阅读说明：本技术 深空探测环绕器对着陆器接口测试系统 (Deep space exploration surrounding device to lander interface test system ) 是由 汪栋硕 王森 王继业 朱新波 张旭光 王民建 于 2021-08-19 设计创作，主要内容包括：本发明提供了一种深空探测环绕器对着陆器接口测试系统,包括以下设备：器间低频线路转接设备、着陆器供配电模拟设备、着陆器有线测控模拟设备、器间射频链路衰减设备、着陆器UHF频段射频测控模拟设备、着陆器X频段通信模拟设备和着陆器载荷模拟源设备。本发明提供的深空探测环绕器对着陆器接口测试系统,能够在深空探测环绕器与着陆器装配对接前对环绕器上的两器接口模块进行自检,检查环绕器对着陆器供配电接口、低频有线测控接口、射频通信接口的匹配性和工作协调性,避免在两器对接后因接口不匹配而导致两器之间接口功能异常和安全隐患。(The invention provides a deep space exploration surrounding device to lander interface test system, which comprises the following equipment: the system comprises inter-device low-frequency line switching equipment, lander power supply and distribution simulation equipment, lander wired measurement and control simulation equipment, inter-device radio frequency link attenuation equipment, lander UHF frequency band radio frequency measurement and control simulation equipment, lander X frequency band communication simulation equipment and lander load simulation source equipment. The deep space detection surrounding device to lander interface test system provided by the invention can carry out self-inspection on the interface modules of the two devices on the surrounding device before the deep space detection surrounding device and the lander are assembled and butted, check the matching performance and the working coordination of the surrounding device to a lander power supply and distribution interface, a low-frequency wired measurement and control interface and a radio frequency communication interface, and avoid the abnormal function and the potential safety hazard of the interfaces between the two devices caused by the unmatched interfaces after the two devices are butted.)

1. A deep space exploration surround to lander interface test system, characterized by, includes the following equipment:

inter-device low-frequency line switching equipment: the device is used for adapting the connection point switching between the low-frequency signal interface of the deep space detection surrounding device facing the lander and the lander power supply and distribution simulation equipment and the lander wired measurement and control simulation equipment; the lander low-frequency signal interface is connected with the deep space detection surrounding device through an inter-device low-frequency interconnection cable, and is connected with lander power supply and distribution simulation equipment and lander wired measurement and control simulation equipment through a low-frequency cable;

lander power supply and distribution simulation equipment: the testing system is used for testing the functions of a power supply interface and a charging interface of the deep space exploration surrounding device to the lander;

lander wired measurement and control simulation equipment: the system is used for testing the function of the low-frequency wired measurement and control interface of the deep space exploration surrounding device to the lander;

inter-device radio frequency link attenuation device: the system is used for realizing the attenuation of radio frequency signals between the deep space detection surrounding device facing the land device radio frequency signal interface and the lander UHF frequency band radio frequency measurement and control simulation equipment and the lander X frequency band communication simulation equipment; forward and backward radio frequency signals are transmitted to the ground device radio frequency signal interface through the radio frequency cable in a wired mode or through the ground antenna and the onboard antenna in a wireless mode; the system is connected with lander UHF frequency band radio frequency measurement and control simulation equipment through a radio frequency cable to transmit a telemetering return signal between UHF frequency band devices and a telemetering forward signal between UHF frequency band devices; the X-band communication simulation device is connected with the lander X-band communication simulation device through a radio frequency cable to transmit return signals between the X-band devices;

lander UHF frequency channel radio frequency observes and controls analog device: the system is used for testing the UHF frequency band radio frequency measurement and control interface function of the deep space exploration surrounding device to the lander;

lander X frequency channel communication analog equipment: the system is used for testing the function of an X-frequency band radio frequency interface of the deep space exploration surrounding device to the lander;

lander load simulation source equipment: for generating lander load simulation data; and the low-frequency cable is connected with the X-frequency-band communication simulation equipment of the lander.

2. The deep space exploration surround to lander interface test system of claim 1, wherein: the lander power supply and distribution simulation equipment comprises a power supply load simulation module and a charging function simulation module, wherein the power supply load simulation module simulates the power consumption of each track stage when the lander flies on the track and is used for testing the power supply function of the lander by the deep space detection surrounding device before the two devices are separated; the charging function simulation module has two working modes of constant-current charging and constant-voltage charging and is used for testing the charging function of the deep space detection surrounding device on the storage battery of the lander before the two devices are separated.

