Spacecraft thermal control software test method and device based on temperature inverse solution, computer program product

Abstract

The application provides a spacecraft thermal control software test method and device based on temperature inverse solution, and a computer program product, comprising: obtaining the scale factor of a thermal resistor on a satellite and the corresponding information of the thermal resistor and a heating loop on the satellite through telemetry; obtaining the temperature original code corresponding to the current thermal resistor on the satellite through telemetry, and determining the temperature generated by the current heating loop on the satellite; determining the resistance value of the thermal resistor under the current temperature and the scale factor of the thermal resistor according to the resistance value-temperature relationship of the thermal resistor; under the fixed resistance value of the thermal resistor, updating any scale factor value of the selected thermal resistor according to the set target temperature, and maintaining the scale factor values of other thermal resistors unchanged; uploading the updated scale factor value of the thermal resistor to the on-orbit thermal control system to complete the on-orbit parameter update, and obtaining the on-orbit target temperature according to the updated scale factor of the thermal resistor by the on-orbit thermal control system, and implementing the spacecraft thermal control software test by comparing the consistency of the on-orbit target temperature and the set target temperature.

Description

Technical Field

[0001] This invention belongs to the field of thermal control testing technology, and specifically relates to a spacecraft thermal control software testing method, device, and computer program product based on temperature inverse kinematics. Background Technology

[0002] Currently, spacecraft thermal control software testing methods utilize ground-based testing software and equipment. Ground-based testing equipment primarily replaces the actual heating circuits of the spacecraft. By setting the output resistance value of the ground-based testing equipment, the temperature acquired by the spacecraft's thermal control software is altered, thereby testing the software logic. To create temperature differences between different circuits in the spacecraft, target temperatures for each circuit need to be set in the ground-based testing equipment. The equipment calculates the required output resistance value for that circuit using a formula, and the onboard thermal control equipment acquires this resistance value via a satellite-to-ground cable and calculates the target temperature. The main challenges in using ground-based testing for thermal control testing are as follows:

[0003] (1) In order to adapt to different types and different spectrums of thermal control equipment, a lot of resources need to be invested in the design and production of transfer cables in the thermal control test preparation stage.

[0004] (2) Due to the limited resources of ground testing equipment, it is impossible to meet the need for simultaneous testing of all loops on the satellite. During the testing process, cable connections need to be constantly replaced.

[0005] (3) The ground inspection equipment is complex to use. It is necessary to configure the thermistor division coefficient and point number in advance, and adjust it according to the cable connection. Summary of the Invention

[0006] In order to overcome the shortcomings of the existing technology, the inventors have conducted intensive research and provided a spacecraft thermal control software testing method, device and computer program product based on temperature inverse solution, which solves the problems of complex ground inspection equipment and cumbersome cable adjustment caused by the current ground inspection equipment.

[0007] The technical solution provided by this invention is as follows:

[0008] Firstly, a spacecraft thermal control software testing method based on temperature inverse kinematics includes:

[0009] Telemetry acquires the calibration coefficient of the onboard thermistor and the corresponding information between the thermistor and the onboard heating circuit;

[0010] Telemetry acquires the original temperature code corresponding to the current thermistor on the satellite, and determines the temperature generated by the current heating circuit on the satellite.

[0011] Based on the relationship between the thermistor resistance and temperature, determine the thermistor resistance at the current temperature and the thermistor calibration coefficient.

[0012] With a fixed thermistor resistance value, update any of the selected thermistor's scale factor values ​​according to the set target temperature, while keeping the scale factor values ​​of other thermistors unchanged.

[0013] The updated thermistor calibration coefficient values ​​are uploaded to the onboard thermal control system to complete the onboard parameter update. The onboard thermal control system obtains the onboard target temperature based on the updated thermistor calibration coefficients. The consistency between the onboard target temperature and the set target temperature is checked, and the spacecraft thermal control software is tested.

[0014] Secondly, a spacecraft thermal control software testing device based on temperature inverse kinematics includes:

[0015] One or more processors;

[0016] Storage device for storing one or more programs.

[0017] When the one or more programs are executed by the one or more processors, the one or more processors implement the spacecraft thermal control software testing method based on temperature inverse kinematics as described in the first aspect.

