Rocket engine with gas swing for attitude control

Abstract

The application discloses a rocket engine for attitude control by using gas swing, comprising an injector, a combustion chamber and a tail nozzle. The combustion chamber is provided with an X gas extraction pipe, and the first end of the X gas extraction pipe penetrates the wall surface of the combustion chamber and communicates with the inside of the combustion chamber. The combustion chamber is provided with a Y gas extraction pipe, and the first end of the Y gas extraction pipe penetrates the wall surface of the combustion chamber and communicates with the inside of the combustion chamber. The application controls the conduction and shutdown of four output pipes by two shunt valves, and the pressure difference vectors are superposed when three output pipes are simultaneously conducted, so that the high-speed main flow gas is precisely deflected, the rocket rapid and precise attitude correction or yaw is realized. The outlet ends of the four output pipes are flat, when the rocket needs to yaw or correct the attitude, only one output pipe needs to be conducted, the ejected gas forms a "wide coverage characteristic" oblique shock, so that the rocket thrust vector control is realized, the loss of main flow gas energy is avoided, and the attitude precise control and propulsion performance of the rocket are considered.

Description

Technical Field

[0001] This invention specifically relates to a rocket engine that utilizes gas oscillation to achieve attitude control. Background Technology

[0002] With the development of technology, some attitude-controllable rocket engines have emerged in existing technologies: the first stage of the Long March 7 carrier rocket uses a dual-engine parallel helium-pressurized bidirectional oscillating engine, and the second stage uses a four-engine parallel engine, of which two are fixed and two are bidirectional oscillating. The attitude control of the rocket is achieved by the oscillation of the engines; the Tianque 12 is a pump-driven oscillating gas generator circulating liquid oxygen methane rocket engine independently developed by LandSpace. Each individual engine is unidirectionally oscillating, with the oscillation direction being tangential to the rocket body and the oscillation angle being ±8°, which can provide attitude control forces in all directions for rocket flight.

[0003] For example, DeepBlue Aerospace Technology filed a patent application with patent number 202010329068.X, which discloses a parallel structure for multiple rocket engines, including a frame and several engines, as well as a swing mechanism. The swing mechanism includes a rotating shaft, a swing arm, and a servo motor. The rotating shaft is connected to the servo motor, and one end of the swing arm is mounted on the rotating shaft, while the other end is connected to the engine. During rocket recovery, the rocket's heading and attitude are adjusted by controlling the engine's swing, ensuring stable recovery.

[0004] For example, Beijing University of Aeronautics and Astronautics filed a patent application with patent number 201710853057.X, disclosing an attitude control device utilizing rocket engine exhaust gas, including a propellant tank, a heat exchanger, a main engine, a buffer gas tank, and an attitude control device utilizing rocket engine exhaust gas. The attitude control device utilizing rocket engine exhaust gas includes at least two sets of engine groups; the two sets of engine groups are arranged opposite each other.

[0005] The existing technical solutions described above involve complex oscillation mechanisms. The procurement of multiple oscillation engines and their associated servo motors increases the rocket's R&D and manufacturing costs. Furthermore, the oscillation engines have a slow response speed, failing to meet the attitude adjustment and correction requirements during rocket recovery. Simultaneously, the complexity of the control and oscillation systems increases the rocket's failure rate, hindering its competitiveness. The technical solution proposed by Beijing University of Aeronautics and Astronautics utilizes the horizontal driving force of two sets of auxiliary engines to flexibly control the rocket's attitude, achieving pitch, roll, and yaw functions. However, these two sets of auxiliary engines do not generate thrust for the rocket; they are only used for attitude control. Therefore, carrying two additional sets of auxiliary engines not only increases the rocket's additional load but also raises its manufacturing costs. Summary of the Invention

[0006] To overcome the shortcomings mentioned above, the present invention aims to provide a technical solution that can solve the above problems.

[0007] A rocket engine that uses gas oscillation to achieve attitude control includes: an injector, a combustion chamber, and a tail nozzle;

[0008] An X-type exhaust pipe is provided outside the combustion chamber, and the first end of the X-type exhaust pipe penetrates the wall of the combustion chamber and communicates with the interior of the combustion chamber.

[0009] The other end of the X extraction pipe is connected to the X diversion valve. The two output ends of the X diversion valve are respectively connected to the Xa output pipe and the Xb output pipe. The outlet ends of the Xa output pipe and the Xb output pipe extend into the interior of the tail nozzle in opposite directions.

