Thrust control device and power system of orbiter and orbiter

Abstract

The present application discloses a thrust control device and a power system of an orbital vehicle and an orbital vehicle. The thrust control device comprises: a support frame, comprising a first sub-support frame and a second sub-support frame, wherein the first sub-support frame and the second sub-support frame are mounted on a base of the orbital vehicle; and a thrust direction adjustment structure, which is mounted on the first sub-support frame and the second sub-support frame, and the thrust direction adjustment structure adjusts the thrust direction of the engine of the orbital vehicle in three-dimensional space. Thereby, the maneuverability of the aircraft is improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace engineering, and more specifically, to a thrust control device and power system of an orbital vehicle and an orbital vehicle. Background Art

[0002] In the field of aerospace engineering, the power system of an orbital transfer vehicle is one of its core components, which is responsible for providing the necessary thrust during orbit changes and attitude adjustments.

[0003] Currently, most orbital transfer vehicles use fixed thrust devices, such as traditional rocket engines. The thrust direction of fixed thrust devices is fixed and cannot be adjusted in real time according to the needs of the flight mission, which limits the maneuverability of the vehicle in complex orbital operations.

[0004] Therefore, how to improve the maneuverability of aircraft becomes a technical problem that needs to be solved in this field. Summary of the invention

[0005] In view of this, the present application proposes a thrust control device and a power system of an orbital vehicle and an orbital vehicle, so as to improve the maneuverability of the vehicle.

[0006] In a first aspect, the present application provides a thrust control device for an orbital vehicle, the thrust control device comprising: a support frame, comprising a first sub-support frame and a second sub-support frame, the first sub-support frame and the second sub-support frame being mounted on a base of the orbital vehicle; and a thrust direction adjustment structure, mounted on the first sub-support frame and the second sub-support frame, the thrust direction adjustment structure adjusting the thrust direction of the engine of the orbital vehicle in three-dimensional space.

[0007] Optionally, the thrust direction adjustment structure includes: an annular frame, rotatably fixed between the first sub-support frame and the second sub-support frame, the annular frame being rotatably fixed to the first end and the second end of the swing arm of the engine of the orbiter; a first driving mechanism, used to drive the annular frame to swing; and a second driving mechanism, used to drive the swing arm to swing.

[0008] Optionally, the annular frame includes a first short shaft and a second short shaft, and the thrust direction adjustment structure also includes: a frame support rotating structure, including a first sub-support rotating structure and a second sub-support rotating structure, the first sub-support rotating structure can rotatably fix the first sub-support frame and the first short shaft, and the second sub-support rotating structure can rotatably fix the second sub-support frame and the second short shaft, so that the annular frame can swing, wherein the first drive mechanism is connected to the first short shaft or the second short shaft; and / or an engine support rotating structure, including a third sub-support rotating structure and a fourth sub-support rotating structure, the third sub-support rotating structure can rotatably fix the annular frame and the first end, and the fourth sub-support rotating structure can rotatably fix the annular frame and the second end, wherein the second drive mechanism is connected to the first end or the second end.

[0009] Optionally, the first sub-support rotating structure and the second sub-support rotating structure are both ball bearings, and / or the third sub-support rotating structure and the fourth sub-support rotating structure are both ball bearings.

[0010] Optionally, the cross-sectional shape of the annular frame is square.

[0011] Optionally, the annular frame includes a first side, a second side, a third side, and a fourth side, the first side and the third side are opposite to each other, the second side and the fourth side are opposite to each other, the first sub-support frame can be rotatably fixed at the center position of the first side, the second sub-support frame can be rotatably fixed at the center position of the third side, the first end can be rotatably fixed at the center position of the second side, and the second end can be rotatably fixed at the center position of the fourth side.

[0012] Optionally, the support frame further includes: at least one third sub-support frame, wherein the third sub-support frame is connected to the base and the first sub-support frame.

[0013] Optionally, the support frame further includes: at least one fourth sub-support frame, wherein the fourth sub-support frame is connected to the base and the second sub-support frame.