3. The deep space exploration surround to lander interface test system of claim 1, wherein: the land device wired measurement and control simulation equipment has the function of simulating the lander to receive the wired channel remote control instruction of the deep space detection surrounding device before the two devices are separated, and has the function of simulating the wired channel remote control instruction fed back to the deep space detection surrounding device.

4. The deep space exploration surround to lander interface test system of claim 3, wherein: the land device wired measurement and control simulation equipment is used for simulating and receiving the deep space detection surrounding device to send multi-channel OC door instructions, detecting and displaying the instruction pulse width of the deep space detection surrounding device, simulating instruction response, providing corresponding analog quantity telemetering simulation signals to the deep space detection surrounding device, and testing the wired telemetering acquisition interface function of the deep space channel simulator.

5. The deep space exploration surround to lander interface test system of claim 3, wherein: the land device wired measurement and control simulation equipment is used for simulating the communication function of an asynchronous RS422 interface between the lander and the deep space exploration surrounding device, receiving and displaying a remote control note number instruction sent by the deep space exploration surrounding device through the RS422 interface, and sending simulation telemetering data to the deep space exploration surrounding device through the RS422 interface.

6. The deep space exploration surround to lander interface test system of claim 1, wherein: the attenuation device of the radio frequency link between the devices comprises a main control module and a plurality of program control attenuation combinations, each program control attenuation combination forms an attenuation link, attenuation values of the program control attenuation combinations in the attenuation links are set through a local control mode and a network remote control mode, and functions of dynamically setting the attenuation values of the attenuation links are achieved.

7. The deep space exploration surround to lander interface test system of claim 6, wherein: when the attenuation link works in a dynamic mode, a series of attenuation values and corresponding duration time are preset in a configuration table mode, and after the attenuation link works, the attenuation values of the attenuation link are sequentially and dynamically set according to the configuration table to simulate the dynamic change state of the space attenuation of the radio frequency signal.

8. The deep space exploration surround to lander interface test system of claim 1, wherein: the lander UHF frequency channel radio frequency measurement and control simulation equipment is used for simulating a UHF frequency channel relay communication function between the lander and the deep space exploration surrounding device after the lander and the deep space exploration surrounding device are separated, and comprises the following components:

receiving forward data of communication between UHF frequency range devices sent by a deep space detection surrounding device, and performing down-conversion, demodulation and channel decoding display;

generating communication return data between UHF frequency range devices, completing channel coding, modulation and up-conversion, and then sending the data to a deep space exploration surround device UHF frequency range relay communication machine;

when the UHF frequency band forward and backward data communication is carried out with the deep space sounding surround device, the communication data format and the transmission flow conform to the CCSDS adjacent space protocol specification.

9. The deep space exploration surround to lander interface test system of claim 1, wherein: the lander X-frequency-band communication simulation device is used for simulating an X-frequency-band relay communication function between the lander and the deep space detection surrounding device after the two devices are separated, receiving a simulation load data frame generated by the lander load simulation source device, carrying out channel coding, scrambling, modulation and up-conversion, and then sending the simulation load data frame to the deep space detection surrounding device X-frequency-band relay communication machine.

10. The deep space exploration surround to lander interface test system of claim 1, wherein: the lander load simulation source equipment is used for generating a data frame with fixed content, supporting reading of a load data file, and performing frame format encapsulation according to a CCSDS advanced on-orbit system protocol format to form a simulation load data frame.

Technical Field

The invention relates to the technical field of spacecraft testing, in particular to a deep space exploration surrounding device land facing device interface testing system.

Background

In deep space exploration engineering, a deep space probe typically comprises a surround device and a lander, wherein the surround device and the lander can independently execute corresponding work tasks and have compact functional interfaces. Before the two devices are separated, the surrounding device provides energy supply for the work of the lander and the charging of a storage battery, and provides a wired measurement and control channel for the work setting and the state detection of the lander; after the two devices are separated, the surround provides the lander with relay communication with the earth station.

In order to ensure the safety and normal function of the interface after the two devices are butted, the self-checking test of the deep space detection surrounding device facing to the interface of the land device is required before the two devices are butted. The interface state and function of the deep space exploration surrounding device to the lander are greatly different from the interfaces of the sub systems of the near space vehicle, the existing near space vehicle test system cannot meet the test requirement of the deep space exploration surrounding device to the lander interface, and the test system needs to be designed according to the characteristic that the deep space exploration surrounding device faces the lander interface.

