Attitude-controllable parallel structure of multiple rocket engines

Abstract

The invention discloses an attitude-controllable multi-rocket engine parallel connection structure which comprises a rack, and a first engine, a second engine, a third engine and a fourth engine which are mounted on the rack and are uniformly arranged along the periphery of a rocket center shaft, a center shaft of the first engine and a center shaft of the second engine are oppositely and obliquely arranged, and a center shaft of the third engine and a center shaft of the fourth engine are oppositely and obliquely arranged. Through the design that the four engines incline oppositely, the pitching, rolling and yawing functions are successfully integrated, and the problem of energy loss during rocket flight is effectively avoided. Meanwhile, a complex swing engine and a matched servo motor thereof in the prior art are abandoned, the system structure is greatly simplified, and the cost is remarkably reduced. According to the invention, the cost is obviously reduced, the performance of the rocket is not influenced, and the balance between cost control and performance expression is realized.

Description

Technical Field

[0001] The invention relates to a parallel structure of multiple rocket engines capable of attitude control, in particular to an electric flame cooker. Background Art

[0002] Traditional rocket engines are mostly arranged vertically or in parallel. When dealing with complex flight missions such as orbit adjustment and attitude maintenance, this conventional layout makes it difficult to flexibly and accurately implement power vector control, which limits the rocket's flight performance and makes it impossible to fully meet the needs of diverse missions. Especially when the rocket needs to roll, traditional rocket engines cannot quickly and accurately generate torque to rotate the rocket around its own axis, which severely restricts the flexibility of the rocket's attitude control and greatly weakens its mission execution capabilities.

[0003] With the development of technology, some attitude-controlled parallel structures of multiple rocket engines have appeared in the prior art. For example, Deep Blue Aerospace Technology has filed an application with patent number 202010329068.X. The application document discloses a parallel structure of multiple rocket engines, including a frame and several engines, and also includes 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 arranged on the rotating shaft, and the other end is connected to the engine. During the rocket recovery process, the heading and attitude of the rocket body are adjusted by controlling the swing of the engine to ensure stable recovery. However, the swing mechanism structure of the patented technical solution is complex. The purchase of multiple swing engines and their supporting servo motors increases the cost of research and development and manufacturing of the rocket. At the same time, the complexity of the control system increases the failure rate of the rocket and restricts the competitiveness of the launch vehicle.

[0004] Another example is the application filed by Beijing University of Aeronautics and Astronautics with patent number 201710853057.X, which discloses an attitude control device using rocket engine gas, including a propellant tank, a heat exchanger, a main engine, a buffer gas tank, and an attitude control device using rocket engine gas. The attitude control device using rocket engine gas includes at least two groups of engine groups; the two groups of engine groups are arranged relative to each other. The technical solution of this patent is that the two groups of auxiliary engines provide horizontal driving force, which flexibly controls the attitude of the rocket and realizes the pitch, roll and yaw functions. However, the two groups of auxiliary engines cannot generate thrust for the rocket, and are only used for attitude control. Therefore, carrying two additional groups of auxiliary engines not only increases the additional load of the rocket, but also increases the manufacturing cost of the rocket. Summary of the invention

[0005] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can completely solve the above-mentioned problems.

[0006] A parallel structure of multiple rocket engines capable of attitude control comprises a frame, and a first engine, a second engine, a third engine and a fourth engine mounted on the frame and evenly arranged around the central axis of the rocket, wherein the central axis of the first engine is inclined relative to the central axis of the second engine, and the central axis of the third engine is inclined relative to the central axis of the fourth engine; Preferably, the angle formed by the intersection of the extension line of the central axis of the first engine and the extension line of the central axis of the second engine is 10°-30°; Preferably, the angle formed by the intersection of the extension line of the central axis of the third engine and the extension line of the central axis of the fourth engine is 10°-30°; Preferably, the central axis of the first engine is arranged in parallel with the central axis of the fourth engine; Preferably, the central axis of the second engine is arranged in parallel with the central axis of the third engine; Preferably, the frame is circular in shape; Preferably, the first engine, the second engine, the third engine and the fourth engine are all fixedly connected to the frame.