[0014] In a second aspect, the present application also provides a power system for an orbital vehicle, the power system comprising: the above-mentioned thrust control device; and the engine of the orbital vehicle.

[0015] In a third aspect, the present application also provides an orbital vehicle, which includes: the above-mentioned power system.

[0016] According to the technical solution of the present application, the thrust direction adjustment structure is installed on the base of the orbiter through the first sub-support frame and the second sub-support frame. The thrust direction adjustment structure can adjust the thrust direction of the engine of the orbiter in three-dimensional space. In this way, the adjustability of the thrust direction of the engine is realized, the thrust output of the engine in multiple directions is realized, and the flexibility in adjusting the thrust direction is improved, so that the thrust direction of the engine can be adjusted according to the needs of the flight mission, so that the needs of complex orbit transfer missions can be met, and the maneuverability of the aircraft is improved. In addition, according to the technical solution of the present application, the thrust direction can be adjusted in three-dimensional space, and the thrust direction can be controlled more accurately, and the control accuracy of the thrust direction is improved, which can meet the needs of high-precision orbit transformation, reduce the probability of increasing flight errors, and avoid affecting the execution effect of the mission. According to the technical solution of the present application, the precise adjustment of the engine thrust vector in three-dimensional space is realized, and the attitude control accuracy of the aircraft during the orbit transfer process is greatly improved. This improvement is of great significance for executing high-precision aerospace missions, reducing flight errors, and improving the success rate of missions.

[0017] Other features and advantages of the present application will be described in detail in the subsequent detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings constituting a part of the present application are used to provide a further understanding of the present application, and the schematic implementation modes and descriptions of the present application are used to explain the present application. In the accompanying drawings:

[0019] Figure 1 It is a structural schematic diagram of a thrust control device according to a preferred embodiment of the present application;

[0020] Figure 2 It is a structural schematic diagram of a thrust control device according to a preferred embodiment of the present application;

[0021] Figure 3 A cross-sectional view of a partial structure of a thrust control device according to a preferred embodiment of the present application; and

[0022] Figure 4 It is a cross-sectional view of a partial structure of a thrust control device according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0023] The technical solution of the present application will be described in detail below with reference to the accompanying drawings and in combination with the implementation modes.

[0024] In a first aspect, an embodiment of the present application provides a thrust control device for an orbiter. The thrust control device includes a support frame 10 and a thrust direction adjustment structure 20 .

[0025] The support frame 10 includes a first sub-support frame 101 and a second sub-support frame 102, and the first sub-support frame 101 and the second sub-support frame 102 are installed on the base 30 of the orbiter. Figure 1 shown.

[0026] The thrust direction adjustment structure 20 is installed on the first sub-support frame 101 and the second sub-support frame 102. Figure 1 or Figure 2 As shown, the thrust direction adjustment structure 20 adjusts the thrust direction of the orbiter's engine 40 in three-dimensional space.

[0027] Optionally, in the embodiment of the present application, the thrust direction adjustment structure 20 may include an annular frame 201, a first driving mechanism 202 and a second driving mechanism 203, such as Figure 1 Or as shown in 2.

[0028] The annular frame 201 is rotatably fixed between the first sub-support frame 101 and the second sub-support frame 102, and the annular frame 201 is rotatably fixed to the first end 4011 and the second end 4012 of the swing arm 401 of the orbiter's engine 40. It should be noted that the rotatable fixing means that it can rotate around the straight line where the fixed point is located. In the embodiment of the present application, the annular frame 201 can rotate (i.e. swing), and the swing arm 401 can rotate (i.e. swing).

[0029] The use of a swingable annular frame 201 enables the engine to swing at a large angle in a specific plane. The annular frame 201 can be made of high-strength, lightweight materials, such as titanium alloy or carbon fiber composite materials, to reduce the overall weight and improve the structural strength. The annular frame must have sufficient strength and rigidity to support the entire device and be integrated with a drive mechanism.

[0030] The first driving mechanism 202 is used to drive the annular frame 201 to swing. The second driving mechanism 203 is used to drive the swing arm 401 to swing.

