Composite charging device of rocket engine
By installing a composition of smoke solid gunpowder and smokeless solid gunpowder in the composite charging device of the rocket engine, the problem of smoke entering the aircraft engine is solved, and the flight distance of the rocket is ensured by burning smoke solid gunpowder, achieving the dual goals of safe flight and effective propulsion.
Patent Information
- Application Number
- CN202411833684.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-13
- Publication Date
- 2025-03-14
AI Technical Summary
In the prior art, when solid rocket engines use smoked solid gunpowder, a large amount of smoke will be generated to block the pilot's field of view and may enter the aircraft engine, resulting in failure; while using smokeless solid gunpowder will have less thrust and specific shock, affecting the rocket's flight distance.
A composite charging device for rocket engines is designed. By installing a composition of smoke solid gunpowder and smokeless solid gunpowder in the shell, the smoke solid gunpowder coaxial sleeve is arranged outside the smokeless solid gunpowder, and smokeless solid gunpowder is burned before the rocket leaves the plane to prevent smoke from entering the aircraft engine; after leaving the plane, smoke solid gunpowder is burned to ensure that the flight distance of the rocket is not shortened.
It effectively prevents smoke generated by gunpowder combustion from entering the aircraft engine, ensures flight safety, and ensures that the rocket's flight distance is not shortened by burning smoke-containing solid gunpowder.
Smart Images
Figure CN119616718A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of rocket engines, and in particular to a composite charge device for a rocket engine. Background Art
[0002] In the prior art, solid rocket engines are loaded on aircraft. Solid rocket engines usually use smoky solid gunpowder as fuel. Smoky solid gunpowder will produce a large amount of smoke when burning. On the one hand, a large amount of smoke will block the pilot's field of vision. On the other hand, it is easy to be inhaled by the aircraft's engine, which may cause the aircraft engine to stop in the air, having a great impact on flight safety.
[0003] In order to reduce the above-mentioned problems caused by the use of smoke-containing solid gunpowder as fuel in solid rocket engines, technicians have made the following improvements: using solid gunpowder with a lower smoke content to load solid rocket engines, but in practice, solid gunpowder with a lower smoke content will still produce a small amount of smoke when burned, and the aircraft's engine will still be affected by the smoke; the technicians have made further improvements: using smokeless solid gunpowder to load rocket engines, but this will bring new problems. Although smokeless solid gunpowder does not produce smoke when burned, its thrust and specific impulse are smaller than those of smoked solid gunpowder, which will affect the flight distance of the rocket.
[0004] Therefore, the technical problem existing in the prior art is that it is urgently necessary to propose a rocket engine composite charge device, which can prevent the smoke from the burning gunpowder from entering the engine of the aircraft without shortening the flight distance of the rocket. Summary of the invention
[0005] In view of the technical problems in the prior art, it is now urgently necessary to propose a rocket engine composite charge device, which can prevent the smoke from the burning of gunpowder from entering the engine of the aircraft and does not shorten the flight distance of the rocket. The present invention provides a rocket engine composite charge device.
[0006] The present invention is achieved through the following technical solutions:
[0007] A rocket engine composite charge device comprises a coaxially arranged shell and a nozzle, wherein the nozzle is connected to one end of the shell along the axis direction of the shell, and the shell has a cavity, and the cavity is communicated with the outside atmosphere only through the tube cavity of the nozzle;
[0008] It also includes smoke solid gunpowder and smokeless solid gunpowder, wherein the smoke solid gunpowder and the smokeless solid gunpowder are both cylindrical structures with openings at both ends along the axial direction, the smoke solid gunpowder is coaxially sleeved outside the smokeless solid gunpowder, and the inner ring wall of the smoke solid gunpowder and the outer ring wall of the smokeless solid gunpowder are in contact with each other; at the same time, the combination of the smoke solid gunpowder and the smokeless solid gunpowder is coaxially arranged in the cavity; the cylindrical channel enclosed by the inner ring wall of the smokeless solid gunpowder is communicated with the tube cavity of the nozzle;
[0009] Also included is an electronic lighter, which is connected to the end of the housing facing away from the nozzle.
