Intelligent shutdown method based on system quality output

Abstract

The invention relates to an intelligent shutdown method based on utilization of system mass output. The intelligent shutdown method comprises the steps of obtaining utilization of system residual propellant mass output, propellant unavailable mass, propellant second consumption and lifting apogee shutdown time; calculating the predicted workable time of the combustion agent and the oxidizing agent in the residual propellant to obtain the predicted workable time of the residual propellant; comparing the predicted workable time of the residual propellant with the lifting apogee shutdown time, and judging whether the liquid rocket can fly to the lifting apogee or not; and according to a judgment result, selecting a lifting apogee corresponding semi-major axis or a standard apogee corresponding semi-major axis to execute shutdown control. According to the method, the satellite injection target orbit is switched, so that the apogee of the satellite is raised, the propellant consumption caused by satellite orbital transfer is reduced, the in-orbit life of the satellite is prolonged, and the utilization rate of the residual propellant is increased.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid launch vehicles and relates to an intelligent shutdown method based on utilizing system mass output. Background Art

[0002] The liquid rocket utilization system adjusts the propellant mixing ratio during the operation of the liquid rocket to ensure that the oxidizer and the fuel are consumed in an appropriate ratio and improve the propellant utilization rate. However, the existing utilization system does not predict the remaining fuel and cannot effectively use the remaining propellant to continue working to raise the apogee height of the satellite payload. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to propose an intelligent shutdown method based on the utilization of system mass output, to predict the reachability of the flight target orbit according to the real-time propellant remaining situation of the utilization system mass output, and to raise the satellite apogee by switching the satellite into orbit target orbit under the premise of meeting the safety shutdown requirement, to reduce the propellant consumption caused by the satellite orbit change, and to increase the satellite's on-orbit life.

[0004] The solution to the technical problem of the present invention is: an intelligent shutdown method based on utilizing system quality output, comprising the following steps:

[0005] Obtain the remaining propellant mass output of the utilization system, the unavailable propellant mass, the propellant consumption per second and the lift apogee shutdown time;

[0006] The predicted operable time of the combustion agent and the oxidizer in the remaining propellant is calculated respectively according to the remaining propellant mass output of the utilization system, the unusable mass of the propellant and the propellant consumption per second, so as to obtain the predicted operable time of the remaining propellant;

[0007] Compare the predicted working time of the remaining propellant with the shutdown time of the lift apogee to determine whether the liquid rocket can fly to the lift apogee;

[0008] According to the judgment result, the semi-major axis corresponding to the lifting apogee or the semi-major axis corresponding to the standard apogee is selected to perform shutdown control.

[0009] Furthermore, the remaining propellant mass output of the utilization system includes: the remaining propellant mass M R , the remaining oxidant mass M Y .

[0010] Furthermore, the unavailable mass of the propellant includes: the unavailable mass of the combustion agent M hj_R 、Oxidant unusable mass M hj_Y .

[0011] Furthermore, the propellant consumption per second includes: the standard propellant consumption per second M 75R 、Oxidant standard consumption per second M 75Y .

[0012] Furthermore, the predicted working time of the combustion agent is:

[0013] T hj_R =(M R -M hj_R ) / M 75R .

[0014] Furthermore, the predicted working time of the oxidant is:

[0015] T hj_Y =(M Y -M hj_Y ) / M 75Y .

[0016] Furthermore, the predicted working time of the remaining propellant is:

[0017]

[0018] Further, the method of selecting the semi-major axis corresponding to the lifting apogee or the semi-major axis corresponding to the standard apogee to perform shutdown control is:

[0019]

[0020] When the predicted working time of the remaining propellant is T hj When the shutdown time is greater than tk5T, the liquid rocket can fly to the apogee of the lift, and the semi-major axis a corresponding to the apogee of the lift is used. T Shutdown control is performed; when the predicted working time T of the remaining propellant is hj When the shutdown time is less than tk5T, the liquid rocket cannot fly to the apogee of the lift. The standard apogee corresponds to the semi-major axis a b Perform shutdown control.

[0021] A computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of an intelligent shutdown method based on utilizing system quality output are implemented.

[0022] An electronic device comprises a memory, a processor and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the steps of an intelligent shutdown method based on utilizing system quality output are implemented.

[0023] The beneficial effects of the present invention compared with the prior art are:

[0024] (1) The present invention predicts the reachability of the flight target orbit based on the real-time propellant remaining status of the system mass output. Under the premise of meeting the safety shutdown requirement, the satellite is switched to the target orbit to raise the apogee of the satellite, thereby reducing the propellant consumption caused by the satellite orbit change and improving the satellite's on-orbit life.

[0025] (2) The present invention predicts the remaining fuel by using the system mass output, thereby improving the utilization rate of the remaining propellant; the method has strong real-time calculation adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 The present invention is a flow chart of an intelligent shutdown method based on utilizing system quality output. DETAILED DESCRIPTION

[0027] The present invention proposes an intelligent shutdown method based on utilizing system quality output, such as Figure 1 As shown, the following steps are included:

[0028] (1) Obtain the remaining propellant mass output, unusable propellant mass, propellant consumption per second, and lift apogee shutdown time of the utilization system;

[0029] (2) Calculating the predicted operable time of the fuel and oxidizer in the remaining propellant according to the remaining propellant mass output of the utilization system, the unusable mass of the propellant, and the propellant consumption per second, respectively, to obtain the predicted operable time of the remaining propellant;

[0030] (3) Compare the predicted working time of the remaining propellant with the shutdown time at the lift apogee to determine whether the liquid rocket can fly to the lift apogee;

[0031] (4) Based on the judgment result, the semi-major axis corresponding to the lifting apogee or the semi-major axis corresponding to the standard apogee is selected to perform shutdown control.