[0031] The first driving mechanism 202 drives the annular frame 201 to swing and the second driving mechanism 203 drives the swing arm 401 to swing, so that the thrust direction of the engine 40 is adjusted in three-dimensional space, that is, the thrust direction of the engine 40 is changed in three-dimensional space. Flexible and precise rotational motion is achieved through the swinging of the annular frame 201 and the swing arm 401 to drive the change of the engine thrust vector. In the embodiment of the present application, the material and structural strength of the swing arm 401 can be determined according to the specific situation to ensure the accuracy and stability of the swinging action.

[0032] According to the technical solution provided in the embodiment of the present application, it is only necessary to drive the annular frame 201 and the swing arm 401 to swing, so that the thrust direction of the engine 40 can be adjusted in three-dimensional space, and the thrust direction adjustment can be directly realized without the need for a complex attitude control system, which simplifies the attitude control system, reduces the complexity of operation, and reduces energy consumption. By reducing unnecessary energy consumption of the attitude control system, it helps to optimize the overall energy management of the aircraft and improve the efficiency and endurance of the aircraft. In addition, according to the technical solution provided in the embodiment of the present application, it is not necessary to coordinate the actions of multiple thrusters, and the operation does not consume a lot of energy, which reduces the requirements for the energy management of the aircraft, improves the reliability of long-term operation, and can show strong stability in extreme environments.

[0033] Optionally, in the embodiment of the present application, the annular frame 201 includes a first short axis 2011 and a second short axis 2012. Figure 1 As shown. The first short axis 2011 is fixedly connected to the first sub-support frame 101 by screws. Specifically, the end of the first short axis 2011 fixedly connected to the first sub-support frame 101 has a planar structure, and the planar structure is fixedly connected to the first sub-support frame 101 by screws. The second short axis 2012 is fixedly connected to the second sub-support frame 102 by screws. Specifically, the end of the second short axis 2012 fixedly connected to the second sub-support frame 102 has a planar structure, and the planar structure is fixedly connected to the second sub-support frame 102 by screws.

[0034] The thrust direction adjustment structure 20 also includes: a frame support rotating structure and / or an engine support rotating structure.

[0035] The frame support rotating structure includes a first sub-support rotating structure and a second sub-support rotating structure 2042. The first sub-support rotating structure is installed in the first sub-support frame 101, and the second sub-support rotating structure 2042 is installed in the second sub-support frame 102.

[0036] The first sub-support rotating structure rotatably fixes the first sub-support frame 101 and the first short axis 2011, and the second sub-support rotating structure rotatably fixes the second sub-support frame 102 and the second short axis 2012, so that the annular frame 201 can swing. The first sub-support rotating structure rotatably fixes the first sub-support frame 101 and the first short axis 2011, and the first short axis 2011 can rotate. The second sub-support rotating structure 2042 rotatably fixes the second sub-support frame 102 and the second short axis 2012, and the second short axis 2012 can rotate. The first short axis 2011 and the second short axis 2012 can rotate, so that the annular frame 201 can swing.

[0037] The first driving mechanism 202 is connected to the first short shaft 2011 or the second short shaft 2012 .

[0038] like Figure 1 or Figure 3 As shown, the first driving mechanism 202 is connected to the second short shaft 2012. Figure 3 As shown, the second sub-support rotating structure 2042 can rotatably fix the second sub-support frame 102 and the second short shaft 2012, wherein the second sub-support rotating structure 2042 is a ball bearing. In addition, the first driving mechanism 202 is connected to the second short shaft 2012 through a coupling.

[0039] In the implementation manner of the present application, the first sub-support rotating structure can be understood with reference to the second sub-support rotating structure 2042, and the first sub-support rotating structure can also be a ball bearing.

[0040] The engine supporting rotating structure includes a third sub-supporting rotating structure and a fourth sub-supporting rotating structure 2052. The third sub-supporting rotating structure and the fourth sub-supporting rotating structure 2052 are installed in the annular frame 201.

