Temperature control method and system for propulsion system based on satellite autonomous maneuvering mission

Abstract

The present invention provides a propulsion system temperature control method and system based on a satellite autonomous maneuvering mission, comprising: step 1: sending a thruster head temperature control on request or a thruster head temperature control off request according to the autonomous maneuvering mission window; step 2: analyzing heater fault diagnosis conditions through a ground system and setting a thruster head temperature control channel identifier; step 3: setting a thruster head temperature control program control prohibition identifier through an onboard integrated electronic computer, and based on the program control identifier, sending a thruster head temperature control on command chain, sending a thruster head temperature control off command chain, or not responding to the heater temperature control on / off request; step 4: setting an onboard temperature control on-time limit, wherein the thruster head temperature control advance on-time is modified according to the satellite's on-orbit ambient temperature. The present invention, based on a propulsion system temperature control design for autonomous maneuvering missions, solves the problem of cold starting of the propulsion system when the satellite autonomously completes attitude and orbit maneuvers on-orbit, thereby ensuring the safety of the satellite's on-orbit operation.

Description

Technical Field

[0001] The present invention relates to the field of autonomous temperature control technology for spacecraft, and specifically to a temperature control method and system for a propulsion system based on an autonomous maneuvering mission of a satellite, and in particular to a temperature control method for a propulsion system based on an autonomous maneuvering mission of a low-orbit, low-inclination satellite. Background Art

[0002] With the continuous development of aerospace technology, higher requirements are placed on satellite detection areas. The low-latitude areas in the north and south have gradually become hot spots for detection. In order to meet the high time revisit requirements with a smaller number of satellites, the demand for the development of inclined orbit satellites is increasing.

[0003] The most notable feature of inclined orbit satellites is that the angle between the solar vector and the orbital plane is constantly changing. The lighting conditions of the entire satellite are complex, and the satellite has no fixed heat dissipation surface, which makes the thermal control design of the entire satellite very difficult. The fixed-wing single-axis one-dimensional driven solar sail panels receive a short period of illumination and cannot meet the energy supply demand. The satellite needs to perform frequent autonomous attitude maneuvers to ensure energy. During the satellite attitude maneuvers, the propulsion system needs to be in an appropriate operating temperature range, otherwise the propulsion system will fail to start or the single unit will be damaged.

[0004] Low-orbit satellite remote sensing instruments can obtain better image data when the orbit is 300km to 400km high. However, at the orbital altitude of 300km to 400km, the satellite is subject to large atmospheric resistance. During the peak year of solar activity, the average atmospheric density can reach 5.0e~11kg / m3, which is 10 to 100 times that of a sun-synchronous orbit satellite. The satellite needs to frequently perform orbital control tasks. When the satellite orbital altitude is maintained at ±0.2km, the frequency of orbital control reaches 2 times a day. This also requires the propulsion system to work and be in a suitable operating temperature range, otherwise it will also cause the propulsion system to fail to start or the single unit to be damaged. The temperature control method of the propulsion system based on the autonomous maneuvering mission of the low-orbit low-inclination satellite in this application can solve the above problems.

[0005] Patent publication number CN111232246B discloses a comprehensive optimization design method based on the lighting conditions of inclined-orbit satellites. The method includes the following steps: calculating the solar vector, derived from onboard orbital parameters or measured by solar sensors, and calculating the solar altitude angle, using the solar altitude angle as a parameter to characterize changes in the satellite's energy supply and heat dissipation surface; determining a flight plan, developing a satellite turnaround flight plan that takes into account both the satellite's energy supply and the design of a fixed heat dissipation surface; determining the satellite's flight polarity, determining the satellite's flight polarity based on the direction of the solar vector's change; determining suitability, determining a shadow zone determination method and the suitability of the turnaround flight plan in shadow zones; and selecting the basis for selecting the turnaround flight time. However, the patent document does not describe methods for controlling the propulsion system's operating temperature.

