Ground support verification method for air supply strategy of buffer air capacity of air cooling system

Abstract

A ground support verification method for a buffer air capacity air supply strategy of an air cooling system belongs to the technical field of satellite propulsion systems, and comprises the following steps: a ground simulation system collects execution mechanism information output by a satellite; the ground simulation system collects the working time of an attitude and orbit control thruster and a pressure air supply control electromagnetic valve used by the cold air system; the ground simulation system calculates the consumption amount and the supplement amount of the working medium gas in the gas capacitor in each period through the working duration; the ground simulation system calculates the current air capacity pressure and the pressure variation; the ground simulation system performs fault simulation and fault pressure setting; the ground simulation system converts the pressure variation into a voltage value for output, and the satellite system receives the voltage value for pressure conversion and telemetering output; the ground simulation system calculates star attitude information through a control moment generated by air injection, generates sensor information through the star attitude information, and sends the sensor information to a satellite system to form whole data interaction and verification.

Description

Technical Field

[0001] This invention relates to a ground support verification method for a buffer gas capacity replenishment strategy for a cold air system, belonging to the technical field of satellite propulsion systems. Background Technology

[0002] For long-life satellites employing cooled gas propulsion systems, high-pressure gas is typically carried and multi-stage decompression is used. Maintaining the pressure of the buffer gas reservoir within a certain range is crucial for ensuring stable output from the cooled gas thruster. Therefore, verifying the correctness of the onboard buffer gas reservoir replenishment strategy and comprehensively simulating the gas reservoir's operation under normal and various fault conditions is extremely important. Summary of the Invention

[0003] The technical problem to be solved by this invention is to overcome the shortcomings of the prior art, comprehensively simulate the gas capacity operation of a long-life satellite cooling system under normal and various fault conditions, and verify the correctness of the satellite-end gas replenishment strategy.

[0004] The objective of this invention is achieved through the following technical solutions:

[0005] A ground support verification method for a buffer gas capacity replenishment strategy for a cooling system includes:

[0006] The signal acquisition unit module acquires actuator information output by the satellite;

[0007] The signal acquisition unit module accurately acquires the working time of the attitude control thruster and the gas capacity replenishment control solenoid valve used in the air conditioning system.

[0008] The signal acquisition unit module calculates the consumption and replenishment of the working gas in the gas container for each cycle based on the working time.

[0009] The current gas pressure and pressure change are calculated using the gas pressure simulation calculation module.

[0010] The gas capacity fault module enables fault simulation, fault pressure setting, and other operational settings.

[0011] Through high-precision D / A conversion, the pressure value is converted into a voltage value for output. The satellite system receives the voltage value, converts it into a pressure value, and outputs it remotely.

[0012] The dynamic model module calculates the attitude information of the satellite by using the control torque generated by the jet, and the ground simulation system generates sensor information from the attitude information and sends it to the satellite system, forming the entire data interaction and verification process.

[0013] Preferably, the signal acquisition unit module accurately acquires the working time of the attitude control thruster and the gas capacity replenishment control solenoid valve:

[0014] The signal acquisition unit module collects the working time of the attitude and orbit control thruster and the air capacity replenishment control solenoid valve.

[0015] The effective working time of the attitude control thruster and the air capacity replenishment solenoid valve includes both the partially open and fully open states of the solenoid valve.

[0016] Preferably, the effective operating time of the attitude control thruster and the air capacity replenishment solenoid valve includes:

[0017] The ground simulation mission runs on a control cycle of 10ms.

[0018] In a simulation task, the attitude control thruster and the gas capacity replenishment solenoid valve were completed from opening to full power operation. The working time t of the solenoid valve from 0 flow to full flow was collected in real time, the process of gas from zero to full was monitored, and the gas flow rate was calculated.

[0019] The control torque generated by the initial flow rate is incorporated into the control calculation;

[0020] The faster the signal acquisition unit module acquires data, the more accurate the jet volume calculated in the simulation task will be.

[0021] Preferably, the gas pressure model in the gas capacity simulation module is built as follows:

[0022] The gas content in the gas container includes three parts: the amount of gas present in the gas container, the amount of gas output for control when the air conditioning system is working, and the amount of gas supplemented by the upstream system when the air conditioning system is working.

