Design method for digital simulation interface of satellite measurement and control subsystem

Abstract

The invention provides a digital simulation interface design method for a satellite measurement and control subsystem, which comprises the following steps of: describing working states of the measurement and control subsystem by using six types of interfaces, namely an initialization interface, a simulation control interface, a model event interface, a simulation state interface, a running log interface and a telemetering interface; wherein the initialization interface, the simulation control interface and the model event interface are used for data input of a subsystem, and the simulation state interface, the running log interface and the telemetering interface are used for data output. According to the invention, interface testing of a satellite digital subsystem model can be systematically carried out with least units, convenience is provided for integrated use of measurement and control services, related digital work of satellites is promoted, and related real installation designers are assisted to carry out simulation digitization of subsystems.

Description

Technical Field

[0001] The present invention relates to the technical field of digital analog interface design, and in particular to a digital analog interface design method for a satellite measurement and control subsystem. Background Art

[0002] The digital satellite model needs to truly reflect the satellite's functions, performance, working mode and on-orbit status. The functions of the core software and the external software interface must be consistent with the onboard software, and the core data format must be consistent with the real satellite. The simulation results have good consistency with the satellite-ground data deduction results. The measurement and control subsystem mainly completes the functions of sending and receiving remote control commands, injection data and telemetry parameters in conventional and ad hoc modes, ensuring that the satellite correctly executes remote control commands and injects data blocks. The frame format, frame data field, data packet format, packet data field, frame period, timing, etc. of remote control commands, telemetry parameters and other data must be consistent with the real satellite. The data types are numerous and the relationships are complex. Therefore, the present invention proposes a digital analog interface design method for satellite measurement and control subsystems based on the initial state and simulation state.

[0003] Patent application document CN118296802A describes a satellite digital model design method based on a virtual bus engine. This method addresses the requirements for satellite digital models to be applicable in multiple scenarios, versatile across multiple models, and multifunctional, as well as modular, standardized, and parameterized. The method follows a domain-driven layered architecture design, encapsulating universal satellite external interfaces, dividing standard subsystem modules, and unifying subsystem interface specifications. Furthermore, the method uses a virtual bus model as an integration platform to achieve rule-based isomorphic processing of subsystem models. However, this patent fails to fully resolve existing technical issues and fails to meet the requirements of the present invention. Summary of the Invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a method for designing a digital analog interface for a satellite measurement and control subsystem.

[0005] The digital analog interface design method for a satellite measurement and control subsystem provided by the present invention includes: using six types of interfaces to describe the working status of the measurement and control subsystem, namely, initialization interface, simulation control interface, model event interface, simulation status interface, operation log interface and telemetry interface;

[0006] Among them, the initialization interface, simulation control interface and model event interface are used for input data of the subsystem, and the simulation status interface, operation log interface and telemetry interface are used for data output;

[0007] The specific process is:

[0008] Step 1: Define the initialization interface of the measurement and control link model and the simulation control interface of the measurement and control subsystem;

[0009] Step 2: Define the measurement and control link list data type and the measurement and control link status data type;

[0010] Step 3: Define antenna data type and antenna status data type;

[0011] Step 4: Define the beam structure interface;

[0012] Step 5: Define transponder data type, define transponder working mode list interface and define transponder status data type;

[0013] Step 6: Define the receiving and sending channel parameter interface;

[0014] Step 7: Define the measurement and control fixed release data type and the measurement and control wave control machine status data type.

[0015] Preferably, the initialization interface includes basic information parameters, system power consumption, system heat consumption, working mode selection, initial working status, measurement and control link list, antenna list and transponder list information;

[0016] The simulation control interface includes basic information parameters, measurement and control mode, total power consumption, total heat consumption, system fault status, measurement and control link status, antenna status, transponder status, measurement and control fixed release status, wave control machine status and real-time simulation information of on-board telemetry data.