[0032] The present invention will be further described below in conjunction with the embodiments.

[0033] Example 1

[0034] (1) Determine the input parameters.

[0035] Obtain the remaining propellant mass output of the utilization system, the unavailable propellant mass, the propellant consumption per second and the lift apogee shutdown time tk5T;

[0036] Among them, the remaining propellant mass output of the system includes: the remaining propellant mass M R , the remaining oxidant mass M Y ;

[0037] The unusable mass of propellant includes: the unusable mass of combustion agent Mhj_R 、Oxidant unusable mass M hj_Y ;

[0038] The propellant consumption per second includes: the standard consumption per second of the combustion agent M 75R 、Oxidant standard consumption per second M 75Y ;

[0039] (2) Determine the predicted working time T of the remaining propellant hj .

[0040] 1) Predicted working time of the combustion agent:

[0041] T hj_R =(M R -M hj_R ) / M 75R

[0042] 2) Predicted working time of oxidant:

[0043] T hj_Y =(M Y -M hj_Y ) / M 75Y

[0044] 3) Predicted working time of remaining propellant:

[0045]

[0046] (3) Determine whether the liquid rocket can fly to the apogee of lift and select the corresponding semi-major axis a.

[0047] The estimated working time T based on the remaining propellant hj The following judgment is made based on the lift apogee shutdown time tk5T:

[0048]

[0049] When the predicted working time of the remaining propellant is T hj When the shutdown time is greater than tk5T, the liquid rocket can fly to the apogee of the lift, and the semi-major axis a corresponding to the apogee of the lift is used. T Carry out subsequent shutdown control; when the predicted working time T of the remaining propellant is hj When the shutdown time is less than tk5T, the liquid rocket cannot fly to the apogee of the lift, and the standard apogee corresponds to the semi-major axis a b Perform subsequent shutdown control.

[0050] The present application provides a computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions, and when the computer instructions are executed on a computer, the computer executes Figure 1The method described.

[0051] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the present application may adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage and optical storage, etc.) that contain computer-usable program code.

[0052] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0053] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0054] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0055] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

[0056] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. An intelligent shutdown method based on utilizing system quality output, characterized in that: The following steps are involved: Obtain the remaining propellant mass output of the utilization system, the unavailable propellant mass, the propellant consumption per second and the lift apogee shutdown time; The predicted operable time of the combustion agent and the oxidizer in the remaining propellant is calculated respectively according to the remaining propellant mass output of the utilization system, the unusable mass of the propellant and the propellant consumption per second, so as to obtain the predicted operable time of the remaining propellant; Compare the predicted working time of the remaining propellant with the shutdown time of the lift apogee to determine whether the liquid rocket can fly to the lift apogee; According to the judgment result, the semi-major axis corresponding to the lifting apogee or the semi-major axis corresponding to the standard apogee is selected to perform shutdown control.

2. The intelligent shutdown method based on utilizing system quality output according to claim 1, characterized in that: The remaining propellant mass output of the utilization system includes: the remaining propellant mass M R , the remaining oxidant mass M Y .

3. The intelligent shutdown method based on utilizing system quality output according to claim 2, characterized in that: The unusable mass of the propellant includes: the unusable mass of the combustion agent M hj_R 、Oxidant unusable mass M hj_Y .

4. The intelligent shutdown method based on utilizing system quality output according to claim 3, characterized in that: The propellant consumption per second includes: the standard consumption per second of the combustion agent M 75R 、Oxidant standard consumption per second M 75Y .

5. The intelligent shutdown method based on utilizing system quality output according to claim 4, characterized in that: The predicted working time of the combustion agent is: Thj_R=(M R -Mhj_ R ) / M 75R 。 6. The intelligent shutdown method based on utilizing system quality output according to claim 5, characterized in that: The predicted working time of the oxidant is: T hj_Y =(M Y -M hj_Y ) / M 75Y 。 7. The intelligent shutdown method based on utilizing system quality output according to claim 6, characterized in that: The predicted working time of the remaining propellant is:

8. The intelligent shutdown method based on utilizing system quality output according to claim 7, characterized in that: The method for selecting the semi-major axis corresponding to the lifting apogee or the semi-major axis corresponding to the standard apogee to perform shutdown control is: When the predicted working time of the remaining propellant is T hj When the shutdown time is greater than tk5T, the liquid rocket can fly to the apogee of the lift, and the semi-major axis a corresponding to the apogee of the lift is used. T Shutdown control is performed; when the predicted working time T of the remaining propellant is hj When the shutdown time is less than tk5T, the liquid rocket cannot fly to the apogee of the lift, and the standard apogee corresponds to the semi-major axis a b Perform shutdown control.

9. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 8 are implemented.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 8 are implemented.

Images