[0006] Patent document CN111114833B discloses a method and system for orbit maintenance and relay application compatibility based on autonomous mission planning. The method includes: configuring the data transmission relay to operate in a cyclical mode, organizing work instructions in the form of a job table; noting the job table to the onboard computer, which calculates the data transmission relay's busy / idle status and the duration of the busy / idle status, and deletes the job table or inserts a new one based on ground application conditions; the onboard computer broadcasts the relay's busy / idle status and duration to the attitude and orbit control subsystem; the attitude and orbit control subsystem completes autonomous orbit maintenance control within a sufficient period of idle time for the data transmission relay based on orbital decay and the data transmission relay's operating status, and issues a completion indicator. The ground then determines the orbit based on the completion indicator. However, the patent document does not describe the operation of the thruster head heater during orbit control.

[0007] Patent document CN104469998A discloses a method for protecting and installing heating tape for a satellite propulsion system pipeline. The method involves welding the lead wires of the heating tape and attaching an insulating film, with both ends of the insulating film being longer than the winding length of the heating tape. Single-sided polyimide tape is then used to secure the heating tape starting from the lead wires. A thin layer of silicone rubber is evenly applied to the adhesive surface of the tape. The silicone rubber is cured, and according to a predetermined heating circuit design, the heating circuit is welded with wires. Double-layer heat shrink tubing is then applied and heat-shrunk. A certain length of the heating circuit lead wire is reserved at the pipeline adapter. However, the patent document does not describe autonomous heating design for satellites in orbit.

[0008] Patent publication number CN106467176A discloses a temperature control method for a satellite propulsion module. This method involves installing the propulsion system in a separate module. The design employs a multi-layer insulation coating on the entire module exterior; several thrusters are also covered with multi-layer insulation outside the module; a compensating heater is designed to maintain the temperature of the solenoid valves; and multi-layer insulation is applied to the external piping and brackets. No thermal control is performed inside the module. This patent differs from the technical solution of the present application. Summary of the Invention

[0009] In view of the defects in the prior art, the purpose of the present invention is to provide a temperature control method and system for a propulsion system based on a satellite autonomous maneuvering mission.

[0010] According to the present invention, a temperature control method for a propulsion system based on a satellite autonomous maneuvering mission is provided, comprising:

[0011] Step 1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, it sends a thruster head temperature control on request through program control. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, it sends a thruster head temperature control off request through program control.

[0012] Step 2: Analyze the heater fault diagnosis through the ground system and set the thruster head temperature control channel identifier;

[0013] Step 3: Setting a program control permission / prohibition flag for the thruster head temperature control by the onboard integrated electronic computer; when the program control flag is permission and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head temperature control on command chain; when the program control flag is permission and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head temperature control off command chain; when the program control flag is prohibition, the onboard integrated electronic computer does not respond to the heater temperature control on / off request;

[0014] Step 4: Set the on-board temperature control startup time limit. The thruster head temperature control advance startup time is modified according to the satellite's on-orbit ambient temperature. When the attitude and orbit control subsystem working status changes, the new working status is sent to the on-board integrated electronic computer.

[0015] Preferably, in step 1, the autonomous maneuvering task window includes a track control window and an attitude maneuvering window;

[0016] The orbit control window is established in combination with the current orbit altitude and the orbit control threshold; the attitude maneuvering window is established according to the satellite solar altitude angle and the change of the satellite solar altitude angle.

[0017] Preferably, the solar altitude angle reaches a set threshold range, which is the attitude maneuvering window.

[0018] Preferably, in step 2, the thruster head has six temperature control channels, three main temperature control channels and three backup temperature control channels;

[0019] The three main temperature control channels are the first main temperature control channel, the second main temperature control channel, and the third main temperature control channel; the three standby temperature control channels are the first standby temperature control channel, the second standby temperature control channel, and the third standby temperature control channel;

[0020] The onboard program control software controls one of the three main temperature control channels and one of the three backup temperature control channels;

[0021] The satellite is set up as the second temperature control channel in orbit.

[0022] Preferably, the onboard software identifies the heater program-controlled channel as 0x0B1B, and program-controls the second main temperature control channel and the second standby temperature control channel;

[0023] When the heater program control channel identifier is 0x0717, the program control temperature controls the first main temperature control channel and the first standby temperature control channel;

[0024] When the heater program control channel identifier is 0x0F1F, the program control temperature controls the third main temperature control channel and the third standby temperature control channel.

