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

Abstract

The invention provides a spacecraft thermal control software test method and device based on temperature inverse solution, and a computer program product. The method comprises the following steps: remotely measuring to obtain an on-satellite thermistor indexing coefficient and corresponding information of a thermistor and an on-satellite heating loop; a temperature original code corresponding to the current thermistor on the satellite is obtained through telemetering, and the temperature generated by the current heating loop on the satellite is determined; determining the thermistor resistance value under the current temperature and the thermistor indexing coefficient according to the relation between the thermistor resistance value and the temperature; under the fixed resistance value of the thermistor, any one indexing coefficient value of the selected thermistor is updated according to the set target temperature, and the indexing coefficient values of other thermistors are kept unchanged; the updated thermistor indexing coefficient value is injected into the on-satellite thermal control system to complete on-satellite parameter updating, the on-satellite thermal control system obtains the on-satellite target temperature according to the updated thermistor indexing coefficient value, and spacecraft thermal control software testing is implemented by comparing the consistency of the on-satellite target temperature and the set target temperature.

Description

Technical Field

[0001] The present invention belongs to the field of thermal control testing technology, and in particular relates to a method, device and computer program product for testing spacecraft thermal control software based on temperature inversion. Background Art

[0002] At present, the spacecraft thermal control software testing method is carried out using ground test software and ground inspection equipment. It mainly relies on ground inspection equipment to replace the real heating circuit of the spacecraft. By setting the output resistance of the ground inspection equipment, the temperature collected by the spacecraft thermal control software is changed to test the logic of the thermal control software. In order to create temperature differences between different circuits of the spacecraft, it is necessary to set the target temperature of the circuit in the ground inspection equipment. The ground inspection equipment calculates the resistance value that the circuit should output according to the formula. The onboard thermal control equipment collects the resistance value through the satellite-to-ground cable and calculates the target temperature. The following problems are mainly faced in thermal control testing using ground inspection:

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

[0004] (2) Due to the limited resources of ground inspection equipment, it is impossible to meet the needs of testing all loops on the satellite at the same time, and the cable connection needs to be constantly replaced during the test process;

[0005] (3) The ground inspection equipment is complex to use and requires the configuration of information such as thermistor division coefficient and point number in advance, and adjustment based on the cable connection conditions. Summary of the invention

[0006] In order to overcome the deficiencies in the prior art, the inventors have conducted intensive research and provided a method, device, and computer program product for testing spacecraft thermal control software based on temperature inversion to solve the problems of complex ground inspection equipment and cumbersome cable adjustment caused by the current ground inspection equipment.

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

[0008] In a first aspect, a method for testing spacecraft thermal control software based on temperature inversion includes:

[0009] Telemetry to obtain the on-board thermistor division coefficient and the corresponding information between the thermistor and the on-board heating circuit;

[0010] Telemetry obtains the temperature code corresponding to the current thermistor on the satellite and determines the temperature generated by the current heating circuit on the satellite;

[0011] According to the relationship between thermistor resistance and temperature, determine thermistor resistance under the current temperature and thermistor division coefficient;

[0012] Under the condition of fixed thermistor resistance, update any division coefficient value of the selected thermistor according to the set target temperature, and keep the division coefficient values ​​of other thermistors unchanged;

[0013] The updated thermistor division coefficient value is added 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 division coefficient, and implements the spacecraft thermal control software test by comparing the consistency of the onboard target temperature with the set target temperature.

[0014] In a second aspect, a spacecraft thermal control software testing device based on temperature inversion includes:

[0015] one or more processors;

[0016] a 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 solution described in the first aspect.

[0018] In a third aspect, a readable storage medium stores a computer program, which, when executed by a processor, implements the spacecraft thermal control software testing method based on temperature inversion described in the first aspect.

[0019] In a fourth aspect, a computer program product is provided, comprising: a computer program (also referred to as code, or instruction), which, when executed, executes the spacecraft thermal control software testing method based on temperature inversion described in the first aspect.

