A control system and control method for a space vehicle's thrust chamber
By introducing actuators, angle monitors, reset processing modules, and correction modules into the thrust chamber of the space launch vehicle, the problem of the thrust chamber tilting angle deviating from the central axis was solved, enabling real-time angle correction and reset of the thrust chamber, and improving the flight accuracy and reliability of the space launch vehicle.
Patent Information
- Application Number
- CN202310093621.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2023-02-10
- Publication Date
- 2026-05-15
- Estimated Expiration
- 2043-02-10
AI Technical Summary
If the line of action of the thrust chamber of a space launch vehicle engine deviates from the central axis, the thrust chamber will not be able to swing at the predetermined tilt angle during the oscillation process, affecting the accuracy of trajectory correction and maneuvering flight.
The system employs actuators, angle monitors, reset processing modules, and correction modules. By monitoring the relationship between the actual tilt angle of the thrust chamber and the predetermined tilt angle, it calculates the offset and performs reset processing to ensure that the thrust chamber swings according to the predetermined tilt angle.
It enables real-time tilt angle correction and reset of the thrust chamber, improving the accuracy of flight trajectory correction and maneuvering of the space launch vehicle, and enhancing the reliability of the system and flight reliability.
Smart Images
Figure CN116331519B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of space launch vehicle control, and more specifically to a thrust chamber control system and control method for a space launch vehicle. Background Technology
[0002] Ideally, the line of action of the thrust chamber of a space launch vehicle engine should coincide with the engine's central axis. However, in reality, limitations in manufacturing precision can cause geometric asymmetry in the engine, or asymmetrical flow of high-temperature, high-pressure gas through the thrust chamber nozzle, as well as deformation caused by ablation at the nozzle throat. This results in the thrust chamber's line of action deviating from the engine's central axis, preventing it from oscillating at the predetermined tilt angle during rocking maneuvers. Current technology lacks procedures for resetting and correcting the thrust chamber during space launch vehicle testing or flight, which is crucial for orbital correction and maneuvering of space launch vehicles.
[0003] Therefore, there is an urgent need to design a high-precision, convenient, and reliable thrust chamber control system and control method for space launch vehicles. Summary of the Invention
[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a thrust chamber control system and control method for a space launch vehicle.
[0005] This invention provides a thrust chamber control system for a space launch vehicle, comprising: an actuator for providing power to control the thrust chamber to swing at a predetermined tilt angle; an angle monitor for monitoring the actual tilt angle of the thrust chamber; a reset processing module for controlling the thrust chamber to reset via the actuator; and a correction module for performing correction with the reset processing module. The resetting of the thrust chamber via the actuator includes: if the actual tilt angle is equal to the predetermined tilt angle, the reset processing module resets the thrust chamber according to the predetermined tilt angle; if the actual tilt angle is not equal to the predetermined tilt angle, the correction module calculates a correction offset based on the relationship between the actual tilt angle and the predetermined tilt angle, and the reset processing module adds or subtracts the offset to the predetermined tilt angle to reset the thrust chamber.
[0006] According to one embodiment of the present invention, when the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is greater than or equal to a first threshold, the correction module uses the first threshold as the offset, and the reset processing module performs a reset process by adding the offset to the predetermined tilt angle.
[0007] According to one embodiment of the present invention, when the actual tilt angle is greater than the predetermined tilt angle and the difference between the two is less than a first threshold, the correction module uses the difference as the offset, and the reset processing module performs a reset process by adding the offset to the predetermined tilt angle.
[0008] According to one embodiment of the present invention, when the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is greater than or equal to a second threshold, the correction module uses the second threshold as the offset, and the reset processing module performs a reset process on the predetermined tilt angle minus the offset.
[0009] According to one embodiment of the present invention, when the actual tilt angle is less than the predetermined tilt angle and the difference between the two is less than a second threshold, the correction module uses the difference as the offset, and the reset processing module performs a reset process on the predetermined tilt angle minus the offset.
[0010] According to one embodiment of the present invention, when the predetermined tilt angle is zero degrees, if the actual tilt angle is not equal to zero and the actual tilt angle is greater than or equal to a third threshold, the correction module uses the third threshold as the offset, and the reset processing module performs reset processing by correcting the offset.
[0011] According to one embodiment of the present invention, when the predetermined tilt angle is zero degrees, if the actual tilt angle is not equal to zero and the actual tilt angle is less than a third threshold, the reset processing module performs a reset process based on the actual tilt angle.
