ejection device 4 is provided with a guide cone 401; after the guide groove 101 contacts and cooperates with the guide cone 401, the ejection device 4 can axially stably enter the buffer tube 1 and implement buffer braking.

[0008] Preferably, during the buffer braking process, the axial impact force of the ejection device 4 is converted into radial elastic-plastic deformation energy and friction energy of the buffer cylinder 1 through the interference fit between the ejection device 4 and the buffer cylinder 1, thereby effectively reducing the axial impact force during the braking process.

[0009] Preferably, the relationship between the outer diameter B of the aircraft 3 and the inner diameter A of the buffer tube 1 is B<A, ensuring that the aircraft 3 can be placed in the buffer tube 1.

[0010] Preferably, the interference between the inner diameter A of the buffer cylinder 1 and the outer diameter C of the ejection device 4 can be adjusted according to the ejection index requirements of the aircraft 3. The direction in which the ejection device 4 approaches the buffer cylinder 1 is the heading.

[0011] Preferably, when the aircraft 3 is launched, the pyrotechnic power source of the ejection device 4 is ignited to generate gas, and the pressure of the gas in the sealed cavity formed between the ejection device 4 and the main cylinder 2 increases rapidly. Under the action of the high-pressure gas, the ejection device 4 moves forward, thereby pushing the aircraft 3 forward to implement the launch.

[0012] According to the invention, a braking control method for an impact buffer structure of a launch tube ejection device includes the following steps:

[0013] Step 1: Install the ejection device 4 inside the rear end of the main cylinder 2, then connect the buffer cylinder 1 and the main cylinder 2 together with fasteners and fix them as a whole in the launch device, then load the aircraft 3 into the buffer cylinder 1 and the main cylinder 2, and push them backward until the rear end of the aircraft 3 is in contact with the front end of the ejection device 4;

[0014] Step 2: When the aircraft 3 is launched, according to the system launch command, the pyrotechnic power source of the ejection device 4 ignites to generate gas. The pressure of the gas in the sealed cavity formed between the ejection device 4 and the main cylinder 2 increases rapidly. Under the action of the high-pressure gas, the ejection device 4 moves forward, thereby pushing the aircraft 3 forward to launch;

[0015] Step 3: After the ejection device 4 and the aircraft 3 have moved a certain distance, the guide cone 401 at the front end of the ejection device 4 contacts the guide groove 101 at the rear end of the buffer tube 1. The outer diameter C of the ejection device 4 is larger than the inner diameter A of the buffer tube 1, and the ejection device 4 and the buffer tube 1 form an interference fit. Under the action of the guide cone 401 and the guide groove 101, the ejection device 4 can more easily enter the buffer tube 1 and apply braking;

[0016] Step 4: After the ejection device 4 contacts the buffer tube 1, due to the interference fit structure, the ejection device 4 and the buffer tube 1 begin to be radially squeezed, and the buffer tube 1 produces elastic-plastic expansion deformation in the radial direction. Then the ejection device 4 begins to decelerate, and then the aircraft 3 separates from the ejection device 4 and is safely launched from the tube at the designed speed.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. Based on the elastic-plastic deformation and frictional energy absorption principles of a thin-walled expansion ring structure, this invention achieves efficient buffering and braking of the ejection device after launch, reducing the impact force during the braking process and improving the safety of the ejection device. This effectively addresses the high impact force during the buffering and braking process of conventional launch tube ejection devices, effectively reducing the safety risks associated with the buffering and braking process. Multiple launch tests have confirmed the effectiveness of this buffering structure, achieving low-impact, high-safety buffering and braking of the ejection device.

[0019] 2. The present invention effectively realizes the ejection device with low impact buffer braking, converts the axial impact force of the ejection device into friction energy between the ejection device and the buffer cylinder and the radial elastic-plastic deformation energy of the buffer cylinder, thereby improving the buffer braking efficiency and the safety of the buffer braking process, and reducing the axial impact force of the buffer braking.

[0020] 3. The present invention boasts a simple structure and strong portability. Fasteners connect the various components, making final assembly easy. Furthermore, portability is relatively simple for aircraft launch tubes. By simply adjusting the structural dimensions between the outer diameter of the ejection device and the inner diameter of the buffer tube according to the ejection specifications of different aircraft, the interference fit between the ejection device and the buffer tube can be efficiently adjusted to meet the new ejection buffer braking requirements. This allows for rapid adjustment of buffering performance and efficient application in different products, improving product development efficiency and overall cost, while maintaining high reliability.

[0021] 4. The present invention improves the safety and reliability of the ejection device's safety brake by providing guide grooves and guide cones. The present invention has been verified in multiple launch tests, confirming that the buffer structure meets design and use requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0023] Figure 1 This is a schematic diagram of the overall structure of the present invention before launch;

[0024] Figure 2 It is a schematic diagram of the structure when the ejection device contacts the buffer tube during the launch process;

[0025] Figure 3 It is a partial enlarged structural diagram of the ejection device and the buffer tube during the launch process;

[0026] Figure 4This is a schematic diagram of the structure of the ejection device buffering and braking state during the launch process;

[0027] Figure 5 This is a schematic diagram of the partially enlarged structure of the buffer braking state of the ejection device during the launch process.