[0017] Preferably, the measurement and control link list data includes: link number, link type, direction flag, measurement and control system, satellite transmission EIRP, satellite reception G / T value and operating frequency information;

[0018] The link number is represented by a character array of fixed size 16; the link type is represented by an integer type, with a value of 0 indicating a ground link and a value of 1 indicating a relay link; the direction flag is represented by an integer type, with a value of 0 indicating sending and a value of 1 indicating receiving; the measurement and control system is represented by an integer type; the satellite transmit EIRP, satellite receive G / T value and operating frequency are all represented by floating-point type.

[0019] Preferably, the antenna data includes: basic information parameters, antenna type, antenna installation matrix, antenna polarization mode, antenna receiving gain, antenna transmitting gain, antenna pattern - receiving, antenna pattern - transmitting, antenna initial pointing, antenna pointing range constraint and beam information;

[0020] Basic information parameters are represented by floating-point types; antenna type is represented by integer type, with a value of 1 indicating a parabola, a value of 2 indicating a reflector, a value of 3 indicating a phased array, and a value of 4 indicating a helical antenna; the antenna installation matrix is represented by a floating-point array of size 6; the antenna polarization mode is represented by an integer type, with a value of 1 indicating left-hand circular polarization, a value of 2 indicating right-hand circular polarization, a value of 3 indicating linear polarization, and a value of 4 indicating elliptical polarization; both antenna receive gain and antenna transmit gain are represented by floating-point types; antenna radiation pattern - receive and antenna radiation pattern - transmit are stored in files; the antenna initial pointing is represented by a floating-point array of size 2, with the two digits in the array corresponding to the azimuth and elevation angles, respectively; the antenna pointing range constraint is represented by a floating-point array of size 4, with the first two digits indicating the start and end range of the azimuth angle, and the last two digits indicating the start and end range of the elevation angle; the beam is represented by a custom beam structure.

[0021] Preferably, the beam structure interface includes: beam number, beam switch status, frequency, half-cone angle and beam pointing information; the beam number is represented by an integer type; the beam switch status is represented by an integer type, when the value is 0, it indicates that the switch is in the closed state, and when the value is 1, it indicates that the switch is open; the frequency and half-cone angle are both represented by a floating point type; the beam pointing is represented by a floating point type array of size 2, where the first bit represents the azimuth angle and the second bit represents the pitch angle.

[0022] Preferably, the transponder data includes: basic information parameters, single-machine general attribute parameters and a working mode list, wherein the working mode list is represented by a custom transponder working mode structure;

[0023] The transponder working mode list includes: working mode name, receiving channel parameters and sending channel parameter information, wherein the working mode name is represented by a character type array of size 16, and the receiving channel parameters and sending channel parameters are both represented by a custom transponder working mode structure.

[0024] Preferably, the receiving and transmitting channel parameters include: measurement and control system, center frequency, bandwidth, modulation mode, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, channel bit error rate, noise figure, anti-interference capability, maximum non-destructive power and transponder output power information;

[0025] The measurement and control system is represented by an integer type. A value of 0 represents incoherent spread spectrum, a value of 1 represents spread frequency hopping, and a value of 2 represents a USB unified carrier system. The center frequency, bandwidth, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, channel bit error rate, noise figure, maximum undamaged power, and transponder output power are all represented by floating-point types. The uplink information rate, uplink frame error rate noise figure, anti-interference capability, and maximum undamaged power are only used in the receiving channel, and the transponder output power is only used in the transmitting channel. The modulation mode is represented by an integer type. The anti-interference capability is represented by a floating-point array of size 10.

[0026] Preferably, the measurement and control link status data includes: link number, link type, direction flag, measurement and control system, satellite transmission EIRP, satellite reception G / T value and operating frequency information;

[0027] The link number is represented by a character array of size 16; the link type is represented by an integer type, with a value of 0 indicating a ground link and a value of 1 indicating a relay link; the direction flag is represented by an integer type, with a value of 0 indicating sending and a value of 1 indicating receiving; the measurement and control system is represented by an integer type, with a value of 0 indicating incoherent spread spectrum, a value of 1 indicating spread hopping frequency, and a value of 2 indicating a USB unified carrier system; the satellite transmit EIRP, satellite receive G / T value, and operating frequency are all represented by floating-point types.