[0010] Furthermore, the ignition end of the electronic lighter is arranged in a cylindrical channel formed by the inner wall of the smokeless solid gunpowder.
[0011] Furthermore, one end of the shell facing the nozzle is provided with a connecting plate, and the nozzle and the connecting plate are connected by welding.
[0012] Furthermore, the cavity is a columnar cavity.
[0013] Compared with the prior art, the advantages of the present invention are:
[0014] 1. The present invention proposes a rocket engine composite charge device, which creatively sets a smoky solid gunpowder coaxially outside the smokeless solid gunpowder, and the combination of the smoky solid gunpowder and the smokeless solid gunpowder is set in the outer shell. Before the rocket engine leaves the aircraft, the smokeless solid gunpowder is burned, which avoids the phenomenon of the engine failure of the aircraft caused by the smoke generated by the burning of gunpowder blocking the pilot's field of vision and the smoke entering the engine of the aircraft in the prior art; after the rocket engine leaves the aircraft, the smoky solid gunpowder is burned, and the smoky solid gunpowder has greater power, ensuring that the flight distance of the rocket is not shortened. Therefore, the present invention solves the technical problems existing in the prior art: it is urgently necessary to propose a rocket engine composite charge device, which can prevent the smoke from the burning of gunpowder from entering the engine of the aircraft and does not shorten the flight distance of the rocket. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 It is a structural schematic diagram of the rocket engine composite charge device of the present invention;
[0016] Figure 2 It is a schematic diagram of the connection structure between the shell and the nozzle;
[0017] Figure 3 for Figure 1 Sectional view;
[0018] Figure 4 for Figure 3 Schematic diagram of the enlarged structure of area A in the middle.
[0019] Markings in the figure: housing (1), nozzle (2), cavity (3), tube cavity (4), smoke-containing solid gunpowder (5), smokeless solid gunpowder (6), electronic lighter (7), connecting plate (8). DETAILED DESCRIPTION
[0020] The following is a further non-restrictive detailed description of the technical solution of the invention in conjunction with the preferred embodiments and the accompanying drawings. In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate the orientation or position relationship based on the orientation or position relationship shown in the accompanying drawings. In addition, the terms "first" and "second" are used only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and cannot be understood as limitations on the present invention.
[0021] Example 1
[0022] like Figure 1 to Figure 3 As shown, this embodiment proposes a rocket engine composite charge device, which includes a coaxially arranged shell 1 and a nozzle 2, along the axial direction of the shell 1, the nozzle 2 is connected to one end of the shell 1, the shell 1 has a cavity 3, and the cavity 3 is connected to the outside atmosphere only through the tube cavity 4 of the nozzle 2; it also includes smoke solid gunpowder 5 and smokeless solid gunpowder 6, wherein the smoke solid gunpowder 5 and the smokeless solid gunpowder 6 are both cylindrical structures with openings at both ends along the axial direction, the smoke solid gunpowder 5 is coaxially sleeved outside the smokeless solid gunpowder 6, and the inner ring wall of the smoke solid gunpowder 5 and the outer ring wall of the smokeless solid gunpowder 6 are in contact with each other; at the same time, the combination of the smoke solid gunpowder 5 and the smokeless solid gunpowder 6 is coaxially arranged in the cavity 3; the cylindrical channel enclosed by the inner ring wall of the smokeless solid gunpowder 6 is connected to the tube cavity 4 of the nozzle 2; it also includes an electronic lighter 7, which is connected to the end of the shell 1 away from the nozzle 2.