[0018] Thirdly, a readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the spacecraft thermal control software testing method based on temperature inverse kinematics as described in the first aspect.

[0019] Fourthly, a computer program product comprising: a computer program (also referred to as code or instructions) that, when run, executes the spacecraft thermal control software testing method based on temperature inverse kinematics as described in the first aspect.

[0020] The spacecraft thermal control software testing method, apparatus, and computer program product based on temperature inverse kinematics provided by the present invention have the following beneficial effects:

[0021] This invention provides a spacecraft thermal control software testing method based on temperature inverse kinematics, comprising: telemetry acquisition of the calibration coefficient of onboard thermistors and the corresponding information between thermistors and onboard heating circuits; telemetry acquisition of the original temperature code corresponding to the current onboard thermistor to determine the temperature generated by the current onboard heating circuit; determining the thermistor resistance value at the current temperature and the thermistor calibration coefficient according to the thermistor resistance-temperature relationship formula; and updating any calibration coefficient value of a selected thermistor according to a set target temperature while keeping the calibration coefficient values ​​of other thermistors unchanged, while keeping the calibration coefficient values ​​of other thermistors unchanged. The updated thermistor calibration coefficient values ​​are uploaded to the onboard thermal control system to complete the onboard parameter update. The onboard thermal control system obtains the target temperature based on the updated thermistor calibration coefficients. By comparing the onboard target temperature with the set target temperature, the spacecraft thermal control software is tested. This invention uses ground testing software and onboard heating circuits to achieve precise setting of temperature differences between different circuits in the spacecraft, eliminating the need for ground testing equipment. This enables the testing of the spacecraft thermal control software, providing an algorithm and software foundation for automated testing of spacecraft thermal control software, and eliminating the testing mode that requires excessive operator intervention. Attached Figure Description

[0022] Figure 1 This is a flowchart of a spacecraft thermal control software testing method based on temperature inverse kinematics according to the present invention. Detailed Implementation

[0023] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0024] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0025] This invention provides a spacecraft thermal control software testing method based on temperature inverse kinematics, such as... Figure 1 As shown, it includes the following steps:

[0026] Step 1: Telemetry is used to obtain the calibration coefficients of the onboard thermistors and store them in the model database. The heating areas corresponding to each heating circuit on the satellite are monitored for temperature using the corresponding thermistors.

[0027] The model database stores basic model data, including the original thermistor calibration coefficient and thermistor number. The heating circuit corresponding to each thermistor is determined by the thermistor number. In the early stage of testing, the original on-board data can be parsed and stored in the database by configuring the basic packet format and downloading on-board parameters for subsequent testing.

[0028] The model database is a relational database, where various types of data are stored in key-value pairs. The corresponding value is retrieved by calling the key. The data structure design is shown in Table 1 below:

[0029] Table 1

[0030]

[0031] Step 2: Telemetry is used to obtain the original temperature code corresponding to the current thermistor on the satellite, determine the temperature value generated by the current heating circuit, and complete the temperature inverse solution.

[0032] Assume the satellite transmits N bytes of temperature data (original temperature code), which is T bytes in decimal. N Temperature stratification value is Num T A full F hexadecimal number of length N bytes is F N ;

[0033] When the original temperature code is less than or equal to B500H, it indicates that the current temperature is positive. The positive temperature value is:

[0034]

[0035] When the original temperature code is greater than B500H, it indicates that the current temperature is negative. The negative temperature resolution value is:

[0036]

[0037] Step 3: Determine the thermistor resistance value at the current temperature and the thermistor scale factor based on the thermistor resistance-temperature conversion formula.

[0038] Thermostat temperature-resistance conversion formula:

[0039]

[0040] in:

[0041] T represents the temperature value, in °C.

[0042] R is the actual resistance value of the thermistor, in Ω.

[0043] A, B, and C are all thermistor calibration coefficients; different thermistors correspond to different calibration coefficients.

[0044] Let LnR = D, T' = T + 273.15, then:

[0045]

[0046] The formula can be transformed to obtain:

[0047]

[0048] Given the current temperature as T, we can use the formula to solve for D under the original parameters A, B, and C.