[0010] Preferably, the X diverter valve can independently adjust the on / off state of the Xa output pipe and the Xb output pipe, and can independently control the gas flow rate flowing into the Xa output pipe and the Xb output pipe;

[0011] Preferably, a Y-extraction pipe is provided outside the combustion chamber, the first end of the Y-extraction pipe penetrates the wall of the combustion chamber and communicates with the interior of the combustion chamber; the other end of the Y-extraction pipe is connected to a Y-diverter valve, the two output ends of the Y-diverter valve are respectively connected to a Ya output pipe and a Yb output pipe, and the outlet ends of the Ya output pipe and the outlet ends of the Yb output pipe extend into the interior of the tail nozzle in opposite directions.

[0012] Preferably, the Y-diverter valve can independently adjust the on / off state of the Ya output pipe and the Yb output pipe, and can independently control the gas flow rate flowing into the Ya output pipe and the Yb output pipe;

[0013] Preferably, the valve cores of both the X-flow divider valve and the Y-flow divider valve are hollow structures, and both valve cores of the X-flow divider valve and the Y-flow divider valve have two through holes;

[0014] Preferably, the outlet ends of the Xa output pipe, the Xb output pipe, the Ya output pipe, and the Yb output pipe are all inclined toward the outlet direction of the tail nozzle, with an inclination angle of 30°-45° with the central axis of the tail nozzle.

[0015] Preferably, it also includes an attitude control module, which is electrically connected to the X-splitter valve and the Y-splitter valve respectively; the attitude control module can receive the rocket's attitude detection signal, calculate the required thrust vector adjustment amount according to the signal, and send control commands to the X-splitter valve and the Y-splitter valve to realize independent attitude control or cooperative attitude control in the X and Y directions.

[0016] Preferably, the interior of the combustion chamber and the sidewall of the tail nozzle are cavities, forming cooling channels.

[0017] Compared with the prior art, the advantages of the present invention are:

[0018] This invention controls the on / off state of four output pipes by using two diverter valves. When three output pipes are on simultaneously, a pressure difference vector superposition is generated, which completes the precise deflection of the high-speed mainstream gas, enabling rapid and precise attitude correction or yaw of the rocket.

[0019] The outlet ends of all four output pipes in this invention are flat. When the rocket needs to yaw or correct its attitude, only one output pipe needs to be turned on. The ejected gas forms a slanted shock wave with "wide coverage characteristics", thereby achieving thrust vector control of the rocket, avoiding the loss of mainstream gas energy, and taking into account both the rocket's precise attitude control and propulsion performance.

[0020] The outlet ends of the present invention are all inclined toward the outlet direction of the tail nozzle, with an inclination angle of 30°-45° with the central axis of the tail nozzle. The ejected gas forms a "forward angle" with the mainstream gas, which can be more smoothly integrated into the mainstream flow field, thereby increasing the deflection angle of the mainstream gas and significantly improving the response speed of attitude control.

[0021] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a three-dimensional structural view of the present invention.

[0024] Figure 2 This is a schematic diagram of the engine working principle in Example 1.

[0025] Figure 3 This is an exploded view of the diversion valve structure in Example 1.

[0026] Figure 4 This is a schematic diagram of the engine working principle in Example 2.

[0027] Figure 5 This is an exploded view of the diversion valve structure in Example 2.

[0028] Figure 6 This is a schematic diagram illustrating the working principle of the present invention. Detailed Implementation

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] In the description of this invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0031] Furthermore, in the description of this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components; they can refer to a wireless connection or a wired connection. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0032] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0033] Please see Figures 1-5 In this embodiment of the invention, a rocket engine that uses gas oscillation to achieve attitude control includes: an injector 100, a combustion chamber 200, and a tail nozzle 300.

[0034] An X-extraction pipe 400 is provided on the outside of the combustion chamber 200. The first end of the X-extraction pipe 400 penetrates the wall of the combustion chamber 200 and communicates with the inside of the combustion chamber 200.

[0035] The other end of the X extraction pipe 400 is connected to the X diversion valve 500. The two output ends of the X diversion valve 500 are respectively connected to the Xa output pipe 510 and the Xb output pipe 520. The outlet ends of the Xa output pipe 510 and the Xb output pipe 520 extend into the interior of the tail nozzle 300 in opposite directions.