[0007] Compared with the prior art, the advantages of the present invention are: the present invention successfully integrates the pitch, roll and yaw functions through the design of four engines tilted relative to each other, and effectively avoids the problem of energy loss during rocket flight. At the same time, the present invention abandons the complex swing engine and its supporting servo motor in the prior art, greatly simplifies the system structure, and in terms of cost, reduces materials, simplifies processes, and optimizes assembly processes, all-roundly reducing various costs in the manufacturing process. While significantly reducing costs, the present invention ensures that rocket performance is not affected, achieving a balance between cost control and performance.

[0008] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0010] Figure 1 It is a perspective view of the present invention.

[0011] Figure 2It is a schematic diagram of the thrust of the engine of the present invention when the rocket is in pitch motion.

[0012] Figure 3 It is a schematic diagram of the thrust of the engine of the present invention when the rocket is in yaw motion.

[0013] Figure 4 It is a schematic diagram of the thrust of the engine of the present invention when the rocket is in rolling motion.

[0014] Figure 5 It is a schematic diagram of the inclination angle a formed by the engine of the present invention and the vertical line of the frame plane. DETAILED DESCRIPTION

[0015] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0016] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0017] In addition, in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, it can also be the internal communication of two components, it can be a wireless connection, or it can be a wired connection. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0018] In addition, the technical features involved in the different embodiments of the present invention described later can be combined with each other as long as they do not conflict with each other.

[0019] See also Figure 1In an embodiment of the present invention, a parallel structure of multiple rocket engines with attitude control includes a frame 1, and a first engine 100, a second engine 200, a third engine 300 and a fourth engine 400 installed on the frame 1 and evenly arranged around the central axis of the rocket, the central axis of the first engine 100 is inclined relative to the central axis of the second engine 200, and the central axis of the third engine 300 is inclined relative to the central axis of the fourth engine 400.

[0020] In the embodiment of the present invention, the working principle of the present invention is: The first engine 100, the second engine 200, the third engine 300 and the fourth engine 400 work independently and generate high-temperature and high-pressure gas by burning propellant. The high-pressure gas is ejected from the nozzle at high speed, and according to Newton's third law, a reaction force, that is, thrust, is generated to push the rocket forward.

[0021] like Figure 2 As shown, when the rocket needs to be controlled to perform pitch motion, for example, to lift the rocket head upward, the thrust of the first engine 100 and the fourth engine 400 can be increased, while the thrust of the second engine 200 and the third engine 300 can be reduced. Since the central axes of the first engine 100 and the fourth engine 400 are parallel and have a certain angle with the central axis of the rocket, the thrust increased by the inclined jet will cause the rocket head to be subjected to an upward moment F; while the thrust of the second engine 200 and the third engine 300 is reduced, so that the downward moment F on the rocket tail is reduced, thereby achieving the upward pitch motion of the rocket head.

[0022] Compared with a vertical jet engine, the torque F generated by the tilted jet in the present invention can complete the pitch motion of the rocket more quickly.

[0023] like Figure 3 As shown, when the yaw motion of the rocket is required, such as yaw to the left, the thrust of the second engine 200 and the third engine 300 can be increased, while the thrust of the first engine 100 and the fourth engine 400 can be reduced. The second engine 200 and the third engine 300 are relatively tilted, and the thrust increased by the tilted jet will generate a rightward resultant moment F on the left side of the rocket, while the thrust of the first engine 100 and the fourth engine 400 is reduced, so that the moment F on the right side of the rocket is relatively increased, thereby causing the rocket to yaw to the left around the vertical axis. Similarly, the rightward yaw of the rocket can be achieved by adjusting the opposite thrust.

[0024] Compared with the rocking engine, the present invention does not require engine swing, and the torque F generated directly by the tilted jet can correct the rocket attitude more quickly.

[0025] like Figure 4As shown, the present invention can also realize the rolling motion of the rocket by controlling the thrust difference of two relative engines among the four engines to realize the rolling control. For example, increasing the thrust of the first engine 100 and the third engine 300 while reducing the thrust of the second engine 200 and the fourth engine 400 will cause the rocket to generate a rolling moment F around its longitudinal axis, thereby realizing the rolling motion. The specific rolling direction depends on the specific situation of the engine layout and thrust adjustment.