[0028] Preferably, the transponder status data includes: the current working mode is represented by an integer type, when the value is 1, it indicates the non-coherent spread spectrum working mode, when the value is 2, it indicates the high-speed injection working mode, when the value is 3, it indicates the relay continuous service working mode, when the value is 4, it indicates the relay short message service working mode, when the value is 5, it indicates the random mode, when the value is 6, it indicates that the first and second modes work at the same time, when the value is 7, it indicates that the first and third modes work at the same time, when the value is 8, it indicates that the first and fourth modes work at the same time, when the value is 9, it indicates that the first and fifth modes work at the same time, when the value is 10, it indicates that the second and third modes work at the same time, when the value is 11, it indicates that the second and fourth modes work at the same time, when the value is 12, it indicates that the second and fifth modes work at the same time, when the value is 13, it indicates that the third and fifth modes work at the same time, and when the value is 14, it indicates that the fourth and fifth modes work at the same time.

[0029] Preferably, the measurement and control fixed-placement data includes: basic information parameters, power consumption, heat consumption, power on / off status and output power data, and the power consumption, heat consumption, power on / off status and output power are all represented by floating point type;

[0030] The measurement and control wave control machine status data includes: basic information parameters, power consumption, heat consumption and power on / off status data; power consumption and heat consumption are represented by floating point type, and power on / off status is represented by integer type, when the value is 0, it means shutdown, and when the value is 1, it means startup.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] The present invention proposes a method for designing a digital analog interface for a satellite measurement and control subsystem. The method divides the interface into two categories based on the working status: an initialization data interface and a simulation status data interface. This method clearly divides the numerous and complex data types in the measurement and control subsystem. The design is testable and extensible, facilitating the integrated use of measurement and control services, promoting satellite-related digitalization work, and assisting relevant installation designers in the simulation and digitization of subsystems. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] 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:

[0034] Figure 1 This is the external interface design diagram of the general digital model of the satellite measurement and control subsystem. DETAILED DESCRIPTION

[0035] 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.

[0036] Example

[0037] like Figure 1 The present invention proposes a method for designing a digital analog interface of a satellite measurement and control subsystem, comprising:

[0038] Step 1: Use six types of interfaces to describe the working status of the measurement and control subsystem, namely initialization interface, simulation control interface, model event interface, simulation status interface, operation log interface, and telemetry interface.

[0039] Step 2: Define the data type of the TT&C link list. This includes information such as link number, link type, direction flag, TT&C system, satellite transmit EIRP, satellite receive G / T value, and operating frequency. The link number is represented by a character array of fixed size 16; the link type is represented by an integer type, with a value of 0 indicating a ground link and a value of 1 indicating a relay link. The direction flag is represented by an integer type, with a value of 0 indicating transmission and a value of 1 indicating reception. The TT&C system is also represented by an integer type, while the satellite transmit EIRP, satellite receive G / T value, and operating frequency are all represented by floating-point types.

[0040] Step 3: Define the antenna data type. This includes basic information parameters, antenna type (normal, phased array), antenna mounting matrix, antenna polarization, antenna receive gain, antenna transmit gain, antenna pattern - receive, antenna pattern - transmit, antenna initial pointing, antenna pointing range constraints, and beam (list). The antenna type is represented by an integer: a value of 1 indicates a parabola, a value of 2 indicates a reflector, a value of 3 indicates a phased array, and a value of 4 indicates a helical antenna. The antenna mounting matrix is represented by a floating-point array of size 6. The antenna polarization is represented by an integer: a value of 1 indicates left-hand circular polarization, a value of 2 indicates right-hand circular polarization, a value of 3 indicates linear polarization, and a value of 4 indicates elliptical polarization. Both antenna receive gain and antenna transmit gain are represented by floating-point data. The antenna pattern - receive and antenna pattern - transmit are stored in files. The antenna initial pointing is represented by a floating-point array of size 2, with the two digits corresponding to the azimuth and elevation angles, respectively. Antenna pointing range constraints are represented using a floating-point array of size 4. The first two digits represent the azimuth start and end range, and the last two digits represent the elevation start and end range. Beams (lists) are represented using a custom beam structure.