[0025] Preferably, in step 3, when the identifier is 0xAAAA, it indicates permission, and when the identifier is 0x5555, it indicates prohibition, the prohibition identifier is set by the ground annotation instruction;

[0026] When the program control flag is enabled and a thruster head temperature control start request is received, the corresponding thruster head temperature control start instruction chain is sent according to the heater program control channel flag; the heater program control channel flag is 0x0B1B, 0x0717 or 0x0F1F;

[0027] When the program control flag is enabled and a thruster head temperature control shutdown request is received, the corresponding thruster head temperature control shutdown instruction chain is sent according to the heater program control channel flag; the heater program control channel flag is 0x0B1B, 0x0717 or 0x0F1F;

[0028] When the program control is the prohibition flag 0x5555, the onboard program control software does not respond to the heater temperature control switch request.

[0029] Preferably, in step 4, the thruster head temperature control is set to open-loop control.

[0030] Preferably, the temperature control start-up time limit is up to 14 orbital cycles, and the on-board integrated electronic computer sets the thruster head temperature control advance start-up time to 3 hours.

[0031] Preferably, in step 4, the temperature control request is transmitted via the 1553B data bus.

[0032] The present invention also provides a propulsion system temperature control system based on the autonomous maneuvering mission of the angular satellite, comprising the following modules:

[0033] Module M1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, it sends a thruster head temperature control on request through program control. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, it sends a thruster head temperature control off request through program control.

[0034] Module M2: Analyze the heater fault diagnosis through the ground system, set the thruster head temperature control channel identifier, and set the satellite to the second temperature control channel while in orbit;

[0035] Module M3: Setting the thruster head temperature control program control permission / prohibition flag via the onboard integrated electronic computer. When the program control flag is permission and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head temperature control on command chain. When the program control flag is permission and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head temperature control off command chain. When the program control flag is prohibition, the onboard integrated electronic computer does not respond to the heater temperature control on / off request.

[0036] Module M4: Sets the on-board temperature control startup time limit. The thruster head temperature control early startup time is modified according to the satellite's on-orbit ambient temperature. When the attitude and orbit control subsystem working status changes, the new working status is sent to the on-board integrated electronic computer.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. Based on the design requirements of the entire satellite and in the context of high-frequency autonomous maneuvering missions, this invention proposes a temperature control method for the propulsion system based on the autonomous maneuvering missions of low-orbit, low-inclination satellites. This method solves the cold start problem of the propulsion system and ensures the service life of the product.

[0039] 2. The temperature control design of the propulsion system based on the autonomous maneuvering mission solves the problem of cold start of the propulsion system when the satellite completes autonomous attitude and orbit maneuvers on orbit, ensuring the safety of the satellite's on-orbit operation.

[0040] 3. The present invention uses the establishment of the satellite maneuvering window as an input condition, determines the number and time of heater switch paths according to the heating power and efficiency of the propulsion system, and is based on the interaction between the integrated electronic subsystem and the attitude and orbit control subsystem to solve the problem of cold start of the propulsion system when the satellite autonomously completes attitude and orbit maneuvers in orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0042] Figure 1 This is a temperature control flow chart for the propulsion system based on the high-frequency autonomous maneuvering mission of low-frequency and low-inclination satellites. DETAILED DESCRIPTION

[0043] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0044] Example 1:

[0045] like Figure 1 As shown, this embodiment provides a propulsion system temperature control method based on a satellite autonomous maneuvering mission, including:

[0046] Step 1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, it sends a thruster head temperature control on request through program control. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, it sends a thruster head temperature control off request through program control. The autonomous maneuvering mission window includes an orbit control window and an attitude maneuvering window. The orbit control window is established in combination with the current orbit altitude and the orbit control threshold. The attitude maneuvering window is established based on the satellite solar altitude angle and the change in the satellite solar altitude angle. When the solar altitude angle reaches the set threshold range, it is the attitude maneuvering window.

[0047] Step 2: Analyze the heater fault diagnosis through the ground system and set the thruster head temperature control channel identifier. The thruster head has six temperature control channels, including three main temperature control channels and three backup temperature control channels. The three main temperature control channels are the first main temperature control channel, the second main temperature control channel, and the third main temperature control channel. The three backup temperature control channels are the first backup temperature control channel, the second backup temperature control channel, and the third backup temperature control channel. The onboard program control software programs one of the three main temperature control channels and one of the three backup temperature control channels. When the satellite is in orbit, the second temperature control channel is set. The onboard software identifies the heater program control channel as 0x0B1B and program controls the second main temperature control channel and the second backup temperature control channel. When the heater program control channel identifier is 0x0717, the first main temperature control channel and the first backup temperature control channel are program controlled. When the heater program control channel identifier is 0x0F1F, the third main temperature control channel and the third backup temperature control channel are program controlled.