[0028] The figure shows:

[0029] DETAILED DESCRIPTION

[0030] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0031] like Figures 1 to 5 As shown, the present invention is installed within a launcher and includes a buffer tube 1, a main cylinder 2, and an ejection device 4. The buffer tube 1 and main cylinder 2 are connected as a whole by fasteners and fixed as a whole within the launcher; a guide groove 101 is provided at the rear end of the buffer tube 1; the ejection device 4 is located at the rear end of the main cylinder 2 and is coaxial with the main cylinder 2; a guide cone 401 is provided at the front end of the ejection device 4; the aircraft 3 is installed within the buffer tube 1 and main cylinder 2, with its rear end face in contact with the ejection device 4. The relationship between the inner diameter A of the buffer tube 1, the outer diameter B of the aircraft 3, and the outer diameter C of the ejection device 4 is B<A<C. The arrows in the figure indicate the heading.

[0032] like Figure 1 As shown, the ejection device 4 is installed at the rear end of the main cylinder 2, and then the buffer cylinder 1 and the main cylinder 2 are connected as a whole by fasteners and fixed as a whole in the launching device. Then, the aircraft 3 is loaded into the buffer cylinder 1 and the main cylinder 2, and pushed backward until the rear end face of the aircraft 3 is in contact with the front end face of the ejection device 4.

[0033] like Figure 2 、 Figure 3 As shown, when launching an aircraft 3, according to the system's launch command, the pyrotechnic power source of the ejection device 4 ignites to generate combustion gas. The pressure of the combustion gas rapidly increases within the sealed chamber formed between the ejection device 4 and the main cylinder 2. Under the action of the high-pressure combustion gas, the ejection device 4 moves forward, thereby propelling the aircraft 3 forward and launching it. After the ejection device 4 and the aircraft 3 have moved a certain distance, the guide cone 401 at the front end of the ejection device 4 contacts the guide groove 101 at the rear end of the buffer cylinder 1. The outer diameter C of the ejection device 4 is larger than the inner diameter A of the buffer cylinder 1, forming an interference fit between the ejection device 4 and the buffer cylinder 1. Under the action of the guide cone 401 and the guide groove 101, the ejection device 4 also easily enters the buffer cylinder 1 and applies the brake.

[0034] like Figure 4 、 Figure 5 As shown, after the ejection device 4 contacts the buffer tube 1, due to the interference fit structure, the ejection device 4 and the buffer tube 1 begin to be radially squeezed, and the buffer tube 1 produces elastic-plastic expansion deformation in the radial direction. Then the ejection device 4 begins to decelerate, and then the aircraft 3 separates from the ejection device 4 and is safely launched from the tube at the designed speed.

[0035] The braking control method of the impact buffer structure of the launch tube ejection device comprises the following steps:

[0036] Step 1: Install the ejection device 4 inside the rear end of the main cylinder 2, then connect the buffer cylinder 1 and the main cylinder 2 together with fasteners and fix them as a whole in the launch device, then load the aircraft 3 into the buffer cylinder 1 and the main cylinder 2, and push them backward until the rear end of the aircraft 3 is in contact with the front end of the ejection device 4;

[0037] Step 2: When the aircraft 3 is launched, according to the system launch command, the pyrotechnic power source of the ejection device 4 ignites to generate gas. The pressure of the gas in the sealed cavity formed between the ejection device 4 and the main cylinder 2 increases rapidly. Under the action of the high-pressure gas, the ejection device 4 moves forward, thereby pushing the aircraft 3 forward to launch;

[0038] Step 3: After the ejection device 4 and the aircraft 3 have moved a certain distance, the guide cone 401 at the front end of the ejection device 4 contacts the guide groove 101 at the rear end of the buffer tube 1. The outer diameter C of the ejection device 4 is larger than the inner diameter A of the buffer tube 1, and the ejection device 4 and the buffer tube 1 form an interference fit. Under the action of the guide cone 401 and the guide groove 101, the ejection device 4 can more easily enter the buffer tube 1 and apply braking;

[0039] Step 4: After the ejection device 4 contacts the buffer tube 1, due to the interference fit structure, the ejection device 4 and the buffer tube 1 begin to be radially squeezed, and the buffer tube 1 produces elastic-plastic expansion deformation in the radial direction. Then the ejection device 4 begins to decelerate, and then the aircraft 3 separates from the ejection device 4 and is safely launched from the tube at the designed speed.

[0040] The impact buffer structure of a launch tube ejection device involved in the present invention effectively achieves low-impact buffering and braking of the ejection device 4. The buffer structure converts the axial impact force of the ejection device 4 into friction energy between the ejection device 4 and the buffer tube 1, as well as the radial elastic-plastic deformation energy of the buffer tube 1, thereby improving the buffering and braking efficiency, reducing the axial impact force of the buffering and braking, and improving the safety of the buffering and braking process of the ejection device 4. By changing the structural dimensions between the outer diameter C of the ejection device 4 and the inner diameter A of the buffer tube 1, the interference fit between the ejection device 4 and the buffer tube 1 can be efficiently adjusted, achieving rapid adjustment of the buffering efficiency and efficient conversion and application in different projects, thereby improving product development efficiency. In addition, by providing a guide groove 101 and a guide cone 401, the reliability of the safe braking of the ejection device 4 is improved. The present invention was verified in multiple launch test assessments, confirming that the buffer structure meets the design and use requirements.