[0041] Step 4: Define the beam structure interface, which includes information such as the beam number, beam switch status, frequency, half-cone angle, and beam pointing direction. The beam number is represented by an integer. The beam switch status is represented by an integer, with a value of 0 indicating the switch is off and a value of 1 indicating the switch is on. The frequency and half-cone angle are both represented by floating-point types. The beam pointing direction is represented by a floating-point array of size 2, where the first digit represents the azimuth angle and the second digit represents the elevation angle.

[0042] Step 5: Define the transponder data type. This includes basic information parameters, single-device general attribute parameters, and a working mode list. The working mode list is represented by a custom transponder working mode structure.

[0043] Step 6: Define the transponder operating mode list interface, which includes information such as the operating mode name, receiving channel parameters, and sending channel parameters. The operating mode name is represented by a 16-character character array, and the receiving channel parameters and sending channel parameters are both represented by a custom transponder operating mode structure.

[0044] Step 7: Define the receive and transmit channel parameter interface, which includes information such as the measurement and control system, center frequency, bandwidth, modulation mode, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, channel bit error rate, noise figure, anti-interference capability, maximum non-destructive power, and transponder output power. The measurement and control system is represented using an integer type, with a value of 0 representing incoherent spread spectrum, a value of 1 representing spread frequency hopping, and a value of 2 representing the USB unified carrier system. The center frequency, bandwidth, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, channel bit error rate, noise figure, maximum non-destructive power, and transponder output power are all represented using floating-point types. The uplink information rate, uplink frame error rate noise figure, anti-interference capability, and maximum non-destructive power are only used in the receive channel, while transponder output power is only used in the transmit channel. The modulation mode is represented using an integer type. The anti-interference capability is represented using a floating-point array of size 10.

[0045] Step 8: Define the TT&C link status data type. This includes information such as the link number, link type, direction flag, TT&C system, satellite transmit EIRP, satellite receive G / T value, and operating frequency. The link number is represented by a character array of size 16. The link type is represented by an integer type, with a value of 0 indicating a ground link and a value of 1 indicating a relay link. The direction flag is represented by an integer type, with a value of 0 indicating transmission and a value of 1 indicating reception. The TT&C system is represented by an integer type, with a value of 0 indicating incoherent spread spectrum, a value of 1 indicating spread hopping frequency, and a value of 2 indicating a USB unified carrier system. The satellite transmit EIRP, satellite receive G / T value, and operating frequency are all represented by floating-point types.

[0046] Step 9: Define the antenna status data type. This includes basic information parameters and real-time antenna pointing data. Basic information parameters are represented using floating-point data types. Real-time antenna pointing data is represented using a floating-point array of size 2, where the first digit represents the azimuth angle and the second digit represents the elevation angle.

[0047] Step 10: Define the transponder status data type. Specifically, it includes basic information parameters, single-machine general attribute parameters, current working mode, receiving channel parameters, and sending channel parameters. The current working mode is represented by an integer type. When the value is 1, it indicates non-coherent spread spectrum working mode; when the value is 2, it indicates high-speed injection working mode; when the value is 3, it indicates relay continuous service working mode; when the value is 4, it indicates relay short message service working mode; when the value is 5, it indicates random mode; when the value is 6, it indicates that the first and second modes work simultaneously; when the value is 7, it indicates that the first and third modes work simultaneously; when the value is 8, it indicates that the first and fourth modes work simultaneously; when the value is 9, it indicates that the first and fifth modes work simultaneously; when the value is 10, it indicates that the second and third modes work simultaneously; when the value is 11, it indicates that the second and fourth modes work simultaneously; when the value is 12, it indicates that the second and fifth modes work simultaneously; when the value is 13, it indicates that the third and fifth modes work simultaneously; when the value is 14, it indicates that the fourth and fifth modes work simultaneously.

[0048] Step 11: Define the receive channel parameter interface. This includes the measurement and control system, center frequency, bandwidth, modulation mode, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, and channel bit error rate. The data type and physical meaning of these fields are the same as those of the transponder receive channel parameters.