[0048] Step 3: Set the thruster head temperature control program control prohibition flag through the onboard integrated electronic computer. When the program control flag is allowed and a thruster head temperature control opening request is received, the onboard integrated electronic computer sends a thruster head temperature control opening instruction chain. When the program control flag is allowed and a thruster head temperature control closing request is received, the onboard integrated electronic computer sends a thruster head temperature control closing instruction chain. When the program control flag is prohibited, the onboard integrated electronic computer does not respond to the heater temperature control switch request. When the flag is 0xAAAA, it indicates permission, and when the flag is 0x5555, it indicates prohibition, the prohibition flag is transmitted through the ground Note: After the command setting is completed, when the program control flag is allowed and a thruster head temperature control on request is received, the corresponding thruster head temperature control on command chain is sent according to the heater program control channel flag. The heater program control channel flag is 0x0B1B, 0x0717 or 0x0F1F. When the program control flag is allowed and a thruster head temperature control off request is received, the corresponding thruster head temperature control off command chain is sent according to the heater program control channel flag. The heater program control channel flag is 0x0B1B, 0x0717 or 0x0F1F. When the program control flag is prohibited 0x5555, the on-board program control software does not respond to the heater temperature control on / off request.

[0049] Step 4: The thruster head temperature control is set to open-loop control, and the on-board temperature control start-up time limit is set. The thruster head temperature control advance start-up time is modified according to the satellite's on-orbit ambient temperature. When the attitude and orbit control subsystem working state changes, the new working state is sent to the on-board integrated electronic computer. The temperature control start-up time limit is a maximum of 14 orbital cycles. The on-board integrated electronic computer sets the thruster head temperature control advance start-up time to 3 hours. The temperature control request is transmitted via the 1553B data bus.

[0050] Example 2:

[0051] This embodiment also provides a propulsion system temperature control system based on the corner satellite autonomous maneuvering mission, including the following modules:

[0052] Module M1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, it sends a thruster head temperature control on request through program control. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, it sends a thruster head temperature control off request through program control.

[0053] Module M2: Analyze the heater fault diagnosis through the ground system, set the thruster head temperature control channel identifier, and set the satellite to the second temperature control channel while in orbit;

[0054] Module M3: Setting the thruster head temperature control program control permission / prohibition flag via the onboard integrated electronic computer. When the program control flag is permission and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head temperature control on command chain. When the program control flag is permission and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head temperature control off command chain. When the program control flag is prohibition, the onboard integrated electronic computer does not respond to the heater temperature control on / off request.

[0055] Module M4: Sets the on-board temperature control startup time limit. The thruster head temperature control early startup time is modified according to the satellite's on-orbit ambient temperature. When the attitude and orbit control subsystem working status changes, the new working status is sent to the on-board integrated electronic computer.

[0056] Example 3:

[0057] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1 and Embodiment 2.

[0058] This embodiment provides a temperature control method for a propulsion system based on an autonomous maneuvering mission of a low-orbit, low-inclination satellite, including the following steps:

[0059] Step 1: When the attitude and orbit control subsystem establishes the autonomous maneuvering mission window, the program control sends a thruster head temperature control opening request. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, the program control sends a thruster head temperature control closing request.

[0060] Step 2: The ground system sets the thruster head temperature control channel identifier based on the heater fault diagnosis. The satellite defaults to the second channel temperature control when in orbit.

[0061] Step 3: The onboard integrated electronic computer sets the thruster head temperature control program control permission / prohibition flag. When the program control flag is allowed and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head temperature control on command chain. When the program control flag is allowed and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head temperature control off command chain. When the program control flag is prohibited, the onboard integrated electronic computer does not respond to the heater temperature control on / off request.

[0062] Step 4: Set a temperature control activation time limit onboard, with a maximum of 14 orbital cycles. The thruster head temperature control activation time is adjustable based on the satellite's on-orbit ambient temperature and is set to 3 hours by default. Temperature control requests are transmitted via the 1553B data bus. When the attitude and orbit control subsystem's operating status changes, the new status is sent to the integrated electronic computer.