[0023] By building a gas capacity model, the real-time pressure of the gas capacity during each control cycle is calculated using gas flow rate.

[0024] Preferably, the gas capacity simulation module incorporates a fault model, which can simulate fault conditions; the fault pressure and the actual pressure are calculated independently.

[0025] Preferably, the pressure output module uses a high-precision D / A converter to convert the pressure value in the cold air buffer gas container into a 0-5V analog quantity, which is then output to the onboard control unit.

[0026] Compared with the prior art, the present invention has the following advantages:

[0027] (1) The method of the present invention optimizes the electromagnetic valve model in the air conditioning system, achieving the advantages of real-time accuracy.

[0028] (2) The method of the present invention can simulate the real situation of gas in the gas container.

[0029] (3) The method of the present invention can simulate faults such as on-board thrusters and pressure, and can accurately cover various fault modes.

[0030] (4) The method of the present invention models the cold gas buffer gas capacity based on the working time of the thruster and the cold gas replenishment solenoid valve, comprehensively simulates the working conditions of the gas capacity under normal and various fault conditions, and verifies the correctness of the satellite end replenishment strategy. Attached Figure Description

[0031] Figure 1 This is a flowchart illustrating the method of the present invention.

[0032] Figure 2 A simplified diagram of the jetting time for the solenoid valve. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0034] A ground support verification method for a buffer gas capacity replenishment strategy for a cooling system, such as Figure 1 As shown, it includes:

[0035] The ground simulation system's signal acquisition unit module acquires actuator information output from the satellite;

[0036] The ground simulation system's signal acquisition unit module accurately acquires the working time of the attitude control thruster, orbit control thruster, and pressure replenishment control solenoid valve used in the air conditioning system.

[0037] The ground simulation system's signal acquisition unit module calculates the consumption and replenishment of the working gas in the gas container for each cycle based on the working time.

[0038] The gas pressure simulation calculation module of the ground simulation system converts the consumption and replenishment of working gas in the gas container in each cycle into the current gas container pressure and pressure change.

[0039] The ground simulation system uses the gas capacity simulation module to simulate faults and set fault pressures and other working conditions.

[0040] Pressure is converted into voltage through a pressure conversion relationship, and the voltage value is output through a high-precision D / A digital-to-analog converter chip. The satellite system receives the voltage value, performs pressure conversion, and outputs the telemetry value.

[0041] The ground simulation system's dynamic model module calculates the satellite's attitude information using the control torque generated by jet propulsion. The ground simulation system then generates sensor information based on this attitude information and sends it to the satellite system, thus forming the entire data interaction and verification process.

[0042] In the above-mentioned ground support verification method for the air supply strategy of the cooling system buffer gas capacity, the ground simulation system signal acquisition unit collects the following data from the attitude control thruster, orbit control thruster, and pressure replenishment control solenoid valve:

[0043] The ground simulation mission runs on a control cycle of 10ms.

[0044] The ground simulation system signal acquisition unit module collects the working time of all thrusters and pressure replenishment control solenoid valves on the satellite in real time.

[0045] The working characteristics of the thruster and the pressure replenishment control solenoid valve are modeled. Let T1 be the jet rise time, T2 be the jet stabilization time, T3 be the jet descent time, and T be the equivalent working time. The equivalent working time of the original thruster model is determined by the hardware. For example, if the comparison level is set to V = 15V in the hardware, the actual voltage of the output pulse width of the on-board thruster and pressure replenishment control solenoid valve is h = 30V. If the signal acquisition unit module of the ground simulation system acquires the voltage of the output pulse width of the on-board thruster and pressure replenishment control solenoid valve exceeding 15V, then the output pulse width of the thruster and pressure replenishment control solenoid valve is considered valid, and its equivalent output pulse width T is T = (T1*1 / 2 + T2 + T3*1 / 2)h.