[0049] Step 12: Define the transmit channel parameter interface. This includes the measurement and control system, center frequency, bandwidth, modulation mode, telemetry information rate, channel bit error rate, and transponder output power. The data types and physical meanings of these fields are the same as those for the transponder receive channel parameters.

[0050] Step 13: Define the measurement and control data type. This includes basic information parameters, power consumption, heat consumption, power on / off status, output power, and other data. Power consumption, heat consumption, power on / off status, and output power are all represented using floating-point data types.

[0051] Step 14: Define the data type for the measurement and control wave controller status. This includes basic information parameters, power consumption, heat consumption, and power on / off status. Power consumption and heat consumption are represented using floating-point data types. Power on / off status is represented using integer data types, with a value of 0 indicating power off and a value of 1 indicating power on.

[0052] Those skilled in the art will appreciate that, in addition to implementing the system, device, and various modules provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same program in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, embedded microcontrollers, and the like by logically programming the method steps. Therefore, the system, device, and various modules provided by the present invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; the modules for implementing various functions can also be considered both software programs for implementing the method and structures within the hardware component.

[0053] 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 method for designing a digital analog interface for a satellite measurement and control subsystem, characterized in that: include: Six types of interfaces are used to describe the working status of the measurement and control subsystem, namely initialization interface, simulation control interface, model event interface, simulation status interface, operation log interface and telemetry interface; Among them, the initialization interface, simulation control interface and model event interface are used for input data of the subsystem, and the simulation status interface, operation log interface and telemetry interface are used for data output; The specific process is: Step 1: Define the initialization interface of the measurement and control link model and the simulation control interface of the measurement and control subsystem; Step 2: Define the measurement and control link list data type and the measurement and control link status data type; Step 3: Define antenna data type and antenna status data type; Step 4: Define the beam structure interface; Step 5: Define transponder data type, define transponder working mode list interface and define transponder status data type; Step 6: Define the receiving and sending channel parameter interface; Step 7: Define the measurement and control fixed release data type and the measurement and control wave control machine status data type.

2. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The initialization interface includes basic information parameters, system power consumption, system heat consumption, working mode selection, initial working status, measurement and control link list, antenna list and transponder list information; The simulation control interface includes basic information parameters, measurement and control mode, total power consumption, total heat consumption, system fault status, measurement and control link status, antenna status, transponder status, measurement and control fixed release status, wave control machine status and real-time simulation information of on-board telemetry data.

3. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The measurement and control link list data includes: link number, link type, direction mark, measurement and control system, satellite transmission EIRP, satellite reception G / T value and operating frequency information; The link number is represented by a character array of fixed size 16; the link type is represented by an integer type, with a value of 0 indicating a ground link and a value of 1 indicating a relay link; the direction flag is represented by an integer type, with a value of 0 indicating sending and a value of 1 indicating receiving; the measurement and control system is represented by an integer type; the satellite transmit EIRP, satellite receive G / T value and operating frequency are all represented by floating-point type.

4. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The antenna data includes: basic information parameters, antenna type, antenna installation matrix, antenna polarization mode, antenna receiving gain, antenna transmitting gain, antenna pattern - receiving, antenna pattern - transmitting, antenna initial pointing, antenna pointing range constraint and beam information; Basic information parameters are represented by floating-point types; antenna type is represented by integer type, with a value of 1 indicating a parabola, a value of 2 indicating a reflector, a value of 3 indicating a phased array, and a value of 4 indicating a helical antenna; the antenna installation matrix is represented by a floating-point array of size 6; the antenna polarization mode is represented by an integer type, with a value of 1 indicating left-hand circular polarization, a value of 2 indicating right-hand circular polarization, a value of 3 indicating linear polarization, and a value of 4 indicating elliptical polarization; both antenna receive gain and antenna transmit gain are represented by floating-point types; antenna radiation pattern - receive and antenna radiation pattern - transmit are stored in files; the antenna initial pointing is represented by a floating-point array of size 2, with the two digits in the array corresponding to the azimuth and elevation angles, respectively; the antenna pointing range constraint is represented by a floating-point array of size 4, with the first two digits indicating the start and end range of the azimuth angle, and the last two digits indicating the start and end range of the elevation angle; the beam is represented by a custom beam structure.

5. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The beam structure interface includes: beam number, beam switch status, frequency, half-cone angle and beam pointing information; the beam number is represented by an integer type; the beam switch status is represented by an integer type, when the value is 0, it means the switch is in the off state, when the value is 1, it means the switch is on; the frequency and half-cone angle are both represented by floating-point types; the beam pointing is represented by a floating-point type array of size 2, where the first bit represents the azimuth angle and the second bit represents the pitch angle.

6. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The transponder data includes: basic information parameters, single-machine general attribute parameters and a working mode list, wherein the working mode list is represented by a custom transponder working mode structure; The transponder working mode list includes: working mode name, receiving channel parameters and sending channel parameter information, wherein the working mode name is represented by a character type array of size 16, and the receiving channel parameters and sending channel parameters are both represented by a custom transponder working mode structure.

7. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The receiving and transmitting channel parameters include: measurement and control system, center frequency, bandwidth, modulation mode, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, channel bit error rate, noise figure, anti-interference capability, maximum non-destructive power and transponder output power information; The measurement and control system is represented by an integer type. A value of 0 represents incoherent spread spectrum, a value of 1 represents spread frequency hopping, and a value of 2 represents a USB unified carrier system. The center frequency, bandwidth, sensitivity, remote control code rate, uplink information rate, uplink frame error rate, channel bit error rate, noise figure, maximum undamaged power, and transponder output power are all represented by floating-point types. The uplink information rate, uplink frame error rate noise figure, anti-interference capability, and maximum undamaged power are only used in the receiving channel, and the transponder output power is only used in the transmitting channel. The modulation mode is represented by an integer type. The anti-interference capability is represented by a floating-point array of size 10.

8. The satellite measurement and control subsystem digital analog interface design method according to claim 1 is characterized in that: The measurement and control link status data includes: link number, link type, direction flag, measurement and control system, satellite transmission EIRP, satellite reception G / T value and operating frequency information; The link number is represented by a character array of size 16; the link type is represented by an integer type, with a value of 0 indicating a ground link and a value of 1 indicating a relay link; the direction flag is represented by an integer type, with a value of 0 indicating sending and a value of 1 indicating receiving; the measurement and control system is represented by an integer type, with a value of 0 indicating incoherent spread spectrum, a value of 1 indicating spread hopping frequency, and a value of 2 indicating a USB unified carrier system; the satellite transmit EIRP, satellite receive G / T value, and operating frequency are all represented by floating-point types.

9. The satellite measurement and control subsystem digital analog interface design method according to claim 1, characterized in that: The transponder status data includes: the current working mode is represented by an integer type. When the value is 1, it indicates the non-coherent spread spectrum working mode; when the value is 2, it indicates the high-speed injection working mode; when the value is 3, it indicates the relay continuous service working mode; when the value is 4, it indicates the relay short message service working mode; when the value is 5, it indicates the casual mode; when the value is 6, it indicates that the first and second modes work at the same time; when the value is 7, it indicates that the first and third modes work at the same time; when the value is 8, it indicates that the first and fourth modes work at the same time; when the value is 9, it indicates that the first and fifth modes work at the same time; when the value is 10, it indicates that the second and third modes work at the same time; when the value is 11, it indicates that the second and fourth modes work at the same time; when the value is 12, it indicates that the second and fifth modes work at the same time; when the value is 13, it indicates that the third and fifth modes work at the same time; and when the value is 14, it indicates that the fourth and fifth modes work at the same time.

10. The satellite measurement and control subsystem digital analog interface design method according to claim 1, characterized in that: The measurement and control fixed-discharge data includes: basic information parameters, power consumption, heat consumption, power on / off status and output power data, and the power consumption, heat consumption, power on / off status and output power are all represented by floating point type; The measurement and control wave control machine status data includes: basic information parameters, power consumption, heat consumption and power on / off status data; power consumption and heat consumption are represented by floating point type, and power on / off status is represented by integer type, when the value is 0, it means shutdown, and when the value is 1, it means startup.

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