[0063] Step 1 includes: the satellite autonomous maneuvering mission window includes an orbit control window and an attitude maneuvering window. The orbit control window is established based on the current orbit altitude and the orbit control threshold. The attitude maneuvering window is established based on the satellite's solar altitude angle and its changes. When the solar altitude angle falls within the set threshold range, the attitude maneuvering window is established. After the window is established, a thruster head temperature control on request is sent. After the autonomous maneuvering mission is completed, a thruster head temperature control off request is sent.

[0064] Step 2 includes: the ground system sets the thruster head temperature control channel identifier based on the heater fault diagnosis. The satellite has a total of six thruster head temperature control channels, three main and three backup channels. The onboard program control software only needs to program two temperature control channels, namely the main and backup channels. The onboard software defaults to the heater program control channel identifier of 0x0B1B, which indicates the second program control main and backup temperature control channel. When the heater program control channel identifier is 0x0717, it indicates the first program control main and backup temperature control channel. When the heater program control channel identifier is 0x0F1F, it indicates the third program control main and backup temperature control channel.

[0065] The step three includes: the on-board integrated electronic computer sets the thruster head temperature control program control permission and prohibition flag, when the flag bit 0xAAAA indicates permission, when the flag bit 0x5555 indicates prohibition. The permission and prohibition flags are set by the ground injection instruction. When the program control flag is permission and a thruster head temperature control on request is received, the corresponding thruster head temperature control on instruction chain is sent according to the heater program control channel flag (0x0B1B or 0x0717 or 0x0F1F). When the program control flag is permission and a thruster head temperature control off request is received, the corresponding thruster head temperature control off instruction chain is sent according to the heater program control channel flag (0x0B1B or 0x0717 or 0x0F1F). When the program control is the prohibition flag 0x5555, the on-board program control software does not respond to the heater temperature control switch request;

[0066] Step 4 includes: The thruster head temperature control is open-loop, with an onboard temperature control activation time limit set to a maximum of 14 orbital cycles. The onboard integrated electronic computer sets a default 3-hour pre-activation time for the thruster head temperature control, which can be modified based on the satellite's on-orbit ambient temperature. The temperature control request computer of the attitude and orbit control subsystem communicates with the integrated electronic computer via the 1553B data bus. When the attitude and orbit control subsystem's operating status changes, the new operating status is transmitted to the integrated electronic computer.

[0067] 0x0717, 0x0F1F, 0xAAAA, and 0x5555 are identifiers designed according to needs during the research and development process.

[0068] Example 4:

[0069] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1 and Embodiment 2.

[0070] This embodiment uses the establishment of a satellite maneuvering window as an input condition, determines the number and timing of heater switching paths based on the propulsion system heating power and efficiency, and proposes a propulsion system temperature control method for autonomous maneuvering missions of low-orbit, low-inclination satellites based on the interaction between the integrated electronic subsystem and the attitude and orbit control subsystem. The method specifically includes the following steps:

[0071] Step S1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, the program control sends a thruster head temperature control on request. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, the program control sends a thruster head temperature control off request.

[0072] Step S2: The ground system sets the thruster head temperature control channel identifier based on the heater fault diagnosis. The satellite defaults to the second channel temperature control when in orbit.

[0073] Step S3: The onboard integrated electronic computer sets the thruster head heating program control permission / prohibition flag. When the program control flag is allowed and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head heater on command chain. When the program control flag is allowed and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head heater off command chain. When the program control flag is prohibited, the onboard integrated electronic computer does not respond to the heater on / off request.

[0074] Step S4: The duration of the thruster head temperature control start-up is based on the satellite's on-orbit ambient temperature and can be modified by a number of times. The default setting is 3 hours. The temperature control request is transmitted via the 1553B data bus. When the attitude and orbit control subsystem operating status changes, the new operating status is sent to the integrated electronic computer.