[0046] The attitude control thruster, orbit control thruster, and pressure replenishment control solenoid valve all require time to operate and are not linearly variable models. Even before the solenoid valve is fully open, there is already an output pulse width and flow rate. Therefore, the thruster and pressure replenishment control solenoid valve are remodeled, and real-time data is collected from when the thruster and pressure replenishment control solenoid valve are not fully open to when they are fully open. The jet time is recorded in real time, and then the flow rate is calculated.

[0047] Real-time data acquisition is performed using an FPGA, with an acquisition time interval of Δt = 10ms per simulation cycle. Data acquisition begins at the start of each acquisition time interval, starting when the attitude control thruster, orbit control thruster, and pressure replenishment control solenoid valve begin operation. Jet pulse width calculations are performed, and the specific relationship between acquisition time and flow rate is as follows: Figure 2 As shown.

[0048] The above model yields the following:

[0049] a) The equivalent pulse width of a single attitude control thruster in one simulation cycle is T n Each simulation cycle is Δt = 10, and the pulse width voltage of the attitude control thruster acquired in the current cycle is h. n h n-1 The pulse width voltage of the attitude control thruster acquired in the previous cycle is: The equivalent pulse width of the attitude control thruster in one simulation cycle is:

[0050]

[0051] The equivalent pulse width T of one simulation cycle for all working attitude control thrusters z The equivalent pulse widths for one simulation cycle of each thruster are summed.

[0052] b) The equivalent pulse width of a single orbital control thruster in one simulation cycle is T g The duration of each simulation cycle remains constant, and the pulse width voltage of the orbital control thruster acquired in the current cycle is h. g h g-1 The pulse width voltage of the orbital control thruster collected in the previous cycle is: The equivalent pulse width of the orbital control thruster in one simulation cycle is:

[0053]

[0054] c) The equivalent pulse width of the pressure replenishment control solenoid valve within one simulation cycle is T. BC The duration of each simulation cycle remains constant, and the pulse width voltage of the pressure replenishment control solenoid valve acquired in the current cycle is h. BC h BC-1 The pulse width voltage of the pressure replenishment control solenoid valve collected in the previous cycle is: The equivalent pulse width of the pressure replenishment control solenoid valve in one simulation cycle is:

[0055]

[0056] The total working fluid in the gas container during a simulation cycle is equal to the original working fluid plus the supplementary working fluid brought by the operation of the solenoid valve controlled by the gas container pressure, minus the working fluid consumed by the attitude and track control solenoid valves.

[0057] Based on the replenished and consumed gas volume, a model is constructed for the cold gas buffer gas volume, denoted as P, where P is the internal pressure value of the gas volume, P0 is the initial pressure value of the gas volume, and K is the value of the gas volume. mzk K is the flow conversion coefficient of the attitude control thruster. mgk K is the flow conversion coefficient for the orbital control thruster. myk K is the flow conversion coefficient of the air replenishment solenoid valve. mp Let be the gas-capacity mass pressure conversion coefficient, then the gas-capacity working model can be established as follows:

[0058] P = P0 + K mp ×(K myk ×T BC -K mzk ×T z -K mgk ×T g )

[0059] Using the pulse width of consumed working fluid and the pulse width of replenished working fluid calculated by the signal acquisition unit module of the ground simulation system, the pressure value inside the gas container can be calculated in real time based on the above gas container working model.

[0060] The attitude control thruster, orbit control thruster, and pressure replenishment control solenoid valve can be opened and closed through the acquisition unit module. The acquisition unit module also monitors the time after the pressure replenishment control solenoid valve is opened in real time, and simulates the on-orbit failure of the solenoid valve. When the acquisition unit module collects the failure of any solenoid valve, it calculates the corresponding gas consumption mass and failure time, and can monitor the failure time of the gas capacity system.

[0061] The analog values ​​of the gas pressure sensor can be set via a host computer to simulate the fault behavior of the pressure sensor. The fault pressure and the actual pressure are calculated separately. Pressure safety thresholds can be set. If the pressure exceeds the limit during the fault test, the acquisition unit will issue an alarm message.

[0062] The ground simulation system's pressure conversion module converts pressure into voltage through a pressure conversion relationship. The pressure output module outputs the pressure value to the satellite acquisition system. The pressure output module uses a high-precision D / A digital-to-analog converter chip, and the voltage output accuracy is better than 0.5%.