[0012] On the other hand, the present invention also provides a thrust chamber control method for a space launch vehicle. The thrust chamber includes: an actuator that provides power to control the thrust chamber to swing at a predetermined tilt angle; and an angle monitor that monitors the actual tilt angle of the thrust chamber. The method includes: a reset processing step, in which the thrust chamber is reset according to the predetermined tilt angle if the actual tilt angle is equal to the predetermined tilt angle; and a correction step, in which a correction offset is calculated based on the relationship between the actual tilt angle and the predetermined tilt angle if the actual tilt angle is not equal to the predetermined tilt angle, and the thrust chamber is reset by adding or subtracting the offset according to the predetermined tilt angle.
[0013] According to one embodiment of the present invention, the correction step includes: when the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is greater than or equal to a first threshold, the first threshold is used as the offset, and the actuator performs a reset process at the predetermined tilt angle plus the correction of the offset; when the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is less than the first threshold, the difference is used as the offset, and the actuator performs a reset process at the predetermined tilt angle plus the correction of the offset.
[0014] According to one embodiment of the present invention, the correction step includes: when the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is greater than or equal to a second threshold, the second threshold is used as the offset, and the actuator performs a reset process on the correction of the predetermined tilt angle minus the offset; when the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is less than the second threshold, the difference is used as the offset, and the actuator performs a reset process on the correction of the predetermined tilt angle minus the offset.
[0015] This application controls the reset of the thrust chamber by analyzing the reset processing module and the correction module in the thrust chamber control system of the space launch vehicle. It can continuously correct the real-time tilt angle of the thrust chamber and reset it during the test or flight using a convenient and reliable control method, and perform real-time correction of the flight trajectory and maneuvering flight, which is conducive to improving the accuracy of the space launch vehicle flying according to the predetermined trajectory.
[0016] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the invention. Attached Figure Description
[0017] The accompanying drawings, which are part of the specification of this invention, illustrate exemplary embodiments of the invention. The drawings, together with the description in the specification, serve to illustrate the principles of the invention.
[0018] Figure 1 This is a schematic diagram of the thrust chamber control system of a space launch vehicle according to an embodiment of the present invention;
[0019] Figure 2 This is a schematic diagram of a thrust chamber control method for a space launch vehicle according to an embodiment of the present invention;
[0020] Figure 3 This is a schematic diagram of the thrust chamber of a space launch vehicle according to an embodiment of the present invention;
[0021] Figure 4 This is a schematic diagram of the thrust chamber of a space launch vehicle according to another embodiment of the present invention.
[0022] Explanation of reference numerals in the attached figures:
[0023] 100-Swing shaft, 200-Bearing housing, 300-Normal flat seat, 400-Rocker arm, 500-Actuator, 600-Angle monitor. Detailed Implementation
[0024] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.
[0025] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" 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 direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.
[0026] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.
[0027] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.
[0028] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.
[0029] Figure 1 This is a schematic diagram of the thrust chamber control system of a space launch vehicle according to an embodiment of the present invention; Figure 2 This is a schematic diagram of a thrust chamber control method for a space launch vehicle according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the thrust chamber of a space launch vehicle according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the thrust chamber of a space launch vehicle according to another embodiment of the present invention.
[0030] like Figure 1 As shown, the present invention provides a thrust chamber control system for a space launch vehicle, comprising: an actuator for providing power to control the thrust chamber to swing at a predetermined tilt angle; an angle monitor for monitoring the actual tilt angle of the thrust chamber; a reset processing module for controlling the thrust chamber to reset via the actuator; and a correction module for performing correction with the reset processing module. The resetting of the thrust chamber via the actuator includes: if the actual tilt angle is equal to the predetermined tilt angle, the reset processing module resets the thrust chamber according to the predetermined tilt angle; if the actual tilt angle is not equal to the predetermined tilt angle, the correction module calculates a correction offset based on the relationship between the actual tilt angle and the predetermined tilt angle, and the reset processing module adds or subtracts the offset to reset the thrust chamber according to the predetermined tilt angle.
[0031] like Figure 3 and Figure 4 As shown, the present invention provides a thrust chamber for a space launch vehicle, comprising: a rocking shaft 100 fixed on both sides of the thrust chamber axis; a sliding bearing mounted on the rocking shaft 100 for providing circumferential motion around the rocking shaft 100; a bearing housing 200 with a circular bearing hole 201 in the middle for mounting the sliding bearing; and a constant-level seat 300, which is a frame structure and spans across the bearing housings 200 located on both sides of the thrust chamber for bearing support during the rocking motion of the thrust chamber.