[0020] A method, device, and computer program product for testing spacecraft thermal control software based on temperature inversion provided by the present invention have the following beneficial effects:

[0021] The present invention provides a spacecraft thermal control software testing method based on temperature inverse solution, comprising: remotely measuring and acquiring the on-board thermistor division coefficient and the corresponding information between the thermistor and the on-board heating circuit; remotely measuring and acquiring the temperature source code corresponding to the current on-board thermistor to determine the temperature generated by the current on-board heating circuit; determining the thermistor resistance value under the current temperature and the thermistor division coefficient according to the thermistor resistance value and temperature relationship formula; and updating any division coefficient value of the selected thermistor according to the set target temperature under the fixed thermistor resistance value, and maintaining the division coefficient values ​​of other thermistors unchanged. ; The updated thermistor division coefficient value is added to the onboard thermal control system to complete the onboard parameter update. The onboard thermal control system obtains the onboard target temperature according to the updated thermistor division coefficient, and implements the spacecraft thermal control software test by comparing the consistency of the onboard target temperature with the set target temperature; The method of the present invention adopts ground test software and onboard heating circuit, and realizes the precise setting of temperature differences between different circuits of the spacecraft without ground inspection equipment, realizes the spacecraft thermal control software test, provides algorithm and software basis for the automated testing of spacecraft thermal control software, and abandons the test mode with excessive operator participation. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 The present invention is a flow chart of a method for testing spacecraft thermal control software based on temperature inversion. DETAILED DESCRIPTION

[0023] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0024] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0025] The present invention provides a method for testing spacecraft thermal control software based on temperature inversion. Figure 1 As shown, the following steps are included:

[0026] Step 1: remotely obtain the on-board thermistor division coefficient and store it in the model database. The heating area corresponding to each heating circuit on the satellite is temperature-monitored by the corresponding thermistor.

[0027] The model database stores basic model data, including the original thermistor division coefficient, thermistor number, and the heating circuit corresponding to each thermistor is determined by the thermistor number. In the early stage of the test, the original data on the satellite can be parsed and stored in the database by configuring the basic package format and transmitting the on-board parameters for use in subsequent tests.

[0028] The model database is a relational database. Various data are stored in the database in the form of key-value. The corresponding value is obtained by calling the key value. The data structure design is shown in Table 1 below:

[0029] Table 1

[0030]

[0031] Step 2: Telemetry obtains the temperature code corresponding to the current thermistor on the satellite, determines the temperature value generated by the current heating circuit, and completes the temperature inverse solution.

[0032] Assume that the satellite transmits temperature data (temperature original code) with a total of N bytes, and converts it into decimal data as T N , the temperature stratification value is Num T , the full F hexadecimal number of N bytes is F N ;

[0033] When the temperature original code is ≤B500H, it means the current temperature is positive. The positive temperature parsing value is:

[0034]

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

[0036]

[0037] Step 3: Determine the resistance of the thermistor at the current temperature and the thermistor division coefficient according to the thermistor resistance and temperature conversion formula.

[0038] Thermistor temperature and resistance conversion formula:

[0039]

[0040] in:

[0041] T is the temperature value, unit: °C;

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

[0043] A, B, and C are thermistor graduation coefficients. Different thermistors correspond to different graduation coefficients.

[0044] Remember LnR = D, T' = T + 273.15, we get:

[0045]

[0046] The formula transformation yields:

[0047]

[0048] Get the current temperature as T, and use the formula to inversely solve D under the original A, B, and C parameters.

[0049] Step 4: Under a fixed thermistor resistance value, update any division coefficient value of the selected thermistor according to the set target temperature, and keep the division coefficient values ​​of other thermistors unchanged.

[0050] According to the set target temperature T target The new parameter A' is calculated as follows:

[0051]

[0052] Or, according to the target temperature T target The new parameter B' is calculated as follows:

[0053]

[0054] Or, according to the target temperature T target The new parameter C' is calculated as follows:

[0055]

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

[0057] When updating thermistor division coefficients, any division coefficient value of one or more thermistors can be updated, and the division coefficient values ​​of other thermistors can be kept unchanged. When updating any division coefficient value of multiple thermistors, multiple heating circuits can be tested simultaneously.

[0058] Step 5: The updated thermistor division coefficient value is entered into 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 division coefficient, compares the consistency of the onboard target temperature with the set target temperature, and implements the spacecraft thermal control software test.

[0059] If the original A on the satellite is updated to A', the temperature calculated by the on-board thermal control equipment according to A', B, C and the formula is the target temperature. That is:

[0060]

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

[0062]

[0063] If the original C on the satellite is updated to C', the temperature calculated by the on-board thermal control equipment according to A, B, C' and the formula is the target temperature. That is:

[0064]

[0065] Through the above process, it is possible to set the on-board temperature without ground inspection equipment, and then check the logical processing results of the spacecraft thermal control software to complete the spacecraft thermal control software architecture test.

[0066] The present invention also provides a spacecraft thermal control software testing device based on temperature inversion, comprising:

[0067] one or more processors;

[0068] a 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 above-mentioned spacecraft thermal control software testing method based on temperature inverse solution.

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

[0071] The readable storage medium includes, but is not limited to, various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk.

[0072] The present invention also provides a computer program product, which includes: a computer program (also referred to as code, or instruction), which, when executed, executes the above-mentioned spacecraft thermal control software testing method based on temperature inversion.