[0041] The third sub-support rotating structure rotatably fixes the annular frame 201 and the first end 4011 of the swing arm 401, and the fourth sub-support rotating structure 2052 rotatably fixes the annular frame 201 and the second end 4012 of the swing arm 401. By rotatably fixing, the swing arm 401 can rotate.

[0042] The second driving mechanism 203 is connected to the first end 4011 or the second end 4012 .

[0043] like Figure 1 or Figure 4 As shown, the second driving mechanism 203 is connected to the second end 4012. Figure 4 As shown, the fourth sub-support rotating structure 2052 can rotatably fix the annular frame 201 and the second end 4012 of the swing arm 401, wherein the fourth sub-support rotating structure 2052 is a ball bearing. In addition, the second driving mechanism 203 is connected to the second end 4012 through a coupling.

[0044] In the implementation manner of the present application, the third sub-support rotating structure can be understood with reference to the fourth sub-support rotating structure 2052, and the third sub-support rotating structure can also be a ball bearing.

[0045] Optionally, in the embodiment of the present application, at least one of the following groups are all ball bearings: the first sub-support rotating structure and the second sub-support rotating structure, the third sub-support rotating structure and the fourth sub-support rotating structure. In other words, the first sub-support rotating structure and the second sub-support rotating structure are both ball bearings, and / or the third sub-support rotating structure and the fourth sub-support rotating structure are both ball bearings.

[0046] Optionally, in the embodiment of the present application, the ball bearing may adopt a high-precision bearing to support smooth rocking motion.

[0047] Optionally, in an embodiment of the present application, the first sub-support rotating structure and the second sub-support rotating structure are both magnetic bearings, and / or the third sub-support rotating structure and the fourth sub-support rotating structure are both magnetic bearings.

[0048] Optionally, in the embodiment of the present application, the magnetic bearing includes an electromagnetic coil. The electromagnetic coil is installed inside the annular frame 201 to generate a magnetic field to control the suspension and swing of the engine 40. The engine 40 is designed to have magnetism or built-in magnetic materials to interact with the magnetic field generated by the electromagnetic coil.

[0049] The magnetic bearing uses magnetic suspension technology to achieve contactless swinging motion of the engine 40 (or other loads) in the annular frame 201 through electromagnetic field force. The magnetic bearing uses the principle of mutual repulsion of like magnetic poles, allowing the engine 40 to levitate and move without physical contact.

[0050] A magnetic suspension bearing is used to replace the ball bearing, and the magnetic field force is used to make the engine 40 swing without contact in the annular frame 201. This solution has the advantages of low friction, long life, high precision, etc.

[0051] Optionally, in the embodiment of the present application, the cross-sectional shape of the annular frame 201 is a square. Figure 1 As shown, the cross-sectional shape of the annular frame 201 is a square. In addition, the cross-sectional shape of the annular frame 201 can also be a rectangle.

[0052] Optionally, in the embodiment of the present application, the annular frame 201 includes a first side 2013, a second side 2014, a third side 2015, and a fourth side 2016, the first side 2013 and the third side 2015 are opposite, the second side 2014 and the fourth side 2016 are opposite, the first sub-support frame 101 is rotatably fixed at the center of the first side 2013, the second sub-support frame 102 is rotatably fixed at the center of the third side 2015, the first end 4011 of the swing arm 401 is rotatably fixed at the center of the second side 2014, and the second end 4012 of the swing arm 401 is rotatably fixed at the center of the fourth side 2016. In this way, the control accuracy of the thrust direction can be further improved.

[0053] like Figure 1 As shown, the first short shaft 2011 is fixed at the center position of the first side 2013 , and the first sub-support frame 101 is rotatably fixed to the first short shaft 2011 , so that the first sub-support frame 101 is rotatably fixed at the center position of the first side 2013 .

[0054] like Figure 1 As shown, the second short shaft 2012 is fixed at the center position of the third side 2015 , and the second sub-support frame 102 is rotatably fixed to the second short shaft 2012 , so that the second sub-support frame 102 is rotatably fixed at the center position of the third side 2015 .