Through the search of the prior art, the invention patent with the publication number of CN202189106U discloses an automatic test system for a satellite low-frequency signal interface, which comprises a contact switching device, an oscilloscope, a digital multimeter, a monitoring computer and a transfer cable, and is suitable for low-frequency signal detection and the conduction insulation inspection of a low-frequency cable network, and does not have the power supply and distribution interface test function between a deep space exploration surrounding device and a lander, the wired measurement and control interface test function and the radio frequency signal interface test function described in the patent.

The invention patent with the publication number of CN202085171U discloses a universal satellite earth and satellite wired interface test system, which comprises main test equipment, an interface adapter, a drop electric connector interface cable, a CAN bus interface cable and an inter-equipment connecting cable, wherein the test system is used for collecting, processing, analyzing, storing and displaying earth and satellite wired analog quantity signals, RS422 signals and CAN bus signals, and does not have the power supply and distribution interface test function, the wired measurement and control interface test function and the radio frequency signal interface test function between a deep space exploration surrounding device and a lander, which are described in the patent.

The invention patent with application publication number CN103913672A discloses an automatic test system for a satellite low-frequency interface, which at least comprises an automatic test platform for a satellite low-frequency interface and an automatic interface tester, and the test system does not have the power supply and distribution interface test function between a deep space exploration circulator and a lander, the wired measurement and control interface test function, and the radio frequency signal interface test function.

Chinese patent publication No. CN110568307A discloses an automatic testing apparatus and method for satellite single-computer interface. The test device comprises: the test instrument is used for testing the satellite single machine; the switch array is provided with an input port, an output port, a control port and a switch matrix; a controller for controlling the test instrument and the switch array; the first transfer line is used for connecting the output port of the satellite single machine and the input port of the switch array; and the second patch cord is used for connecting the output port of the switch array with the input port of the test instrument. The test method is as follows: the controller develops the test tasks according to the pre-planned test task sequence, and replaces the connected single machine interface and the test instrument after the single function test until all the planned task sequences are executed.

Disclosure of Invention

In view of the deficiencies in the prior art, it is an object of the present invention to provide a deep space sounding surround-to-land interface test system.

The invention provides a deep space exploration surrounding device to lander interface test system which comprises the following equipment:

inter-device low-frequency line switching equipment: the device is used for adapting the connection point switching between the low-frequency signal interface of the deep space detection surrounding device facing the lander and the lander power supply and distribution simulation equipment and the lander wired measurement and control simulation equipment; the lander low-frequency signal interface is connected with the deep space detection surrounding device through an inter-device low-frequency interconnection cable, and is connected with lander power supply and distribution simulation equipment and lander wired measurement and control simulation equipment through a low-frequency cable;

lander power supply and distribution simulation equipment: the testing system is used for testing the functions of a power supply interface and a charging interface of the deep space exploration surrounding device to the lander;

lander wired measurement and control simulation equipment: the system is used for testing the function of the low-frequency wired measurement and control interface of the deep space exploration surrounding device to the lander;

inter-device radio frequency link attenuation device: the system is used for realizing the attenuation of radio frequency signals between the deep space detection surrounding device facing the land device radio frequency signal interface and the lander UHF frequency band radio frequency measurement and control simulation equipment and the lander X frequency band communication simulation equipment; forward and backward radio frequency signals are transmitted to the ground device radio frequency signal interface through the radio frequency cable in a wired mode or through the ground antenna and the onboard antenna in a wireless mode; the system is connected with lander UHF frequency band radio frequency measurement and control simulation equipment through a radio frequency cable to transmit a telemetering return signal between UHF frequency band devices and a telemetering forward signal between UHF frequency band devices; the X-band communication simulation device is connected with the lander X-band communication simulation device through a radio frequency cable to transmit return signals between the X-band devices;

lander UHF frequency channel radio frequency observes and controls analog device: the system is used for testing the UHF frequency band radio frequency measurement and control interface function of the deep space exploration surrounding device to the lander;

lander X frequency channel communication analog equipment: the system is used for testing the function of an X-frequency band radio frequency interface of the deep space exploration surrounding device to the lander;

lander load simulation source equipment: for generating lander load simulation data; and the low-frequency cable is connected with the X-frequency-band communication simulation equipment of the lander.

Preferably, the lander power supply and distribution simulation equipment comprises a power supply load simulation module and a charging function simulation module, wherein the power supply load simulation module simulates the power consumption of each track stage when the lander flies on the track and is used for testing the power supply function of the lander by the deep space detection surrounding device before the two devices are separated; the charging function simulation module has two working modes of constant-current charging and constant-voltage charging and is used for testing the charging function of the deep space detection surrounding device on the storage battery of the lander before the two devices are separated.