[0075] The step S1 includes: the satellite autonomous maneuvering mission window includes an orbit control window and an attitude maneuvering window. The orbit control window is established in combination with the current orbit altitude and the orbit control threshold. The nominal value of the average orbit altitude of a satellite in orbit is 407.00 km. The orbit control threshold is set to 0.20 km, that is, when the average orbit altitude is lower than 406.80 km, the orbit control window is established when eccentricity control is not considered. When eccentricity control is considered, the orbit control window is established at the apogee. According to the DTM78 and Msise90 atmospheric models, it is predicted that the maximum average atmospheric density in the peak year of the next solar activity cycle can reach 5.0e-11kg / m3. When the orbit control threshold is set to 0.20 km, orbit control is performed about twice a day in the peak year. After the orbit control maneuvering window is established, the attitude and orbit control subsystem sends a thruster head temperature control opening request to the integrated electronic subsystem, and sends a closing request after the maneuver is completed. The attitude maneuvering window is established based on the satellite's solar altitude angle and its changes. The default solar altitude angle is within the range of ±2° as the attitude maneuvering window. The orbital inclination of a satellite in orbit is 50.0°. According to the change of the satellite's solar altitude angle, it is about 28 days / time. After the attitude maneuvering window is established, the attitude and orbit control subsystem sends a thruster head temperature control opening request to the integrated electronic subsystem, and sends a closing request after the maneuver is completed.

[0076] Step S2 includes the following steps: The satellite has six thruster head temperature control channels, three each for primary and backup. By default, one of the primary and backup channels is always open while in orbit. This means one channel is always open for the primary and one for the backup. When an orbit control window or attitude maneuvering window is established, the onboard integrated electronic computer only needs to program one channel each for primary and backup temperature control, for a total of two channels. Fault diagnosis of the thruster temperature control channels is performed on the ground. If the temperature control channel is open, the thruster head temperature increases; if the temperature control channel is closed, the thruster head temperature decreases. This indicates that the temperature control channel is normal. The ground system sends thruster temperature control channel fault diagnosis results to the satellite via PCM notes. The note packet contains 0x0717, indicating the primary and backup temperature control channels 1, 0x0B1B, and 0x0F1F, respectively. The onboard integrated electronic computer (IC) sends the corresponding on / off command chain for each temperature control channel ID. For example, after a satellite is powered on, the default temperature control channel ID is 0x0B1B, indicating the primary and backup temperature control channels 2. This means that upon receiving a temperature control request, the IC sends the primary and backup heating channel 2 on / off command chain.

[0077] Step S3 includes setting the onboard thruster temperature control program flag to a "permit" flag. The "permit" flag is set by a ground-based command. The flag bit 0xAAAA indicates "permit" and the flag bit 0x5555 indicates "prohibit." When the flag bit is 0x5555, the integrated electronic computer does not respond to the propulsion system autonomous temperature control switch request sent by the attitude and orbit control subsystem. The default setting is "permit" during the initial satellite orbit entry and after powering off. The setting is set to "permit" after the satellite enters orbit and establishes a stable operating state.

[0078] Step S4 includes: The onboard thruster head temperature control is open-loop. To ensure the safety of the entire satellite's temperature control, a temperature control activation time limit is set onboard. The onboard integrated electronic computer software starts counting from the time it sends the temperature control on signal. Based on the premise that the low-inclination satellite does not communicate with the ground station for a maximum of 14 orbital periods T, the maximum temperature control activation time is 14 orbital periods T. When the integrated electronic computer software sends the temperature control off signal, the timer is reset. The onboard integrated electronic computer sets a default value of 3 hours for the thruster head temperature control pre-activation time, which can be modified based on the satellite's on-orbit ambient temperature. The attitude and orbit control subsystem computer communicates with the integrated electronic computer via the 1553B data bus. When the attitude and orbit control subsystem's operating state changes, the new operating state temperature control on / off request is sent to the integrated electronic computer.

[0079] The temperature control design of the propulsion system of the present invention is based on the autonomous maneuvering mission, which solves the problem of cold start of the propulsion system when the satellite completes attitude and orbit maneuvers autonomously in orbit, and ensures the safety of the satellite's in-orbit operation.

[0080] Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same functions of the system and its various devices, modules, and units provided by the present invention in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; the devices, modules, and units for implementing various functions can also be considered as both software modules implementing the method and structures within the hardware component.