[0055] Optionally, in the embodiment of the present application, the support frame 10 further includes: at least one third sub-support frame 103 , and the third sub-support frame 103 is connected to the base 30 and the first sub-support frame 101 .

[0056] like Figure 2 As shown, two third sub-support frames 103 are also included, and each third sub-support frame 103 is connected to the base 30 and the first sub-support frame 101.

[0057] Optionally, in the embodiment of the present application, the support frame 10 further includes: at least one fourth sub-support frame 104 , and the fourth sub-support frame 104 is connected to the base 30 and the second sub-support frame 102 .

[0058] like Figure 2 As shown, two fourth sub-support frames 104 (one of which is blocked) are also included, and each fourth sub-support frame 104 is connected to the base 30 and the second sub-support frame 102.

[0059] In the embodiment of the present application, the third sub-support frame 103 and / or the fourth sub-support frame 104 can be used to increase the firmness, so that the connection between the thrust control device and the base 30 is more firmly established.

[0060] Optionally, in the embodiment of the present application, the first drive mechanism 202 and / or the second drive mechanism 203 include an electric actuator, a hydraulic or pneumatic motor. The first drive mechanism 202 is connected to the annular frame 201 through an efficient transmission system, and the second drive mechanism 203 is connected to the swing arm 401 through an efficient transmission system. The first drive mechanism 202 and the second drive mechanism 203 can quickly and accurately adjust the swing angle of the engine according to the instructions of the intelligent control system.

[0061] The embodiment of the present application also provides an intelligent control system. The intelligent control system integrates advanced sensors and intelligent control algorithms to monitor the attitude, speed, position and other parameters of the aircraft in real time, and calculates the optimal swing parameters (such as swing angle, speed, direction, etc.) through a multi-parameter real-time AI intelligent fusion algorithm based on preset orbital change requirements and real-time data, and realizes precise swinging movements by controlling the driving mechanism, thereby achieving high-precision situational awareness of the flight status of the orbital aircraft.

[0062] The technical solution provided in the implementation mode of the present application adopts an energy optimization strategy and an efficient energy management system. According to the actual needs of the aircraft and the working status of the swing device, based on the input of optimal swing parameters, a multi-parameter real-time AI intelligent fusion algorithm is used to achieve refined dynamic adjustment of energy distribution, reduce unnecessary energy consumption, and improve energy utilization efficiency.

[0063] The embodiments of the present application provide a thrust control device with novel structure, flexible operation and high reliability, which improves the overall performance of the orbital vehicle and enables it to complete space missions more efficiently and safely.

[0064] The technical solution provided by the embodiment of the present application can achieve: 1) vector thrust output of the engine in three-dimensional space (for example, vector thrust output is controlled within a large angular range of the three-dimensional circumference, and vector thrust output is performed along a certain conical surface), meeting the omnidirectional thrust requirements of the orbital vehicle; 2) improving the attitude control accuracy, through the three-dimensional space swinging capability of the annular swing device, the precise control of the attitude of the aircraft is achieved, and the accuracy and stability of the orbital change are significantly improved; 3) improving the flexibility of thrust direction adjustment, through the design of the annular swing frame, the vector thrust output of the engine in multiple directions at a large angle and in three dimensions can be achieved, greatly improving the operational flexibility of the aircraft in a complex orbital environment; 4) simplifying the attitude control system, the direct thrust direction adjustment capability reduces the dependence on the complex attitude control system, and reduces the complexity and energy consumption of attitude adjustment; 5) optimizing energy management, by reducing unnecessary energy consumption of the attitude control system, it helps to optimize the overall energy management of the aircraft and improve the endurance; 6) achieving omnidirectional thrust coverage, the device can achieve the thrust output of the engine within a range of 360 degrees, meeting the omnidirectional thrust requirements of the orbital transfer aircraft.