[0049] Step 4: With the thermistor resistance value fixed, update any of the selected thermistor's scale factor values ​​according to the set target temperature, while keeping the scale factor values ​​of other thermistors unchanged.

[0050] Based on the set target temperature T target The new parameter A' is calculated using the following formula:

[0051]

[0052] Alternatively, based on the target temperature T target The new parameter B' is calculated using the following formula:

[0053]

[0054] Alternatively, based on the target temperature T target The new parameter C' is calculated using the following formula:

[0055]

[0056] Among them, T t ' arget =T target +273.15.

[0057] When updating the thermistor calibration coefficient, any calibration coefficient value of one or more thermistors can be updated while keeping the calibration coefficient values ​​of other thermistors unchanged. Updating any calibration coefficient value of multiple thermistors allows for simultaneous testing of multiple heating circuits.

[0058] Step 5: The updated thermistor calibration coefficient value is uploaded to the onboard thermal control system to complete the onboard parameter update. The onboard thermal control system obtains the onboard target temperature based on the updated thermistor calibration coefficient. The consistency between the onboard target temperature and the set target temperature is checked, and the spacecraft thermal control software is tested.

[0059] If the original onboard temperature A is updated to A', the temperature calculated by the onboard thermal control equipment according to A', B, C, and the formula will be the target temperature. That is:

[0060]

[0061] If the original temperature B on the satellite is updated to B', the temperature calculated by the onboard thermal control equipment according to A, B', C, and the formula will be the target temperature. That is:

[0062]

[0063] If the original onboard temperature C is updated to C', the temperature calculated by the onboard thermal control equipment according to A, B, C' and the formula will be the target temperature. That is:

[0064]

[0065] The above process enables the setting of onboard temperature without ground testing equipment, thereby checking the logical processing results of the spacecraft's thermal control software and completing the spacecraft's thermal control software architecture test.

[0066] This invention also provides a spacecraft thermal control software testing device based on temperature inverse kinematics, comprising:

[0067] One or more processors;

[0068] Storage device for storing one or more programs.

[0069] When the one or more programs are executed by the one or more processors, the one or more processors implement the spacecraft thermal control software testing method based on temperature inverse kinematics described above.

[0070] The present invention also provides a readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aforementioned spacecraft thermal control software testing method based on temperature inverse kinematics.

[0071] The readable storage media include, but are not limited to, USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0072] The present invention also provides a computer program product, the computer program product comprising: a computer program (also referred to as code or instructions), which, when the computer program is run, executes the above-described spacecraft thermal control software testing method based on temperature inverse kinematics.

[0073] The computer program product is a ground-based test system for spacecraft thermal control software. After the ground test system is started, it obtains the original thermistor calibration coefficients from the satellite via the telemetry interface and stores them in the model database according to the loop correspondence. It also obtains the original temperature code corresponding to the current thermistor on the satellite via the telemetry interface. As needed, it sequentially obtains the current temperature of each loop, solves the loop LnR value according to the formula, and then calculates the target temperature T under fixed LnR, B, and C parameters. t ' argetThe corresponding A' is then uploaded to the onboard thermal control equipment via the remote control interface to complete the parameter update, allowing for further testing of other functions of the thermal control software. This method facilitates groundless testing of the spacecraft's thermal control software.

[0074] In the above embodiments, implementation can be achieved, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented using software, it can be implemented, in whole or in part, as a computer program product. The computer program product includes one or more computer instructions. When the computer instructions are loaded and executed on a computer, all or part of the processes or functions described in the embodiments of this application are generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, microwave, etc.) means.