[0023] like Figure 1-2As shown, the shell 1 and the nozzle 2 are both made of metal, and the shell 1 and the nozzle 2 can be processed separately. For example, the shell 1 includes a shell and a top cover, and the upper and lower ends of the shell have openings respectively. After the lower end of the shell and the nozzle 2 are welded together, the opening at the lower end of the shell is communicated with the tube cavity 4 of the nozzle 2, and then smoke solid gunpowder 5 and smokeless solid gunpowder 6 are filled from the top opening of the shell. Finally, the top cover is fixed to the upper end of the shell by screws and the opening at the upper end is sealed; preferably, in this embodiment, the connection method of the shell 1 and the nozzle 2 is: the end of the shell 1 facing the nozzle 2 has a connecting plate 8, and the connecting plate 8 is a metal plate, and the nozzle 2 is connected to the connecting plate 8 by welding.
[0024] In this embodiment, preferably, the cavity 3 is a columnar cavity; the tube cavity 4 of the nozzle 2 is also a cavity structure symmetrical with respect to the axis. In this embodiment, the cavity 3 is connected to the outside atmosphere only through the tube cavity 4 of the nozzle 2, so that after the smoke solid propellant 5 and the smokeless solid propellant 6 arranged in the cavity 3 are burned respectively, the high-temperature and high-pressure gas generated by the combustion is only ejected from the nozzle 2, thereby propelling the rocket to move in a fixed direction.
[0025] like Figure 3 As shown, the smoke solid gunpowder 5 is a cylindrical structure formed by injection molding of smoke solid gunpowder, and the smokeless solid gunpowder 6 is a cylindrical structure formed by injection molding of smokeless gunpowder; in this embodiment, the combination of smoke solid gunpowder 5 and smokeless solid gunpowder 6 is coaxially arranged with the cavity 3. In this embodiment, both the smoke solid gunpowder 5 and the smokeless solid gunpowder 6 are cylindrical, which is easy to process and assemble. The components of the smoke solid gunpowder 5 and the smokeless solid gunpowder 6 are all existing technologies and will not be described here. After ignition, they can burn without oxygen and produce a large amount of high-temperature and high-pressure gas to drive the rocket.
[0026] like Figure 3-4 As shown, the structure of the electronic lighter 7 is the prior art, which is a device that ignites after being powered on, and its structure will not be described in detail here; the connection method between the electronic lighter 7 and the housing 1 also adopts one of the prior art, such as a detachable connection or a non-detachable connection. In the present embodiment, the electronic lighter 7 is detachably fixed to the inner wall of the cavity 3 by screws or bolts, that is, the electronic lighter 7 is detachably fixed to the top cover by screws or bolts; further, in the present embodiment, the ignition end of the electronic lighter 7 is arranged in the cylindrical channel formed by the inner ring wall of the smokeless solid gunpowder 6, so as to save the axial space occupied by the sub-lighter 7; preferably, in the present embodiment, the electronic lighter 7 is arranged at the upper end of the cylindrical channel formed by the inner ring wall of the smokeless solid gunpowder 6, and is opposite to the lower end of the cylindrical channel.
[0027] When in use, the electronic lighter 7 is ignited to ignite the upper end of the inner ring surface of the smokeless solid gunpowder 6; then, the flame burns rapidly along the axial direction of the smokeless solid gunpowder 6 until it burns from the upper end of the inner ring surface of the smokeless solid gunpowder 6 to the lower end of the inner ring surface of the smokeless solid gunpowder 6; thereafter, it burns along the radial direction of the smokeless solid gunpowder 6, from the inner ring of the smokeless solid gunpowder 6 to the direction of the outer ring of the smokeless solid gunpowder 6, until the smokeless solid gunpowder 6 is completely burned; in this process, the smokeless solid gunpowder 6 will not produce smoke, thereby avoiding the impact on the engine of the aircraft, that is, avoiding the phenomenon in the prior art that the smoke generated by the burning of gunpowder blocks the pilot's field of vision, and the smoke enters the engine of the aircraft, causing the engine failure of the aircraft. The amount of gunpowder in the smokeless solid gunpowder 6 should at least be guaranteed to be able to burn until the rocket leaves the aircraft.