[0036] The X diverter valve 500 can independently adjust the on / off state of the Xa output pipe 510 and the Xb output pipe 520, and can independently control the gas flow into the Xa output pipe 510 and the Xb output pipe 520.

[0037] A Y-extraction pipe 600 is provided on the outside of the combustion chamber 200. The first end of the Y-extraction pipe 600 penetrates the wall of the combustion chamber 200 and communicates with the inside of the combustion chamber 200. The other end of the Y-extraction pipe 600 is connected to a Y-divider valve 700. The two output ends of the Y-divider valve 700 are respectively connected to a Ya output pipe 710 and a Yb output pipe 720. The outlet ends of the Ya output pipe 710 and the Yb output pipe 720 extend into the interior of the tail nozzle 300 in opposite directions.

[0038] The Y-diverter valve 700 can independently adjust the on / off state of the Ya output pipe 710 and the Yb output pipe 720, and can independently control the gas flow into the Ya output pipe 710 and the Yb output pipe 720.

[0039] Both the X-flow divider valve 500 and the Y-flow divider valve 700 have hollow valve cores, and both valve cores have through holes.

[0040] When it is necessary to control the rocket's attitude, by controlling the valve core of the X-splitter valve 500 or the conduction state and gas flow of the Y-splitter valve 700, the gas ejected from the Xa output pipe 510 and Xb output pipe 520, and the Ya output pipe 710 and Yb output pipe 720 will generate different pressure distributions in the tail nozzle 300, thereby driving the high-speed gas flow in the tail nozzle 300 to deflect, thus achieving thrust vector control and achieving the purpose of adjusting the rocket's attitude. Example 1

[0041] like Figures 2-3As shown, the outlet ends of Xa output pipe 510, Xb output pipe 520, Ya output pipe 710, and Yb output pipe 720 are all cylindrical. The valve cores of X diverter valve 500 and Y diverter valve 700 each have two through holes. When the rocket needs to yaw or adjust its attitude in the Xb direction, the valve core of the X diverter valve 500 rotates, aligning one of the through holes with the Xa output pipe 510. The high-temperature gas expanding in the gas chamber flows from the X extraction pipe 400 into the valve core of the X diverter valve 500, then through the through hole and the Xa output pipe 510, and is ejected from the outlet end of the Xa output pipe 510, forming an oblique shock wave. The oblique shock wave interacts with the inner wall of the tail nozzle 300 and the mainstream gas, causing a sudden increase in the local gas pressure on one side of the Xa output pipe 510, forming a pressure difference with the Xb direction. This pressure difference will generate a lateral thrust on the mainstream gas in the tail nozzle 300, forcing the mainstream gas injection direction to shift towards the Xb direction. Typically, a unidirectional oblique shock wave will cause a Y-axis offset in the ejection direction of the high-speed mainstream gas. In this embodiment, simultaneously with the Xa output pipe 510, the two through holes in the valve core of the Y split valve 700 are respectively calibrated and connected to the Ya output pipe 710 and the Yb output pipe 720. The high-temperature gas expanding in the gas chamber, ejected from the outlet ends of the Ya output pipe 710 and the Yb output pipe 720 respectively, forms two additional oblique shock waves. These shock waves create vector superposition on the high-speed mainstream gas, preventing some of the high-speed mainstream gas from tilting in the Y direction, thus achieving precise yaw and attitude correction of the rocket. With all three pipes simultaneously connected and through pressure difference vector superposition, precise offset of the high-speed mainstream gas ejection direction can be achieved at the same time, realizing vector control of the rocket thrust and enabling rapid and precise attitude correction or yaw of the rocket. Example 2

[0042] The outlet ends of Xa output pipe 510, Xb output pipe 520, Ya output pipe 710, and Yb output pipe 720 are all flat. The long axis of the flat outlets extends radially along the tail nozzle 300, and the ejected gas forms a "fan-shaped jet" oblique shock wave. Therefore, the oblique shock wave of the flat outlet has wide coverage characteristics, and only a single oblique shock wave is needed to achieve precise rocket deviation or precise attitude correction. Figures 4-6 As shown in this embodiment, when the rocket needs to yaw or correct its attitude, only one output pipe needs to be activated to achieve precise deflection of the high-speed mainstream gas. This single-strand wide-coverage oblique shock wave enables thrust vector control of the rocket, avoiding the loss of high-speed mainstream gas energy and balancing precise attitude control and propulsion performance.