[0075] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0076] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the device and product described above can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0077] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0078] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A spacecraft thermal control software testing method based on temperature inverse kinematics, characterized in that, include: Telemetry acquires the calibration coefficient of the onboard thermistor and the corresponding information between the thermistor and the onboard heating circuit; Telemetry acquires the original temperature code corresponding to the current thermistor on the satellite, and determines the temperature generated by the current heating circuit on the satellite. Based on the relationship between the thermistor resistance and temperature, determine the thermistor resistance at the current temperature and the thermistor calibration coefficient. With a fixed thermistor resistance value, update any of the selected thermistor's scale factor values ​​according to the set target temperature, while keeping the scale factor values ​​of other thermistors unchanged. The updated thermistor calibration coefficient values ​​are uploaded to the onboard thermal control system to complete the onboard parameter update. The onboard thermal control system obtains the target temperature based on the updated thermistor calibration coefficients. The consistency between the target temperature and the set target temperature is checked, and the spacecraft thermal control software is tested.

2. The spacecraft thermal control software testing method based on temperature inverse kinematics as described in claim 1, characterized in that, The steps of telemetry to obtain the calibration coefficient of the on-board thermistor and the correspondence information between the thermistor and the on-board heating circuit include: telemetry to obtain the calibration coefficient of the on-board thermistor and the thermistor number, and determining the heating circuit corresponding to each thermistor through the thermistor number.

3. The spacecraft thermal control software testing method based on temperature inverse kinematics as described in claim 1, characterized in that, The step of telemetry to obtain the calibration coefficient of the on-board thermistor and the corresponding information between the thermistor and the on-board heating circuit further includes: storing the obtained calibration coefficient of the on-board thermistor and the corresponding information between the thermistor and the on-board heating circuit into a relational database, preferably by calling the key value to obtain the corresponding value, where the key value corresponds to the primary key and the value value corresponds to the attribute information stored in the relational database.

4. The spacecraft thermal control software testing method based on temperature inverse kinematics as described in claim 1, characterized in that, In the step of determining the thermistor resistance value at the current temperature and the thermistor calibration coefficient based on the thermistor resistance-temperature relationship formula, the thermistor resistance-temperature relationship formula is as follows: Where T' = T + 273.15, T is the temperature value in °C; D = LnR, where R is the actual resistance value of the thermistor, in Ω; A, B, and C are all thermistor calibration coefficients.

5. The spacecraft thermal control software testing method based on temperature inverse kinematics according to claim 4, characterized in that, In the step of updating any graduation factor value of a selected thermistor according to a set target temperature while keeping the graduation factor values ​​of other thermistors unchanged, under a fixed thermistor resistance value, Based on the set target temperature T target The new parameter A' is obtained, as shown in the following formula: Alternatively, based on the target temperature T target The new parameter B' is obtained, as shown in the following formula: Alternatively, based on the target temperature T target The new parameter C' is obtained, as shown in the following formula: C'=DT t ' arget 2 -AT t ' arget 2 -BT t ' arget Among them, T t ' arget =T target +273.

15.

6. The spacecraft thermal control software testing method based on temperature inverse kinematics according to claim 4, characterized in that, The step of updating any scale factor value of a selected thermistor according to a set target temperature while keeping the scale factor values ​​of other thermistors unchanged under a fixed thermistor resistance value includes: updating any scale factor value of one or more thermistors while keeping the scale factor values ​​of other thermistors unchanged.

7. The spacecraft thermal control software testing method based on temperature inverse kinematics according to claim 5, characterized in that, In the step of uploading the updated thermistor calibration coefficient values ​​to the onboard thermal control system to complete the onboard parameter update, and the onboard thermal control system obtaining the onboard target temperature based on the updated thermistor calibration coefficients... If the original onboard temperature A is updated to A', the onboard thermal control equipment obtains the target temperature according to A', B, C, and the following formula: If the original B on the satellite is updated to B', the onboard thermal control equipment obtains the target temperature according to A, B', C and the following formula: If the original onboard temperature C is updated to C', the onboard thermal control equipment obtains the target temperature according to A, B, C' and the following formula:

8. A spacecraft thermal control software testing device based on temperature inverse kinematics, comprising: One or more processors; Storage device for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the spacecraft thermal control software testing method based on temperature inverse kinematics as described in any one of claims 1 to 7.

9. A readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the spacecraft thermal control software testing method based on temperature inverse kinematics as described in any one of claims 1 to 7.

10. A computer program product, the computer program product comprising: A computer program, when run, executes the spacecraft thermal control software testing method based on temperature inverse kinematics as described in any one of claims 1 to 7.

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