[0032] In one embodiment, an actuator 500 in the thrust chamber is mounted on one side of the constant-level seat 300 and fixedly connected to the rocker shaft 100 via a rocker arm 400. The extension or retraction of the actuator 500 causes the rocker arm 400 to rotate around the rocker shaft 100, thereby causing the thrust chamber to rock to a predetermined tilt angle. When thrust chamber rocking is required, the actuator 500 is energized. Under the action of drive currents of different magnitudes and directions, the actuator 500 extends or retracts, causing the rocker arm 400 to rotate around the rocker shaft 100, thereby causing the thrust chamber to rock to a preset tilt angle. By maintaining different servo drive current magnitudes and being able to lock at any position within the maximum stroke range, the thrust chamber rocking angle is locked. An angle monitor 600 is located at the central axis of the engine thrust chamber to monitor the actual tilt angle of the engine thrust chamber. In this embodiment, the angle monitor 600 can be configured as an angle sensor or angular displacement sensor, or other device capable of measuring angle changes.
[0033] Specifically, when the angle monitor reads the thrust chamber's angle position, it saves the current thrust chamber angle position for no less than ten cycles and performs data filtering using the median filtering method. If the actual tilt angle equals the predetermined tilt angle, it indicates that the actuator has completed the thrust chamber swing according to the predetermined tilt angle and has not been affected by other factors. During the reset operation, the reset processing module resets the thrust chamber using the predetermined tilt angle as the reset angle. If the actual tilt angle does not equal the predetermined tilt angle, it indicates that the actuator has not completed the thrust chamber swing according to the predetermined tilt angle or that the thrust chamber has been affected by the environment. The correction module calculates the correction offset based on the relationship between the actual tilt angle and the predetermined tilt angle. The reset processing module adds or subtracts the offset from the predetermined tilt angle to obtain the reset angle for resetting the thrust chamber.
[0034] The thrust chamber control system of the space launch vehicle described in this application can continuously correct and reset the real-time tilt angle of the thrust chamber during testing or flight using a convenient and reliable control method. This allows for real-time correction of the flight trajectory and maneuvering, improving the accuracy of the space launch vehicle's flight along the predetermined trajectory. Furthermore, the thrust chamber control system can establish a relationship between the thrust chamber's deviations at different flight stages based on data records from each thrust chamber reset, including the relationship between the predetermined and actual tilt angles. This facilitates more precise swing angle control by the thrust chamber actuators, thereby enhancing the flight reliability of the space launch vehicle. As a backup control method for the space launch vehicle's attitude control scheme, this thrust chamber control system can adjust the attitude when the swing thrust chamber malfunctions, effectively improving system reliability and facilitating control reconfiguration.
[0035] Those skilled in the art will understand that the thrust chamber control system of the space launch vehicle provided in the embodiments of this application can be specifically designed and manufactured for the desired purpose, or it may include known devices in a general-purpose computer. These devices have computer programs stored therein that are selectively activated or reconfigured. Such computer programs can be stored in a device (e.g., computer) readable medium or in any type of medium suitable for storing electronic instructions and respectively coupled to a bus.
[0036] In one optional embodiment, this application provides a thrust chamber control system for a space launch vehicle, which further includes a communication module and a memory. The communication module, memory, and thrust chamber control device are connected to the thrust chamber, and the thrust chamber control device includes a reset processing module and a correction module.
[0037] The memory can be ROM (Read-Only Memory) or other types of static storage devices that can store static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices that can store information and instructions, or EEPROM (Electrically Erasable Programmable Read-Only Memory), CD-ROM (Compac Disc Read-Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited thereto.
[0038] The communication module can be used for signal reception and transmission. It allows the thrust chamber control unit of the spacecraft's thrust chamber control system to communicate wirelessly or wiredly with other equipment to exchange data. It should be noted that in practical applications, there is more than one communication module.
[0039] The thrust chamber control system of the space launch vehicle in this embodiment can also be used in the field of space launch vehicle recovery. This control system is beneficial for the attitude and orbit control of the launch vehicle during the recovery process, and can ensure the accuracy of the recovery process.
[0040] According to one embodiment of the present invention, when the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is greater than or equal to a first threshold, the correction module uses the first threshold as an offset, and the reset processing module performs a reset process by adding the offset correction to the predetermined tilt angle.
[0041] According to one embodiment of the present invention, when the actual tilt angle is greater than the predetermined tilt angle and the difference between the two is less than the first threshold, the correction module uses the difference as the offset, and the reset processing module performs reset processing by adding the offset correction to the predetermined tilt angle.