[0043] In this embodiment of the invention, the outlet ends of Xa output pipe 510, Xb output pipe 520, Ya output pipe 710, and Yb output pipe 720 are all inclined toward the outlet direction of the tail nozzle 300, with an inclination angle of 30°-45° to the central axis of the tail nozzle 300. If the outlet is perpendicular to the axis of the tail nozzle 300, the ejected gas will collide with the mainstream gas at a 90° angle, with most of the energy being converted into impact loss and only a small portion forming an effective oblique shock wave. When the inclination is 30°-45°, the ejected gas forms a "forward angle" with the mainstream gas, which can more smoothly integrate into the mainstream flow field and form an oblique shock wave with stable intensity. The "deflection force" of the oblique shock wave on the mainstream gas is more concentrated, which can increase the deflection angle of the mainstream gas under the same gas flow rate, and greatly improve the response speed of attitude control.

[0044] In this embodiment of the invention, the invention also includes an attitude control module (not shown in the accompanying drawings), which is electrically connected to the X-split valve 500 and the Y-split valve 700, respectively. The attitude control module receives the rocket's attitude detection signal, calculates the required thrust vector adjustment based on the signal, and sends control commands to the X-split valve 500 and the Y-split valve 700 to achieve independent or coordinated attitude control in the X and Y directions. Both the X-split valve 500 and the Y-split valve 700 are filled with coolant to prevent overheating of the system within the valve body.

[0045] The combustion chamber 200 has a double-layer sleeve structure on its side wall, and the cavity between the two layers forms an annular cooling channel. The tail nozzle 300 also has a double-layer structure on its side wall. The cooling channel is connected to the cooling channel of the combustion chamber 200. The cooling channel is spiral-shaped, which effectively facilitates heat exchange. The cooling medium is propellant.

[0046] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A rocket engine for attitude control by means of gas swing, characterized in that, Include: injector, combustion chamber, tail nozzle; The combustion chamber is provided with an X air extraction pipe outside, the first end of the X air extraction pipe penetrates the wall surface of the combustion chamber and communicates with the inside of the combustion chamber; The other end of the X air extraction pipe is connected with an X flow distribution valve, two output ends of the X flow distribution valve are respectively connected with an Xa output pipe and an Xb output pipe, the outlet end of the Xa output pipe and the outlet end of the Xb output pipe oppositely extend into the inside of the tail nozzle; The X flow distribution valve can independently adjust the off and on states of the Xa output pipe and the Xb output pipe, and can independently control the gas flow into the Xa output pipe and the Xb output pipe; The combustion chamber is provided with a Y air extraction pipe outside, the first end of the Y air extraction pipe penetrates the wall surface of the combustion chamber and communicates with the inside of the combustion chamber; the other end of the Y air extraction pipe is connected with a Y flow distribution valve, two output ends of the Y flow distribution valve are respectively connected with a Ya output pipe and a Yb output pipe, the outlet end of the Ya output pipe and the outlet end of the Yb output pipe oppositely extend into the inside of the tail nozzle; The Y flow distribution valve can independently adjust the off and on states of the Ya output pipe and the Yb output pipe, and can independently control the gas flow into the Ya output pipe and the Yb output pipe; The valve core of the X flow distribution valve and the valve core of the Y flow distribution valve are both hollow structures, and the valve core of the X flow distribution valve and the valve core of the Y flow distribution valve both have two through holes.

2. The rocket engine for attitude control using gas swing according to claim 1, characterized in that, The outlet end of the Xa output pipe, the outlet end of the Xb output pipe, the outlet end of the Ya output pipe and the outlet end of the Yb output pipe all tilt towards the outlet direction of the tail nozzle, and the tilt angle is 30°-45° with the central axis of the tail nozzle.

3. The rocket engine for attitude control using gas swing according to claim 2, wherein Further include an attitude control module, the attitude control module is respectively connected with X flow distribution valve, Y flow distribution valve; the attitude control module can receive the attitude detection signal of the rocket, calculate the required thrust vector adjustment amount according to the signal, and send control command to X flow distribution valve, Y flow distribution valve, realize X direction, Y direction independent attitude control or collaborative attitude control.

4. The rocket engine for attitude control using gas swing according to claim 3, wherein The inside of the combustion chamber and the side wall of the tail nozzle is a cavity, forming a cooling channel.

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