Preferably, the land device wired measurement and control simulation equipment has the function of simulating the lander to receive the wired channel remote control instruction of the deep space detection surrounding device before the two devices are separated, and has the function of simulating the feedback of the wired channel remote control instruction to the deep space detection surrounding device.

Preferably, the land device wired measurement and control simulation equipment is used for simulating and receiving the deep space exploration surrounding device to send a multi-channel OC door instruction, detecting and displaying the instruction pulse width of the deep space exploration surrounding device, simulating the instruction response, providing a corresponding analog quantity telemetering simulation signal to the deep space exploration surrounding device, and testing the wired telemetering acquisition interface function of the deep space channel simulator.

Preferably, the land device wired measurement and control simulation equipment is used for simulating the communication function of an asynchronous RS422 interface between the lander and the deep space exploration surrounding device, receiving and displaying a remote control note number instruction sent by the deep space exploration surrounding device through the RS422 interface, and sending simulation telemetering data to the deep space exploration surrounding device through the RS422 interface.

Preferably, the inter-device radio frequency link attenuation device includes a main control module and a plurality of program-controlled attenuation combinations, each program-controlled attenuation combination constitutes an attenuation link, attenuation values of the program-controlled attenuation combinations in the attenuation links are set in a local control and network remote control mode, and functions of dynamically setting the attenuation values of the attenuation links are provided.

Preferably, when the attenuation link works in a dynamic mode, a series of attenuation values and corresponding duration time are preset in a configuration table form, and after the work is started, the attenuation values of the attenuation link are sequentially and dynamically set according to the configuration table to simulate the dynamic change state of the spatial attenuation of the radio frequency signal.

Preferably, the lander UHF-band radio frequency measurement and control simulation device is used for simulating a UHF-band relay communication function between the lander and the deep space exploration surrounding device after the two devices are separated, and includes:

receiving forward data of communication between UHF frequency range devices sent by a deep space detection surrounding device, and performing down-conversion, demodulation and channel decoding display;

generating communication return data between UHF frequency range devices, completing channel coding, modulation and up-conversion, and then sending the data to a deep space exploration surround device UHF frequency range relay communication machine;

when the UHF frequency band forward and backward data communication is carried out with the deep space sounding surround device, the communication data format and the transmission flow conform to the CCSDS adjacent space protocol specification.

Preferably, the lander X-band communication simulation device is configured to simulate an X-band relay communication function between the lander and the deep space exploration surrounding device after the two devices are separated, receive a simulated load data frame generated by the lander load simulation source device, perform channel coding, scrambling, modulation and up-conversion, and send the simulated load data frame to the deep space exploration surrounding device X-band relay communication machine.

Preferably, the lander load simulation source device is configured to generate a data frame with fixed content, support reading of a load data file, and perform frame format encapsulation according to a CCSDS advanced on-track system protocol format to form a simulation load data frame.

Compared with the prior art, the invention has the following beneficial effects:

1. the interface test system of the deep space detection surrounding device to the lander can carry out self-inspection on the two interface modules on the surrounding device before the deep space detection surrounding device is assembled and butted with the lander;

2. the testing system for the interface of the deep space exploration surrounding device facing the lander can check the matching and working coordination of the surrounding device to the power supply and distribution interface, the low-frequency wired measurement and control interface and the radio frequency communication interface of the lander;

3. the deep space exploration surrounding device land facing device interface testing system can avoid the problem that the interfaces of two devices are not matched after the two devices are in butt joint, so that the functions of the interfaces between the two devices are abnormal and potential safety hazards are caused.

Drawings

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

FIG. 1 is a block diagram of a deep space sounding surround-lander interface test system.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

As shown in fig. 1, the present invention provides a deep space exploration surround to lander interface test system, which includes:

inter-device low-frequency line switching equipment: the device is used for adapting the connection point switching between the low-frequency signal interface of the deep space detection surrounding device facing the lander and the lander power supply and distribution simulation equipment and the lander wired measurement and control simulation equipment; the lander low-frequency signal interface is connected with the deep space detection surrounding device through an inter-device low-frequency interconnection cable, and is connected with lander power supply and distribution simulation equipment and lander wired measurement and control simulation equipment through a low-frequency cable;

lander power supply and distribution simulation equipment: the testing system is used for testing the functions of a power supply interface and a charging interface of the deep space exploration surrounding device to the lander;