[0063] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0064] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A ground support verification method for a buffer gas capacity replenishment strategy in a cooling system, characterized in that, include: The ground simulation system collects actuator information output by the satellite; The ground simulation system collects the operating time of the attitude control thruster and pressure replenishment control solenoid valve used in the air conditioning system. The ground simulation system calculates the consumption and replenishment of the working gas in the gas container for each cycle based on the working time. The ground simulation system calculates the current gas volume pressure and pressure change; The ground simulation system performs fault simulation and fault pressure setting; The ground simulation system converts pressure changes into voltage values, and the satellite system receives the voltage values, converts them into pressure values, and outputs them remotely. The ground simulation system calculates the attitude information of the celestial body by using the control torque generated by the jet, and then generates sensor information based on the attitude information of the celestial body and sends it to the satellite system, thus forming the entire data interaction and verification process.

2. The ground support verification method for the buffer gas capacity replenishment strategy of the cooling system according to claim 1, characterized in that, The ground simulation system collects data on the attitude and orbit control thruster and the pressure gas capacity replenishment control solenoid valve as follows: The ground simulation mission runs according to a predetermined control cycle. The ground simulation system collects the working time of all thrusters and pressure replenishment control solenoid valves on the satellite in real time, and then calculates the equivalent pulse width of a single attitude control thruster in one simulation cycle, the equivalent pulse width of a single orbit control thruster in one simulation cycle, and the equivalent pulse width of the pressure replenishment control solenoid valve in one simulation cycle. Using the equivalent jet pulse width, the pressure value within the gas container is calculated in real time based on the gas container working model.

3. The ground support verification method for the cold air system buffer gas capacity replenishment strategy according to claim 2, characterized in that, The equivalent pulse width of a single attitude control thruster in one simulation cycle is: The simulation period is Δt, and the pulse width voltage of the attitude control thruster acquired in the current period is h. n h n-1 This is the pulse width voltage of the attitude control thruster collected in the previous cycle.

4. The ground support verification method for the cold air system buffer gas capacity replenishment strategy according to claim 3, characterized in that, The equivalent pulse width of a single orbital control thruster in one simulation cycle is: The pulse width voltage of the orbital control thruster acquired in the current cycle is h. g h g-1 This is the pulse width voltage of the orbital control thruster collected in the previous cycle.

5. The ground support verification method for the cold air system buffer gas capacity replenishment strategy according to claim 4, characterized in that, The equivalent pulse width of the pressure-replenishing control solenoid valve within one simulation cycle is T. BC The pulse width voltage of the pressure replenishment control solenoid valve collected in the current cycle is h. BC h BC-1 The pulse width voltage of the solenoid valve is used to control the pressure replenishment control from the previous cycle.

6. The ground support verification method for the cold air system buffer gas capacity replenishment strategy according to claim 5, characterized in that, The working model of gas capacity is as follows: P=P0+K mp ×(K myk ×T BC -K mzk ×T z -K mgk ×T g ) P is the internal pressure of the gas container, P0 is the initial pressure of the gas container, and K is the pressure value inside the gas container. mzk K is the flow conversion coefficient of the attitude control thruster. mgk K is the flow conversion coefficient for the orbital control thruster. myk K is the flow conversion coefficient of the air replenishment solenoid valve. mp This is the gas volume mass pressure conversion coefficient.

7. The ground support verification method for the cold air system buffer gas capacity replenishment strategy according to claim 1, characterized in that, In a simulation task, the attitude and orbit control thruster and the gas capacity replenishment solenoid valve were completed from opening to full power operation. The working time t of the solenoid valve from 0 flow to full flow was collected in real time, the process of gas from zero to full was monitored, and the gas flow rate was calculated.

8. The ground support verification method for the cold air system buffer gas capacity replenishment strategy according to claim 1, characterized in that, The gas content in the gas container includes three parts: the amount of gas present in the gas container, the amount of gas output for control when the air conditioning system is working, and the amount of gas supplemented by the upstream system when the air conditioning system is working.

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