[0028] When the outer ring surface of the smokeless solid gunpowder 6 burns, the smoke-containing solid gunpowder 5 arranged outside the smokeless solid gunpowder 6 is ignited synchronously, and the smoke-containing solid gunpowder 5 burns radially, and the high-temperature and high-pressure gas generated by it gives the rocket a greater thrust to ensure the flight distance of the rocket; at this time, the rocket has left the aircraft, and the smoke from the burning smoke-containing solid gunpowder 5 will not block the pilot's field of vision, nor will it enter the aircraft's engine to affect the aircraft's engine.
[0029] In the above process, no matter whether the smoke-containing solid propellant 5 or the smokeless solid propellant 6 is burned, the high-temperature and high-pressure gas generated by the combustion is ejected from the nozzle 2 .
[0030] As can be seen from the background technology, the technical problem existing in the prior art is that there is an urgent need to propose a rocket engine composite charge device, which can prevent the smoke from the burning gunpowder from entering the engine of the aircraft without shortening the flight distance of the rocket.
[0031] In this embodiment, a rocket engine composite charge device is proposed, which creatively sets the smoke solid gunpowder 5 coaxially outside the smokeless solid gunpowder 6, and the combination of the smoke solid gunpowder 5 and the smokeless solid gunpowder 6 is arranged in the shell 1. Before the rocket engine leaves the aircraft, the smokeless solid gunpowder 6 is burned, which avoids the phenomenon of the engine failure of the aircraft caused by the smoke generated by the burning of gunpowder in the prior art, which blocks the pilot's vision and the smoke enters the engine of the aircraft; after the rocket engine leaves the aircraft, the smoke solid gunpowder 5 is burned, and the smoke solid gunpowder 5 has greater power, ensuring that the flight distance of the rocket is not shortened. Therefore, this embodiment solves the technical problems existing in the prior art: it is urgently necessary to propose a rocket engine composite charge device, which can prevent the smoke from the burning of gunpowder from entering the engine of the aircraft and does not shorten the flight distance of the rocket.
[0032] The above embodiments only express several implementation methods of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the attached claims.
Claims
1. A rocket engine composite charge device, characterized in that: The invention comprises a coaxially arranged housing (1) and a nozzle (2), wherein the nozzle (2) is connected to one end of the housing (1) along the axial direction of the housing (1), and the housing (1) has a cavity (3), and the cavity (3) is connected to the outside atmosphere only through a tube cavity (4) of the nozzle (2); It also includes smoke-containing solid gunpowder (5) and smokeless solid gunpowder (6), wherein the smoke-containing solid gunpowder (5) and the smokeless solid gunpowder (6) are both cylindrical structures with openings at both ends along the axial direction, the smoke-containing solid gunpowder (5) is coaxially sleeved outside the smokeless solid gunpowder (6), and the inner ring wall of the smoke-containing solid gunpowder (5) and the outer ring wall of the smokeless solid gunpowder (6) are in contact with each other; at the same time, the combination of the smoke-containing solid gunpowder (5) and the smokeless solid gunpowder (6) is coaxially arranged in the cavity (3); the cylindrical channel enclosed by the inner ring wall of the smokeless solid gunpowder (6) is communicated with the tube cavity (4) of the nozzle (2); The utility model also comprises an electronic lighter (7), which is connected to an end of the housing (1) which is away from the nozzle (2).
2. The rocket engine composite charge device according to claim 1, characterized in that: The ignition end of the electronic lighter (7) is arranged in a cylindrical passage formed by the inner wall of the smokeless solid gunpowder (6).
3. The rocket engine composite charge device according to claim 1, characterized in that: One end of the housing (1) facing the nozzle (2) is provided with a connecting plate (8), and the nozzle (2) and the connecting plate (8) are connected by welding.
4. The rocket engine composite charge device according to claim 1, characterized in that: The cavity (3) is a columnar cavity.