Uncovering, unlocking and catapulting integrated system and catapulting method thereof

Abstract

The invention provides an uncovering, unlocking and catapulting integrated system and a catapulting method thereof. The uncovering, unlocking and catapulting integrated system comprises an aircraft flying-out cylinder. An aircraft is installed in the aircraft flying-out cylinder and locked through a first locking bolt and a second locking bolt, a main fuel gas generator is installed at the bottom of the aircraft and installed in the aircraft flying-out cylinder, a fragile cover is installed at the top of the aircraft flying-out cylinder, and an auxiliary fuel gas generator is arranged in the fragile cover. According to the fuel gas bottom-pushing catapulting device, a launching cylinder uncovering system, a locking bolt unlocking system and a fuel gas bottom-pushing catapulting system are designed in an integrated mode, the automatic feedback signal auxiliary fuel gas generator and the automatic unlocking feedback signal locking mechanism are adopted, the systems are designed in an integrated mode and associated, and the automatic feedback signal auxiliary fuel gas generator and the automatic unlocking feedback signal locking mechanism are integrated. And all actions are ensured to act orderly according to a designed time sequence, stable and reliable work of the system is realized, and reliable ejection of the aircraft out of the cylinder is ensured.

Description

Technical Field

[0001] The invention relates to a cover opening, unlocking and ejecting integrated system and an ejecting method thereof. Background Art

[0002] As an important component of the launch tube, the cover-opening ejection system provides power for opening the cover of the launch tube, unlocking the aircraft, and ejecting. Its main function is to reliably open the front cover of the launch tube during the movement of the aircraft out of the tube, clear the movement channel of the aircraft, reliably unlock the aircraft, and continuously generate gas power to eject the aircraft out of the tube. In recent years, after continuous development, the design requirements of the launch tube have become more and more stringent, and it has been continuously developed in the direction of diversified launch methods, lightweight structure, high reliability, and rapid response. For example, a launch tube rear cover structure and installation and use method disclosed in CN112161520A uses the engine gas flow as the power source for breaking the fragile cover, without the need for additional power, and has the advantages of simple structure, low cost, and high reliability. However, it does not associate the breaking of the fragile cover, launch unlocking, and ignition as an integrated system, so that it cannot ensure the orderly movement of each component during the launch process, and the launch reliability is reduced. Summary of the invention

[0003] In order to solve the above technical problems, the present invention provides an integrated cover opening, unlocking and ejecting system and an ejection method thereof.

[0004] The present invention is achieved through the following technical solutions.

[0005] The present invention provides an integrated system for opening a cover, unlocking and ejecting, comprising an aircraft ejection tube; an aircraft is installed in the aircraft ejection tube and is locked by a first locking bolt and a second locking bolt; a main gas generator is installed in the aircraft ejection tube at the bottom of the aircraft; a fragile cover is installed on the top of the aircraft ejection tube, and an auxiliary gas generator is arranged in the fragile cover; the auxiliary gas generator and the main gas generator are connected in parallel to a controller; a micro-trigger switch, a first micro-switch and a second micro-switch are connected in sequence between the controller and the main gas generator; the first micro-switch and the second micro-switch are triggered by the first locking bolt and the second locking bolt respectively; the first locking bolt and the second locking bolt are connected in sequence between the micro-trigger switch and the first micro-switch.

[0006] Signals are transmitted between the controller, the fragile cover and the main gas generator via a cable network.

[0007] An ignition switch is installed on the output end of the controller.

[0008] The opening pressure of the frangible cover is lower than the lowest pressure value generated by the auxiliary gas generator.

[0009] The first locking bolt and the second locking bolt are detonating bolts.

[0010] A method for ejecting a cover-opening, unlocking and ejecting integrated system, the steps of which are:

[0011] S1, start;

[0012] S2, the controller sends an ignition signal;

[0013] S3. The heat generated by the combustion of the auxiliary gas generator breaks the fragile cover;

[0014] S4, the heat generated by the combustion of the auxiliary gas generator triggers the micro-trigger switch to close;

[0015] S5, after the micro-trigger switch is closed, the first locking bolt and the second locking bolt are detonated to separate the aircraft from the aircraft flight tube;

[0016] S6, during the detonation process of the first locking bolt and the second locking bolt, the first micro switch and the second micro switch are triggered to close in sequence;

[0017] S7. The main gas generator receives an ignition signal to ignite the gas to generate pressure to eject the aircraft out of the aircraft ejection tube.

[0018] The auxiliary gas generator can automatically feed back an ignition signal, and can feed back the working state of the auxiliary gas generator to the controller.

[0019] The first locking bolt and the second locking bolt can also feed back an unlocking signal to the controller.