[0073] The computer program product is a ground test system for spacecraft thermal control software. After the ground test system is started, the original thermistor division coefficient is obtained from the satellite through the telemetry interface and stored in the model database according to the loop correspondence, and the temperature original code corresponding to the current thermistor on the satellite is obtained through the telemetry interface; the current temperature of each loop is obtained in turn as needed, the loop LnR value is inversely solved according to the formula, and then the target temperature T is calculated under fixed LnR, B, C parameters. t ' argetThe corresponding A' is finally updated by injecting the updated A' into the onboard thermal control equipment through the remote control interface to complete the parameter update, and other functional tests of the thermal control software can continue. This method is convenient for realizing the non-ground inspection test of the spacecraft thermal control software.

[0074] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of 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, the process or function described in the embodiment of the present application is generated in whole or in part. 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 computer-readable storage medium, for example, the computer instructions can be transmitted from a website site, computer, server or data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (digital subscriber line, DSL)) or wireless (e.g., infrared, microwave, etc.) mode to another website site, computer, server or data center.

[0075] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example 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 performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0076] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process of the above-described device and product can refer to the corresponding process in the aforementioned method embodiment, and will not be repeated here.

[0077] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0078] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A method for testing spacecraft thermal control software based on temperature inversion, characterized in that: include: Telemetry to obtain the on-board thermistor division coefficient and the corresponding information between the thermistor and the on-board heating circuit; Telemetry obtains the temperature code corresponding to the current thermistor on the satellite and determines the temperature generated by the current heating circuit on the satellite; According to the relationship between thermistor resistance and temperature, determine thermistor resistance under the current temperature and thermistor division coefficient; Under the condition of fixed thermistor resistance, update any division coefficient value of the selected thermistor according to the set target temperature, and keep the division coefficient values ​​of other thermistors unchanged; The updated thermistor division coefficient value is added 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 division coefficient, and implements the spacecraft thermal control software test by comparing the consistency of the onboard target temperature with the set target temperature.

2. The spacecraft thermal control software testing method based on temperature inversion according to claim 1 is characterized in that: The step of remotely measuring and obtaining the on-board thermistor division coefficients and the corresponding information between thermistors and on-board heating circuits includes: remotely measuring and obtaining the on-board thermistor division coefficients and thermistor numbers, and determining the heating circuit corresponding to each thermistor by the thermistor numbers.

3. The spacecraft thermal control software testing method based on temperature inversion according to claim 1 is characterized in that: The step of remotely measuring and obtaining the corresponding information between the on-board thermistor division coefficient and the thermistor and the on-board heating circuit also includes: storing the obtained on-board thermistor division coefficient and the corresponding information between the thermistor and the on-board heating circuit in a relational database, preferably obtaining the corresponding value by calling the key value, 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 inversion according to claim 1 is characterized in that: In the step of determining the resistance of the thermistor at the current temperature and the thermistor division coefficient according to the thermistor resistance and temperature relationship, the thermistor resistance and temperature relationship is: Where, T'=T+273.15, T is the temperature value, unit: °C; D=LnR, R is the actual resistance value of the thermistor, unit: Ω; A, B, and C are thermistor graduation coefficients.

5. The spacecraft thermal control software testing method based on temperature inversion according to claim 4 is characterized in that: In the step of updating any division coefficient value of the selected thermistor according to the set target temperature under the fixed thermistor resistance value, and maintaining the division coefficient values ​​of other thermistors unchanged, According to the set target temperature T target , get the new parameter A', the formula is as follows: Or, according to the target temperature T target , get the new parameter B', the formula is as follows: Or, according to the target temperature T target , get the new parameter C', the formula is as follows: 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 inversion according to claim 4 is characterized in that: The step of updating any division coefficient value of a selected thermistor according to a set target temperature and maintaining the division coefficient values ​​of other thermistors unchanged under a fixed thermistor resistance value includes: updating any division coefficient value of one or more thermistors and maintaining the division coefficient values ​​of other thermistors unchanged.

7. The spacecraft thermal control software testing method based on temperature inversion according to claim 5 is characterized in that: In the step of recording the updated thermistor division coefficient value to the on-board thermal control system to complete the on-board parameter update, and the on-board thermal control system obtains the on-board target temperature according to the updated thermistor division coefficient, If the original A on the satellite is updated to A', the on-board thermal control device 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 on-board thermal control equipment obtains the target temperature according to A, B', C and the following formula: If the original C on the satellite is updated to C', the on-board 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 inversion, comprising: one or more processors; a 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 inversion as described in 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 inversion as described in any one of claims 1 to 7.

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

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