[0041] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0042] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A launch tube ejection device impact buffer structure, characterized in that: include: A buffer cylinder (1), a main cylinder (2) and an ejection device (4); The buffer cylinder (1) and the main cylinder (2) are connected as a whole by fasteners and are fixed as a whole in the launching device; the ejection device (4) is located at the rear end of the main cylinder (2) and is coaxially arranged with the main cylinder (2); An aircraft (3) is installed in the buffer cylinder (1) and the main cylinder body (2), and the rear end surface of the aircraft (3) is in contact with the ejection device (4).

2. The impact buffer structure of the launch tube ejection device according to claim 1, characterized in that: The buffer cylinder (1) is a thin-wall expansion ring structure.

3. The impact buffer structure of the launch tube ejection device according to claim 1, characterized in that: The relationship between the inner diameter A of the buffer cylinder (1) and the outer diameter C of the ejection device (4) is A<C; when the ejection device (4) performs buffering braking, an interference fit is formed with the buffer cylinder (1).

4. The impact buffer structure of the launch tube ejection device according to claim 1, characterized in that: The rear end of the buffer cylinder (1) is provided with a guide groove (101); the front end of the ejection device (4) is provided with a guide cone (401); After the guide groove (101) and the guide cone (401) are in contact and fit, the ejection device (4) can be axially and stably entered into the buffer cylinder (1) and buffer braking can be implemented.

5. The impact buffer structure of the launch tube ejection device according to claim 2, characterized in that: During the buffer braking process, the axial impact force of the ejection device (4) is converted into radial elastic-plastic deformation energy and friction energy consumption of the buffer cylinder (1) through the interference fit between the ejection device (4) and the buffer cylinder (1), thereby effectively reducing the axial impact force during the braking process.

6. The impact buffer structure of the launch tube ejection device according to claim 1, characterized in that: The relationship between the outer diameter B of the aircraft (3) and the inner diameter A of the buffer cylinder (1) is B<A, ensuring that the aircraft (3) can be placed in the buffer cylinder (1).

7. The impact buffer structure of the launch tube ejection device according to claim 3, characterized in that: The interference between the inner diameter A of the buffer cylinder (1) and the outer diameter C of the ejection device (4) can be adjusted according to the ejection index requirements of the aircraft (3).

8. The impact buffer structure of the launch tube ejection device according to claim 1, characterized in that: The direction in which the ejection device (4) approaches the buffer cylinder (1) is the heading.

9. The impact buffer structure of the launch tube ejection device according to claim 1, characterized in that: When the aircraft (3) is launched, the pyrotechnic power source of the ejection device (4) is ignited to generate combustion gas, and the pressure of the combustion gas in the sealed cavity formed between the ejection device (4) and the main cylinder (2) increases rapidly. Under the action of the high-pressure combustion gas, the ejection device (4) moves forward, thereby pushing the aircraft (3) forward to launch.

10. A braking control method for an impact buffer structure of a launch tube ejection device, characterized in that: The steps include: Step 1: Install the ejection device (4) inside the rear end of the main cylinder (2), then connect the buffer cylinder (1) and the main cylinder (2) together through fasteners and fix the entirety in the launch device, then load the aircraft (3) into the buffer cylinder (1) and the main cylinder (2), and push them backward until the rear end of the aircraft (3) is in contact with the front end of the ejection device (4); Step 2: When the aircraft (3) is launched, according to the system launch command, the pyrotechnic power source of the ejection device (4) is ignited to generate gas, and the pressure of the gas in the sealed cavity formed between the ejection device (4) and the main cylinder (2) increases rapidly. Under the action of the high-pressure gas, the ejection device (4) moves forward, thereby pushing the aircraft (3) forward to launch; Step 3: After the ejection device (4) and the aircraft (3) move a certain distance, the guide cone (401) at the front end of the ejection device (4) contacts the guide groove (101) at the rear end of the buffer cylinder (1). The outer diameter C of the ejection device (4) is larger than the inner diameter A of the buffer cylinder (1). The ejection device (4) and the buffer cylinder (1) form an interference fit. Under the action of the guide cone (401) and the guide groove (101), the ejection device (4) is also easier to enter the buffer cylinder (1) and implement braking. Step 4: After the ejection device (4) contacts the buffer cylinder (1), due to the interference fit structure, the ejection device (4) and the buffer cylinder (1) begin to be radially squeezed, and the buffer cylinder (1) produces elastic-plastic expansion deformation in the radial direction. Then the ejection device (4) begins to decelerate, and then the aircraft (3) is separated from the ejection device (4) and is safely launched from the cylinder at the designed speed.

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