A multifunctional rocket based on a rocket ejection seat

Abstract

The present invention provides a multifunctional rocket based on a rocket ejection seat, comprising a combined life-saving rocket and a long tail nozzle assembly, wherein the long tail nozzle assembly is arranged beside the combined life-saving rocket and is fixedly connected to the long tail nozzle assembly, and the long tail nozzle assembly comprises an electric detonator, an air bleed joint, a blocking plug and a long tail nozzle, wherein the air bleed joint is an air passage of a three-way structure, one end of which is fixedly connected to the combined life-saving rocket, the blocking plug is placed in the air bleed joint, a gap air passage is left at one end of the long tail nozzle, so that the gas generated in the working combustion chamber of the life-saving rocket can enter, and the other two ends are respectively connected to the long tail nozzle and the electric detonator, when the electric detonator works to generate gas, the gas pushes the blocking plug through the air bleed joint, and moves along the inner cavity of the air bleed joint until it contacts the long tail nozzle, at which time the gas in the combustion chamber is blocked by the blocking plug, and the long tail nozzle stops working. The present invention has a simple structure, a fast response, and a high success rate in life-saving.

Description

Technical Field

[0001] The invention belongs to the technical field of solid rockets and is used for ejection life-saving of a rocket ejection seat, in particular to a multifunctional rocket based on a rocket ejection seat. Background Art

[0002] In the field of aviation life-saving, life-saving rockets provide secondary power for ejection seats to ensure life-saving safety in low-speed and 0-0 ejection. During the ejection of multi-seat aircraft, in order to ensure that the movement between seats does not interfere, the seats are required to be able to change their movement trajectory quickly. Therefore, during multi-seat ejection, life-saving rockets and divergence rockets that meet the overall requirements are often required to provide secondary power and trajectory divergence torque for the seats.

[0003] There are usually two thrust schemes for ejection of multiple seats in the existing ejection seats. One is to use a life-saving rocket and a diverging rocket. The life-saving rocket and the diverging rocket are placed under the seat basin and on the side of the seat respectively. The life-saving rocket provides secondary power for the ejection seat, and the diverging rocket provides lateral diverging torque to achieve seat trajectory divergence. The existing technical problems are that the rocket thrust is fixed, the maintainability is general, and the development cost is high; the other is to use thrust vector control, which is generally installed at the bottom or back of the seat. By adjusting the size and direction of the rocket thrust, the seat height adjustment, attitude control and trajectory divergence can be achieved. However, it needs to be controlled by an electronic control system, which leads to unfavorable factors such as excessive volume and weight of the overall solution, high economic cost, and reduced use and maintainability.

[0004] To sum up, the existing solid rocket technology has technical problems such as fixed thrust, high development cost, heavy weight, and poor maintainability, which affect the success rate of pilots' ejection and rescue. Summary of the invention

[0005] The purpose of the present invention is to provide a multifunctional rocket based on a rocket ejection seat, which can provide the ejection seat with the secondary power required for ejection and life-saving, and can also generate lateral thrust through a long tail nozzle to achieve trajectory divergence of the ejection seat and improve the success rate of pilot ejection and life-saving.

[0006] The technical solution of the present invention is: a multifunctional rocket based on a rocket ejection seat, comprising a combined life-saving rocket with a combustion chamber and a long tail nozzle assembly, the long tail nozzle assembly is arranged next to the combined life-saving rocket, and is fixedly connected to the combustion chamber by screws, the long tail nozzle assembly comprises an electric detonator, an air bleed joint, a blocking plug and a long tail nozzle, the air bleed joint is an air passage with a three-way structure, one end of which is fixedly connected to the combined life-saving rocket, the blocking plug is placed in the air bleed joint, a gap air passage is left at one end of the long tail nozzle, so that the gas generated in the working combustion chamber of the life-saving rocket can enter, and the other two ends are respectively connected to the long tail nozzle and the electric detonator, when the electric detonator works to generate gas, the gas pushes the blocking plug through the gas bleed joint, and moves along the inner cavity of the gas bleed joint until it contacts the long tail nozzle, at which time the gas in the combustion chamber is blocked by the blocking plug, and the long tail nozzle stops working.