[0020] The beneficial effects of the present invention are as follows: the launch tube cover opening, locking bolt unlocking, and gas bottom push ejection system are integrated into an integrated design, an automatic feedback signal auxiliary gas generator and an automatic unlocking feedback signal locking mechanism are adopted, the system is integrated and associated, and each action is ensured to be performed in an orderly manner according to the designed timing, thereby achieving stable and reliable operation of the system and ensuring that the aircraft is reliably ejected from the tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the system principle of the present invention;

[0022] In the figure: 1- auxiliary gas generator, 2- fragile cover, 3- second locking bolt, 4- main gas generator, 5- cable network, 6- first locking bolt, 7- aircraft flies out of the tube, 8- first micro switch, 9- second micro switch, 10- micro trigger switch. DETAILED DESCRIPTION

[0023] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0024] In order to adapt to the development direction of bottom-push ejection launch tubes, the present invention provides an integrated system for opening the cover, unlocking and ejecting. The system designs an opening, unlocking and ejecting system that can respond quickly and actively. It uses a gas generator that automatically feedbacks signals and a locking mechanism that automatically acts and feedbacks unlocking signals. Compared with traditional opening, unlocking and ejecting systems, it can effectively improve the system's working response time and improve the system's working reliability and safety. At the same time, the system structure is simple and compact in design. The system is controlled in an orderly manner through the system's own components, which reduces a large number of control elements, effectively reduces system costs, and improves reliability. The integrated system for opening the cover, unlocking and ejecting realizes a simplified integrated design of the timing control mechanism and the launch tube, meeting the requirements of lightweight, miniaturized, universal, high reliability, and low-cost equipment.

[0025] The present invention discloses an integrated system for opening a cover, unlocking and ejecting, comprising an aircraft ejection tube 7; an aircraft is installed in the aircraft ejection tube 7 and is locked by a first locking bolt 6 and a second locking bolt 3; a main gas generator 4 is installed in the aircraft ejection tube 7 at the bottom of the aircraft; a fragile cover 2 is installed on the top of the aircraft ejection tube 7; an auxiliary gas generator 1 is arranged in the fragile cover 2; the auxiliary gas generator 1 and the main gas generator 4 are connected in parallel to a controller; a micro-trigger switch 10, a first micro-switch 8 and a second micro-switch 9 are connected in sequence between the controller and the main gas generator 4; the first micro-switch 8 and the second micro-switch 9 are triggered by the first locking bolt 6 and the second locking bolt 3 respectively; the first locking bolt 6 and the second locking bolt 3 are connected in sequence between the micro-trigger switch 10 and the first micro-switch 8.

[0026] Signals are transmitted between the controller, the fragile cover 2 and the main gas generator 4 via a cable network 5 .

[0027] An ignition switch is installed on the output end of the controller.

[0028] Since the pressure for opening the fragile cover 2 requires the auxiliary gas generator 1 to generate sufficient pressure in a certain volume chamber instantaneously, and the influence of high and low temperature conditions on pressure changes is considered, the opening pressure of the fragile cover 2 is lower than the minimum pressure value generated by the auxiliary gas generator 1.

[0029] The first locking bolt 6 and the second locking bolt 3 are detonating bolts.

[0030] like Figure 1As shown, the signal transmission between the cover unlocking ejection integrated system and the external system is carried out through the cable network. After the ignition command is issued, the power supply of the external system is connected to the auxiliary gas generator to ignite the auxiliary gas generator. The combustion of the auxiliary gas generator generates gas that acts on the fragile cover of the cylinder to open the fragile cover. At the same time, the generated gas automatically closes the micro switch through the trigger mechanism, so that the ignition circuit of the locking mechanism is connected, and the ignition signal is transmitted to the two parallel locking mechanisms at the same time. The locking bolts in the locking mechanism are detonated and disconnected along the designed separation position to complete the unlocking of the aircraft. The separated locking bolts can automatically trigger the micro switch of the locking mechanism, so that the ignition circuit of the main gas generator is connected. The ignition signal of the external system is finally transmitted to the main gas generator to ignite it. The main gas generator generates gas pressure to push the aircraft out of the cylinder. The auxiliary gas generator adopts a gas generator that can automatically feedback the ignition signal, which can reliably feedback the working signal of the auxiliary gas generator to the system, ensuring the reliable opening of the fragile cover and improving the safety of the system operation. The locking mechanism adopts a locking mechanism that can automatically feedback the unlocking signal, ensuring that the aircraft has been reliably unlocked before the main gas generator is actuated, which can not only meet the needs of rapid response, but also ensure the safety of the aircraft's movement out of the tube. The integrated system of opening the cover, unlocking and ejecting cleverly integrates the launch tube cover opening, aircraft unlocking and ejection system. In the middle, an auxiliary gas generator that can actively open the cover and an active unlocking locking mechanism are used. The system signal transmission is associated through an automatic triggering mechanism to ensure that each action is orderly in accordance with the designed timing, so as to achieve stable and reliable operation of the system and ensure the reliability and safety of the aircraft's exit process. The opening pressure of the fragile cover is designed to match the pressure generated by the auxiliary gas generator in a certain volume cavity. At the same time, the influence of high and low temperature conditions on pressure changes is considered to ensure that the opening index of the fragile cover can be lower than the minimum pressure value generated by the auxiliary gas generator. The locking mechanism adopts two sets of locking bolts in parallel and the automatic triggering feedback mechanism in series, which not only ensures the redundant design of the aircraft locking, but also ensures that the locking is more stable, and ensures that the main gas generator ignition circuit is connected only after the aircraft is reliably unlocked. The integrated system of opening, unlocking and ejecting reacts quickly, and the process of opening, unlocking and ejecting is in milliseconds, which effectively improves the performance of the system. The integrated system of opening, unlocking and ejecting uses active gas power to achieve action, which effectively simplifies the system design and reduces the load requirements on the aircraft.