[0026] Compared with the swinging engine, the fixed engine of the present invention has a faster response speed, and the structure of the present invention is relatively simple. The engine is directly fixed on the frame 1, and no complicated swinging mechanism and servo motor system are required, which helps to reduce the overall weight and manufacturing cost of the rocket, while also reducing potential failure points and improving the reliability of the rocket.

[0027] In an embodiment of the present invention, the angle formed by the extension line of the central axis of the first engine 100 and the extension line of the central axis of the second engine 200 is 10°-30°, and the angle formed by the extension line of the central axis of the third engine 300 and the extension line of the central axis of the fourth engine 400 is 10°-30°.

[0028] like Figure 5 As shown, the inclination angles a formed by the central axes of the first engine 100, the second engine 200, the third engine 300 and the fourth engine 400 and the vertical line of the plane of the frame 1 are 5°-15°, and a smaller inclination makes the adjustment of the engine thrust direction more precise.

[0029] The smaller inclination setting prevents the high-speed gases ejected from the four engines from intersecting. The intersection and collision of high-speed gases will prevent the energy of the gases from being fully converted into thrust for the rocket, which will lead to thrust loss, thereby reducing the effective energy that can be used to propel the rocket forward and causing thrust to drop.

[0030] The present invention successfully integrates the pitch, roll and yaw functions through the design of four engines tilted relative to each other, and effectively avoids the energy loss problem during rocket flight. At the same time, the present invention abandons the complex swing engine and its supporting servo motor in the prior art, greatly simplifies the system structure, and in terms of cost, reduces materials, simplifies processes, and optimizes assembly processes, all-roundly reducing various costs in the manufacturing process. While significantly reducing costs, the present invention ensures that rocket performance is not affected, achieving a balance between cost control and performance.

[0031] In another embodiment of the present invention, the central axis of the first engine 100 is arranged in parallel with the central axis of the fourth engine 400; the central axis of the second engine 200 is arranged in parallel with the central axis of the third engine 300.

[0032] In another embodiment of the present invention, the first engine 100, the second engine 200, the third engine 300 and the fourth engine 400 are all fixedly connected to the frame 1, and the fixed connection design does not require complex movable joints, rotating mechanisms and matching precision manufacturing processes. This makes the manufacturing process of the engine and the frame 1 simpler and more direct, reduces the technical difficulty and process requirements in the production process, and is conducive to improving production efficiency and reducing production costs.

[0033] 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 present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be considered exemplary and non-restrictive in all respects, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention.

Claims

1. A parallel structure of multiple rocket engines capable of attitude control, comprising a frame, and a first engine, a second engine, a third engine and a fourth engine mounted on the frame and evenly arranged around the central axis of the rocket, characterized in that: The central axis of the first engine and the central axis of the second engine are arranged to be inclined relative to each other, and the central axis of the third engine and the central axis of the fourth engine are arranged to be inclined relative to each other.

2. The attitude-controllable parallel structure of multiple rocket engines according to claim 1 is characterized in that: The angle formed by the intersection of the extension line of the central axis of the first engine and the extension line of the central axis of the second engine is 10°-30°.

3. The attitude-controllable parallel structure of multiple rocket engines according to claim 1 is characterized in that: The angle formed by the intersection of the extension line of the central axis of the third engine and the extension line of the central axis of the fourth engine is 10°-30°.

4. The attitude-controllable parallel structure of multiple rocket engines according to claim 1 is characterized in that: The first engine central axis is arranged in parallel with the fourth engine central axis.

5. The attitude-controllable parallel structure of multiple rocket engines according to claim 1 is characterized in that: The second engine central axis is arranged in parallel with the third engine central axis.

6. The attitude-controllable parallel structure of multiple rocket engines according to claim 1 is characterized in that: The frame is circular in shape.

7. The attitude-controllable parallel structure of multiple rocket engines according to claim 1 is characterized in that: The first engine, the second engine, the third engine and the fourth engine are all fixedly connected to the frame.

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