[0042] According to one embodiment of the present invention, when the actual tilt angle is less than the predetermined tilt angle and the difference between the two is greater than or equal to the second threshold, the correction module uses the second threshold as the offset, and the reset processing module performs reset processing by subtracting the offset from the predetermined tilt angle.
[0043] According to one embodiment of the present invention, when the actual tilt angle is less than the predetermined tilt angle and the difference between the two is less than the second threshold, the correction module uses the difference as the offset, and the reset processing module performs reset processing by subtracting the offset from the predetermined tilt angle.
[0044] Specifically, based on the relationship between the actual tilt angle of the thrust chamber and the predetermined tilt angle, and the difference between the two, the thrust chamber reset operation is performed under different conditions.
[0045] In this embodiment, when the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is greater than or equal to a first threshold, the correction module uses the first threshold as the offset, and the reset processing module performs a reset process by adding the offset correction to the predetermined tilt angle. When the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is greater than or equal to a second threshold, the correction module uses the second threshold as the offset, and the reset processing module performs a reset process by subtracting the offset correction from the predetermined tilt angle. In both embodiments, if the difference between the actual tilt angle and the predetermined tilt angle is greater than or equal to the first threshold or the second threshold, the correction module uses the first threshold or the second threshold as the offset. Due to the influence of the thrust chamber environment and mechanical limit positions of the space launch vehicle, setting the offset to the first threshold or the second threshold is beneficial to ensuring the mechanical position of the thrust chamber is corrected and avoiding affecting the space launch vehicle's flight along an incorrect orbital path.
[0046] In this embodiment, when the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is less than a first threshold, the correction module uses the difference as an offset, and the reset processing module performs a reset process by adding the offset correction to the predetermined tilt angle. When the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is less than a second threshold, the correction module uses the difference as an offset, and the reset processing module performs a reset process by subtracting the offset correction from the predetermined tilt angle. In these two embodiments, if the difference between the actual tilt angle and the predetermined tilt angle is less than either the first or the second threshold, the correction module uses the difference as the offset. These two cases indicate that the deviation angle of the thrust chamber sway is within a reasonable range. As long as the offset is still used during correction, the reset processing module adds or subtracts the offset from the predetermined tilt angle to perform the reset process, ensuring that the thrust chamber is reset to zero.
[0047] In one embodiment, the first threshold and the second threshold can be set to be equal, or the first threshold can be set to be less than the second threshold. The specific threshold value is determined based on the actual mechanical limit angle of the thrust chamber and multiple sets of test data.
[0048] According to one embodiment of the present invention, when the predetermined tilt angle is zero degrees, if the actual tilt angle is not equal to zero and the actual tilt angle is greater than or equal to a third threshold, the correction module uses the third threshold as an offset, and the reset processing module performs reset processing by correcting the offset.
[0049] According to one embodiment of the present invention, when the predetermined tilt angle is zero degrees, if the actual tilt angle is not equal to zero and the actual tilt angle is less than a third threshold, the reset processing module performs reset processing based on the actual tilt angle.
[0050] Specifically, when the predetermined tilt angle is zero degrees, it indicates that the thrust chamber of the space launch vehicle has not undergone angle swinging operation. At this time, the angle monitor detects that the actual tilt angle is not zero, which may be due to the influence of the test environment or flight environment on the thrust chamber. Different reset processing operations are performed according to the relationship between the actual tilt angle and the third threshold. That is to say, when the difference is small, the reset processing module uses the actual tilt angle for reset processing; when the difference is large, the reset processing module uses the third threshold for reset processing. This ensures that the thrust chamber remains in the zero position even without swinging operation commands, increasing the reliability of the space launch vehicle during testing or flight and ensuring the safety of the control process.
[0051] On the other hand, such as Figure 2 As shown, the present invention also provides a thrust chamber control method for a space launch vehicle. The thrust chamber includes: an actuator that provides power to control the thrust chamber to swing at a predetermined tilt angle; and an angle monitor that monitors the actual tilt angle of the thrust chamber.
[0052] The thrust chamber control method of this space launch vehicle includes:
[0053] S101, Reset processing step: If the actual tilt angle is equal to the predetermined tilt angle, then reset the thrust chamber according to the predetermined tilt angle.
[0054] S102, Correction step: If the actual tilt angle is not equal to the predetermined tilt angle, calculate the correction offset based on the relationship between the actual tilt angle and the predetermined tilt angle, and add or subtract the offset according to the predetermined tilt angle to reset the thrust chamber.