[0007] In the above scheme, the life-saving rocket also includes a shear pin and a fastening screw, the blocking plug and the air bleed joint are provided with coaxial through holes, the shear pin is inserted into the through hole and fixed by the fastening screw.

[0008] In the above scheme, the life-saving rocket also includes a support seat, and the long tail nozzle is axially parallel to the life-saving rocket and is fixedly connected through the support seat.

[0009] In the above scheme, the combined life-saving rocket also includes an ignition device, a main charge, a nozzle seat and a nozzle. The ignition device is fixedly connected to the combustion chamber, the main charge is freely loaded into the combustion chamber, the nozzle seat is fixedly connected to the combustion chamber, and the nozzle is fixedly connected to the nozzle seat.

[0010] In the above solution, the blocking plug can move freely in the inner cavity of the air bleed connector.

[0011] In the above solution, the shear pin can move freely in the through hole.

[0012] The beneficial effects created by the present invention are as follows: the present invention sets a long tail nozzle assembly, and combines the long tail nozzle with a life-saving rocket to form a combined life-saving rocket. The long tail nozzle structure can realize the opening and closing of the long tail nozzle through the working on and off of the electric detonator, so that the life-saving rocket can be attitude-controlled. The working on and off of the long tail nozzle is realized by the ignition blocking control of the electric detonator. The structure can not only generate the secondary power required for the ejection seat, but also provide a certain lateral force to provide the seat with sufficient attitude deflection torque, thereby controlling the total impulse of the lateral force and meeting the overall requirements for divergence performance.

[0013] The present invention has a simple structure, good parts processability, and fast response. It combines the main thrust of the life-saving rocket with the lateral thrust, has a functional set of secondary power and lateral force divergence, meets the requirements of integration and generalization of the ejection seat pyrotechnic power system, provides a new power technology solution for the secondary power and attitude control of the rocket ejection seat, and has good economic and social benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The utility model is a schematic diagram of the structure of the combined life-saving rocket created by the present invention.

[0015] Figure 2 It is a schematic diagram of the structure of the long tail nozzle assembly created by the present invention.

[0016] Figure 3 It is a schematic diagram of the cross-sectional structure of the long tail nozzle assembly created by the present invention.

[0017] Among them, 1-ignition device, 2-combustion chamber, 3-main charge, 4-nozzle seat, 5-nozzle and 6-long tail nozzle assembly, 7-electric detonator, 8-bleed air joint, 9-blocking plug, 10-shear pin, 11-fastening screw, 12-long tail nozzle, 13-support seat. DETAILED DESCRIPTION

[0018] The present invention is further described in detail below in conjunction with the accompanying drawings:

[0019] Attached Figure 1 The schematic diagram of the structure of the combined life-saving rocket of the present invention is shown in FIG. The combined life-saving rocket is composed of an igniter 1, a combustion chamber 2, a main charge 3, a nozzle seat 4, a nozzle 5, and a long-tail nozzle assembly 6. The igniter 1 is fixedly connected to the combustion chamber 2 by screws, the main charge 3 can be freely loaded into the combustion chamber 2, the nozzle seat 4 is fixedly connected to the combustion chamber 2 by threads, the nozzle 5 is fixedly connected to the nozzle seat 4 by threads, and the long-tail nozzle assembly 6 is fixedly connected to the combustion chamber 2 by screws.

[0020] Attached Figure 2 The figure is a schematic diagram of the structure of the long tail nozzle assembly of the present invention. The long tail nozzle assembly is mainly composed of electric detonator 7, air bleed joint 8, blocking plug 9, shear pin 10, fastening screw 11, long tail nozzle 12, support seat 13 and other parts. The electric detonator 7 is connected to the air bleed joint 8 by threads, the blocking plug 9 is placed in the inner cavity of the air bleed joint 8, the shear pin 10 is inserted into the through hole formed by the blocking plug 9 and the air bleed joint 8, and is fixed by the fastening screw 11, the long tail nozzle 12 is connected to the air bleed joint 8 by threads, and the long tail nozzle 12 is connected to the support seat 13 by threads.