[0065] The technical solution provided by the implementation method of the present application is 1) highly innovative and provides a new device for controlling the thrust direction; 2) highly practical and has a wide range of practicality, suitable for various types of orbital vehicles, and can meet the needs of complex orbital missions; 3) good energy management, which helps to optimize the overall energy management of the vehicle, improves the endurance, and is suitable for long-term space missions; 4) all-round thrust coverage, which can achieve the thrust output of the engine within a range of not less than a large angle (the angle size is determined by the overall layout and overall needs, and the maximum can theoretically exceed 45°) in the circumferential direction in three-dimensional space, meeting the all-round thrust requirements of the orbital transfer vehicle. In summary, the technical solution provided by the implementation method of the present application is innovative in technical principles and applications, can effectively solve the limitations of the prior art in thrust direction adjustment, and has broad application prospects.

[0066] In a second aspect, an embodiment of the present application further provides a power system for an orbital vehicle, the power system comprising: the thrust control device described in the above embodiment; and an engine of the orbital vehicle.

[0067] In a third aspect, an embodiment of the present application further provides an orbital vehicle, which includes: the power system described in the above embodiment.

[0068] The preferred embodiments of the present application are described in detail above; however, the present application is not limited to the specific details in the above embodiments. Within the technical concept of the present application, a variety of simple modifications can be made to the technical solution of the present application, and these simple modifications all fall within the protection scope of the present application.

[0069] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this application will not further describe various possible combinations.

[0070] In addition, the various implementation modes of the present application may be arbitrarily combined, and as long as they do not violate the concept of the present application, they should also be regarded as the contents disclosed by the present invention.

Claims

1. A thrust control device for an orbital vehicle, characterized in that: The thrust control device comprises: a support frame, comprising a first sub-support frame, a second sub-support frame, at least one third sub-support frame and at least one fourth sub-support frame, wherein the first sub-support frame and the second sub-support frame are mounted on a base of the orbiter, the third sub-support frame connects the base and the first sub-support frame, and the fourth sub-support frame connects the base and the second sub-support frame; and a thrust direction adjustment structure, mounted on the first sub-support frame and the second sub-support frame, the thrust direction adjustment structure adjusting the thrust direction of the engine of the orbiter in three-dimensional space; Wherein, the thrust direction adjustment structure comprises: an annular frame, rotatably fixed between the first sub-support frame and the second sub-support frame, the annular frame comprising a first short axis and a second short axis, the annular frame being rotatably fixed to a first end and a second end of a swing arm of an engine of the orbiter, and the cross-sectional shape of the annular frame being a square; A frame support rotating structure, comprising a first sub-support rotating structure and a second sub-support rotating structure, wherein the first sub-support rotating structure can rotatably fix the first sub-support frame and the first short shaft, and the second sub-support rotating structure can rotatably fix the second sub-support frame and the second short shaft, so that the annular frame can swing; A first driving mechanism, used for driving the annular frame to swing, wherein the first driving mechanism is connected to the first short shaft or the second short shaft; an engine support rotating structure, comprising a third sub-support rotating structure and a fourth sub-support rotating structure, wherein the third sub-support rotating structure rotatably fixes the annular frame and the first end, and the fourth sub-support rotating structure rotatably fixes the annular frame and the second end; A second driving mechanism, used for driving the swing arm to swing, wherein the second driving mechanism is connected to the first end or the second end; Wherein, the annular frame includes a first side, a second side, a third side, and a fourth side, the first side and the third side are opposite to each other, the second side and the fourth side are opposite to each other, the first sub-support frame can be rotatably fixed at the center position of the first side, the second sub-support frame can be rotatably fixed at the center position of the third side, the first end can be rotatably fixed at the center position of the second side, and the second end can be rotatably fixed at the center position of the fourth side.

2. The thrust control device according to claim 1, characterized in that: The first sub-support rotating structure and the second sub-support rotating structure are both ball bearings.

3. The thrust control device according to claim 1, characterized in that: The third sub-support rotating structure and the fourth sub-support rotating structure are both ball bearings.

4. A power system for an orbital vehicle, characterized in that: The power system includes: The thrust control device according to any one of claims 1 to 3; and The orbiter's engine.

5. An orbital vehicle, characterized in that: The orbiter includes: The power system of claim 4.

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