[0055] According to one embodiment of the present invention, the correction step includes: when the actual tilt angle is greater than the predetermined tilt angle and the difference between the two is greater than or equal to a first threshold, the first threshold is used as an offset, and the actuator is reset by adding the offset to the predetermined tilt angle; when the actual tilt angle is greater than the predetermined tilt angle and the difference between the two is less than the first threshold, the difference is used as an offset, and the actuator is reset by adding the offset to the predetermined tilt angle.
[0056] According to one embodiment of the present invention, the correction step includes: when the actual tilt angle is less than the predetermined tilt angle and the difference between the two is greater than or equal to a second threshold, the second threshold is used as an offset, and the actuator is reset by correction of the predetermined tilt angle minus the offset; when the actual tilt angle is less than the predetermined tilt angle and the difference between the two is less than the second threshold, the difference is used as an offset, and the actuator is reset by correction of the predetermined tilt angle minus the offset.
[0057] Since the thrust chamber control method of a space launch vehicle is basically the same as the technical characteristics and technical solution of the thrust chamber control system of a space launch vehicle, its technical effects will not be elaborated here.
[0058] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A thrust chamber control system for a space launch vehicle, characterized in that, include: Actuator, providing power to control the thrust chamber to swing at a predetermined tilt angle; Angle monitor monitors the actual tilt angle of the thrust chamber; The reset processing module controls the thrust chamber to reset via the actuator. The calibration module performs calibration with the reset processing module; The control of thrust chamber reset via the actuator includes: If the actual tilt angle is equal to the predetermined tilt angle, the reset processing module resets the thrust chamber according to the predetermined tilt angle. If the actual tilt angle is not equal to the predetermined tilt angle, the correction module calculates the correction offset based on the relationship between the actual tilt angle and the predetermined tilt angle, and the reset processing module adds or subtracts the offset according to the predetermined tilt angle to reset the thrust chamber. When the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is greater than or equal to a first threshold, the correction module uses the first threshold as the offset, and the reset processing module performs a reset process by adding the offset to the predetermined tilt angle. When the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is less than a first threshold, the correction module uses the difference as the offset, and the reset processing module performs a reset process by adding the offset to the predetermined tilt angle.
2. The thrust chamber control system of the space launch vehicle according to claim 1, characterized in that, When the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is greater than or equal to the second threshold, the correction module uses the second threshold as the offset, and the reset processing module performs a reset process on the predetermined tilt angle minus the offset.
3. The thrust chamber control system of the space launch vehicle according to claim 1, characterized in that, When the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is less than the second threshold, the correction module uses the difference as the offset, and the reset processing module performs a reset process by subtracting the offset from the predetermined tilt angle.
4. The thrust chamber control system of the space launch vehicle according to claim 1, characterized in that, When the predetermined tilt angle is zero degrees, if the actual tilt angle is not equal to zero and the actual tilt angle is greater than or equal to the third threshold, the correction module uses the third threshold as the offset, and the reset processing module performs reset processing through the correction of the offset.
5. The thrust chamber control system of the space launch vehicle according to claim 1, characterized in that, When the predetermined tilt angle is zero degrees, if the actual tilt angle is not equal to zero and the actual tilt angle is less than the third threshold, the reset processing module performs a reset process based on the actual tilt angle.
6. A thrust chamber control method for a space launch vehicle, characterized in that, The thrust chamber includes: an actuator that provides power to control the thrust chamber to oscillate at a predetermined tilt angle; and an angle monitor that monitors the actual tilt angle of the thrust chamber; the method includes: The reset process involves resetting the thrust chamber according to the predetermined tilt angle if the actual tilt angle is equal to the predetermined tilt angle. In the correction step, if the actual tilt angle is not equal to the predetermined tilt angle, the offset to be corrected is calculated based on the relationship between the actual tilt angle and the predetermined tilt angle, and the offset is added to or subtracted from the predetermined tilt angle to reset the thrust chamber. When the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is greater than or equal to a first threshold, the first threshold is used as the offset, and the actuator performs a reset process by adding the offset to the predetermined tilt angle for correction. When the actual tilt angle is greater than the predetermined tilt angle, and the difference between the two is less than a first threshold, the difference is used as the offset, and the actuator performs a reset process by adding the offset to the predetermined tilt angle.
7. The thrust chamber control method for a space launch vehicle according to claim 6, characterized in that, The correction steps include: When the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is greater than or equal to the second threshold, the second threshold is used as the offset, and the actuator performs a reset process by subtracting the offset from the predetermined tilt angle. When the actual tilt angle is less than the predetermined tilt angle, and the difference between the two is less than the second threshold, the difference is used as the offset, and the actuator performs a reset process by subtracting the offset from the predetermined tilt angle.