[0081] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A temperature control method for a propulsion system based on a satellite autonomous maneuvering mission, characterized in that: include: Step 1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, it sends a thruster head temperature control on request through program control. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, it sends a thruster head temperature control off request through program control. Step 2: Analyze the heater fault diagnosis through the ground system and set the thruster head temperature control channel identifier; Step 3: Setting a program control permission / prohibition flag for the thruster head temperature control by the onboard integrated electronic computer; when the program control flag is permission and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head temperature control on command chain; when the program control flag is permission and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head temperature control off command chain; when the program control flag is prohibition, the onboard integrated electronic computer does not respond to the heater temperature control on / off request; Step 4: Set the on-board temperature control startup time limit. The thruster head temperature control advance startup time is modified according to the satellite's on-orbit ambient temperature. When the attitude and orbit control subsystem working status changes, the new working status is sent to the on-board integrated electronic computer.

2. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 1, characterized in that: In step 1, the autonomous maneuvering task window includes a track control window and an attitude maneuvering window; The orbit control window is established in combination with the current orbit altitude and the orbit control threshold; the attitude maneuvering window is established according to the satellite solar altitude angle and the change of the satellite solar altitude angle.

3. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 2, characterized in that: When the sun altitude angle reaches a set threshold range, it is the attitude maneuvering window.

4. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 1, characterized in that: In step 2, there are six temperature control channels in the thruster head, three main temperature control channels and three backup temperature control channels; The three main temperature control channels are the first main temperature control channel, the second main temperature control channel, and the third main temperature control channel; the three standby temperature control channels are the first standby temperature control channel, the second standby temperature control channel, and the third standby temperature control channel; The onboard program control software controls one of the three main temperature control channels and one of the three backup temperature control channels; The satellite is set up as the second temperature control channel in orbit.

5. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 4, characterized in that: The onboard software identifies the heater program control channel as 0x0B1B, and program controls the second main temperature control channel and the second backup temperature control channel; When the heater program control channel identifier is 0x0717, the program control temperature controls the first main temperature control channel and the first standby temperature control channel; When the heater program control channel identifier is 0x0F1F, the program control temperature controls the third main temperature control channel and the third standby temperature control channel.

6. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 5, characterized in that: In step 3, when the mark is 0xAAAA, it indicates permission, and when the mark is 0x5555, it indicates prohibition, the prohibition mark is set by the ground injection instruction; When the program control flag is enabled and a thruster head temperature control start request is received, the corresponding thruster head temperature control start instruction chain is sent according to the heater program control channel flag; the heater program control channel flag is 0x0B1B, 0x0717 or 0x0F1F; When the program control flag is enabled and a thruster head temperature control shutdown request is received, the corresponding thruster head temperature control shutdown instruction chain is sent according to the heater program control channel flag; the heater program control channel flag is 0x0B1B, 0x0717 or 0x0F1F; When the program control is the prohibition flag 0x5555, the onboard program control software does not respond to the heater temperature control switch request.

7. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 1, characterized in that: In step 4, the thruster head temperature control is set to open-loop control.

8. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 7, characterized in that: The maximum time limit for temperature control startup is 14 orbital cycles. The onboard integrated electronic computer sets the advance startup time of the thruster head temperature control to 3 hours.

9. The temperature control method for a propulsion system based on a satellite autonomous maneuvering mission according to claim 1, characterized in that: In step 4, the temperature control request is transmitted via the 1553B data bus.

10. A propulsion system temperature control system based on an autonomous maneuvering mission of an angular satellite, characterized in that: Includes the following modules: Module M1: When the attitude and orbit control subsystem establishes an autonomous maneuvering mission window, it sends a thruster head temperature control on request through program control. When the attitude and orbit control subsystem completes the autonomous maneuvering mission, it sends a thruster head temperature control off request through program control. Module M2: Analyze the heater fault diagnosis through the ground system, set the thruster head temperature control channel identifier, and set the satellite to the second temperature control channel while in orbit; Module M3: Setting the thruster head temperature control program control permission / prohibition flag via the onboard integrated electronic computer. When the program control flag is permission and a thruster head temperature control on request is received, the onboard integrated electronic computer sends a thruster head temperature control on command chain. When the program control flag is permission and a thruster head temperature control off request is received, the onboard integrated electronic computer sends a thruster head temperature control off command chain. When the program control flag is prohibition, the onboard integrated electronic computer does not respond to the heater temperature control on / off request. Module M4: Sets the on-board temperature control startup time limit. The thruster head temperature control early startup time is modified according to the satellite's on-orbit ambient temperature. When the attitude and orbit control subsystem working status changes, the new working status is sent to the on-board integrated electronic computer.

Images