[0021] Combined with Figure 1 , Attachment Figure 2 and attached Figure 3 Explain the working principle of the combined life-saving rocket.

[0022] Attached Figure 1 As shown in Figure 3, the working principle of the present invention is that when the combined rocket is working, the gas in the combustion chamber 2 can be ejected through the nozzle 5 to produce the attached Figure 1 The thrust shown in the direction of C in the figure; at the same time, as shown in the attached Figure 2 As shown, the gas in the combustion chamber 2 enters the long tail nozzle 12 through the joint 8, generating an axial thrust along the long tail nozzle 12, and the thrust direction is adjacent to the Figure 1 Middle D direction.

[0023] The combined rocket can generate a main thrust in the C direction, acting on the seat to provide it with secondary power, and at the same time generate a lateral force in the D direction to change the posture of the seat, thereby achieving trajectory divergence or posture change of the seat under the continued action of the main thrust.

[0024] When the electric detonator 7 is working, the blocking plug 9 cuts off the shear pin 10 under the action of the gas, and moves along the inner cavity of the causing joint 8 until it contacts the long tail nozzle 12. At this time, the gas in the combustion chamber 2 is blocked by the blocking plug 9, and the long tail nozzle 12 stops working.

[0025] By controlling the operation of the electric detonator, the long tail nozzle can be turned on and off, thereby adjusting the thrust action time in the D direction, and thus adjusting the attitude deflection torque of the seat.

[0026] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present application, which all belong to the protection scope of the present application.

Claims

1. A multifunctional rocket based on a rocket ejection seat, comprising a combined life-saving rocket provided with a combustion chamber (2) and a long tail nozzle assembly (6), wherein the long tail nozzle assembly (6) is arranged beside the combined life-saving rocket and is fixedly connected to the combustion chamber (2) by screws, characterized in that: The long tail nozzle assembly (6) comprises an electric detonator (7), an air bleed joint (8), a blocking plug (9) and a long tail nozzle (12). The air bleed joint (8) is an air passage of a three-way structure, one end of which is fixedly connected to the combined life-saving rocket. The blocking plug (9) is placed in the air bleed joint. A gap air passage is left at one end of the long tail nozzle (12) to allow the gas generated in the working combustion chamber (2) of the life-saving rocket to enter. The other two ends are respectively connected to the long tail nozzle (12) and the electric detonator (7). When the electric detonator (7) is working and generates gas, it pushes the blocking plug (9) through the air bleed joint (8) and moves along the inner cavity of the air bleed joint (8) until it contacts the long tail nozzle (12). At this time, the gas in the combustion chamber (2) is blocked by the blocking plug (9). The life-saving rocket further comprises a shear pin (10) and a fastening screw (11), the blocking plug (9) and the air bleed joint (8) are provided with a coaxial through hole, the shear pin (10) is inserted into the through hole and fixed by the fastening screw (11); the life-saving rocket further comprises a support seat (13), the long tail nozzle (12) is axially parallel to the life-saving rocket and is fixedly connected by the support seat (13); the combined life-saving rocket further comprises an igniter (1), a main charge (3), a nozzle seat (4) and a nozzle (5), the igniter (1) is fixedly connected to the combustion chamber (2), the main charge (3) is freely loaded into the combustion chamber (2), the nozzle seat (4) is fixedly connected to the combustion chamber (2), and the nozzle (5) is fixedly connected to the nozzle seat (4).

2. A multifunctional rocket based on a rocket ejection seat according to claim 1, characterized in that: The blocking plug (9) can move freely in the inner cavity of the air bleed connector (8).

3. A multifunctional rocket based on a rocket ejection seat according to claim 1, characterized in that: The shear pin (10) can move freely in the through hole.

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