[0031] A method for ejecting a cover-opening, unlocking and ejecting integrated system, the steps of which are:

[0032] S1, start;

[0033] S2, the controller sends an ignition signal;

[0034] S3, the heat generated by the combustion of the auxiliary gas generator 1 breaks the fragile cover 2;

[0035] S4, the heat generated by the combustion of the auxiliary gas generator 1 triggers the micro-trigger switch 10 to close;

[0036] S5, after the micro-trigger switch 10 is closed, the first locking bolt 6 and the second locking bolt 3 are detonated to separate the aircraft from the aircraft flight tube 7;

[0037] S6, the first locking bolt 6 and the second locking bolt 3 trigger the first micro switch 8 and the second micro switch 9 to close in sequence during the detonation process;

[0038] S7, the main gas generator 4 receives the ignition signal to ignite the gas to generate pressure to eject the aircraft out of the aircraft flight tube 7.

[0039] The auxiliary gas generator 1 can automatically feed back an ignition signal, and can feed back the working state of the auxiliary gas generator 1 to the controller, thereby ensuring the reliable opening of the fragile cover 2 and improving the safety of the system operation.

[0040] The first locking bolt 6 and the second locking bolt 3 can also feed back an unlocking signal to the controller. The auxiliary gas generator 1 that can actively open the cover and the locking mechanism that can actively unlock formed by the first locking bolt 6 and the second locking bolt 3, are linked to the system signal transmission through the automatic trigger mechanism to ensure that each action is carried out in an orderly manner according to the designed timing, so as to achieve stable and reliable operation of the system and ensure the reliability and safety of the aircraft's tube-out process. The locking mechanism adopts the form of two sets of locking bolts in parallel and the automatic trigger feedback mechanism in series, which not only ensures the redundant design of the aircraft locking, but also ensures that the locking is more stable, and the main gas generator ignition circuit is connected only after the aircraft is reliably unlocked.

Claims

1. An integrated system for opening a cover, unlocking and ejecting, comprising an aircraft ejection tube (7), characterized in that: An aircraft is installed in the aircraft flight tube (7) and is locked by a first locking bolt (6) and a second locking bolt (3). A main gas generator (4) is installed in the aircraft flight tube (7) at the bottom of the aircraft. A fragile cover (2) is installed on the top of the aircraft flight tube (7). An auxiliary gas generator (1) is arranged in the fragile cover (2). The auxiliary gas generator (1) and the main gas generator (4) are connected in parallel to a controller. A micro-trigger switch (10), a first micro-switch (8), and a second micro-switch (9) are connected in sequence between the controller and the main gas generator (4). The first micro-switch (8) and the second micro-switch (9) are triggered by the first locking bolt (6) and the second locking bolt (3) respectively. The first locking bolt (6) and the second locking bolt (3) are connected in sequence between the micro-trigger switch (10) and the first micro-switch (8).

2. The cover opening, unlocking and ejection integrated system according to claim 1, characterized in that: Signals are transmitted between the controller, the fragile cover (2) and the main gas generator (4) via a cable network (5).

3. The cover opening, unlocking and ejection integrated system according to claim 1, characterized in that: An ignition switch is installed on the output end of the controller.

4. The cover opening, unlocking and ejection integrated system according to claim 1, characterized in that: The opening pressure of the frangible cover (2) is lower than the lowest pressure value generated by the auxiliary gas generator (1).

5. The cover opening, unlocking and ejection integrated system according to claim 1, characterized in that: The first locking bolt (6) and the second locking bolt (3) are detonating bolts.

6. The ejection method of the cover opening, unlocking and ejection integrated system according to any one of claims 1 to 5, wherein the steps are as follows: S1, start; S2, the controller sends an ignition signal; S3, the heat generated by the combustion of the auxiliary gas generator (1) breaks the fragile cover (2); S4, the heat generated by the combustion of the auxiliary gas generator (1) triggers the micro-trigger switch (10) to close; S5, after the micro-trigger switch (10) is closed, the first locking bolt (6) and the second locking bolt (3) are detonated to separate the aircraft from the aircraft flight tube (7); S6, during the detonation process, the first locking bolt (6) and the second locking bolt (3) trigger the first micro switch (8) and the second micro switch (9) to close in sequence; S7, the main gas generator (4) receives the ignition signal to ignite the gas to generate pressure to eject the aircraft out of the aircraft ejection tube (7).

7. The ejection method of the cover opening, unlocking and ejection integrated system according to claim 1, characterized in that: The auxiliary gas generator (1) can automatically feed back an ignition signal, and can feed back the working state of the auxiliary gas generator (1) to the controller.

8. The ejection method of the cover opening, unlocking and ejection integrated system according to claim 1, characterized in that: The first locking bolt (6) and the second locking bolt (3) can also feed back an unlocking signal to the controller.

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