lander wired measurement and control simulation equipment: the system is used for testing the function of the low-frequency wired measurement and control interface of the deep space exploration surrounding device to the lander;

inter-device radio frequency link attenuation device: the system is used for realizing the attenuation of radio frequency signals between the deep space detection surrounding device facing the land device radio frequency signal interface and the lander UHF frequency band radio frequency measurement and control simulation equipment and the lander X frequency band communication simulation equipment; forward and backward radio frequency signals are transmitted to the ground device radio frequency signal interface through the radio frequency cable in a wired mode or through the ground antenna and the onboard antenna in a wireless mode; the system is connected with lander UHF frequency band radio frequency measurement and control simulation equipment through a radio frequency cable to transmit a telemetering return signal between UHF frequency band devices and a telemetering forward signal between UHF frequency band devices; the X-band communication simulation device is connected with the lander X-band communication simulation device through a radio frequency cable to transmit return signals between the X-band devices;

lander UHF frequency channel radio frequency observes and controls analog device: the system is used for testing the UHF frequency band radio frequency measurement and control interface function of the deep space exploration surrounding device to the lander;

lander X frequency channel communication analog equipment: the system is used for testing the function of an X-frequency band radio frequency interface of the deep space exploration surrounding device to the lander;

lander load simulation source equipment: for generating lander load simulation data; and the low-frequency cable is connected with the X-frequency-band communication simulation equipment of the lander.

In the test system, the lander power supply and distribution simulation equipment comprises a power supply load simulation module and a charging function simulation module, wherein the power supply load simulation module can simulate the power consumption of each track stage when the lander flies on the track, the maximum simulation power consumption can reach 500W, and the power supply load simulation module is used for testing the power supply function of the deep space detection surrounding device to the lander before the two devices are separated; the charging function simulation module has two working modes of constant-current charging and constant-voltage charging, can adapt to the maximum 10A charging current during constant-current charging, can adapt to the 29V-29.5V charging voltage during constant-voltage charging, and is used for testing the charging function of the deep space exploration surrounding device to the storage battery of the lander before the two devices are separated.

In the test system, the lander wired measurement and control simulation equipment has the function of simulating the lander to receive the wired channel remote control instruction of the deep space detection surrounding device before the two devices are separated, and has the function of simulating the feedback of the wired channel remote control instruction to the deep space detection surrounding device. The device can simulate and receive at most 15 paths of OC door instructions sent by the deep space detection surrounding device, detect and display the instruction pulse width, simulate the instruction response, provide corresponding analog quantity telemetering simulation signals to the deep space detection surrounding device and test the wired telemetering acquisition interface function of the deep space channel simulator; the remote control data acquisition system can simulate the communication function of an asynchronous RS422 interface between the lander and the deep space exploration surrounding device, receive and display a remote control injection number instruction sent by the deep space exploration surrounding device through the RS422 interface, and send simulated telemetry data to the deep space exploration surrounding device through the RS422 interface.

In the test system, the attenuation equipment for the radio frequency link between the devices comprises a main control module and 3 program-controlled attenuators which are combined to form 3 attenuation links which are respectively used for a UHF frequency band return link, a UHF frequency band forward link and an X frequency band return link between the two devices, the attenuation values of the program-controlled attenuators in the attenuation links can be set in a local control and network remote control mode, the attenuation value range of each attenuator is 0-121 dB, and the working frequency band covers the range of DC-10 GHz; when a certain attenuation link works in a dynamic mode, a series of attenuation values and corresponding duration time are preset in a configuration table form, and after the work is started, the attenuation values of the attenuation link are sequentially and dynamically set according to the configuration table and are used for simulating the dynamic change state of the space attenuation of the radio frequency signal.

In the testing system, the lander UHF frequency band radio frequency measurement and control simulation equipment is used for simulating the UHF frequency band relay communication function between the lander and the deep space detection surrounding device after the two devices are separated, on one hand, the landing device receives the UHF frequency band communication forward data sent by the deep space detection surrounding device, and performs down-conversion, demodulation and channel decoding display; and on the other hand, generating communication return data between the UHF frequency range devices, finishing channel coding, modulation and up-conversion, and then sending the data to the deep space exploration surround device UHF frequency range relay communication machine. When the UHF frequency band forward and backward data communication is carried out with the deep space sounding surround device, the communication data format and the transmission flow conform to the CCSDS adjacent space protocol specification.

In the test system, the lander X-frequency-band communication simulation device is used for simulating the X-frequency-band relay communication function between the lander and the deep space detection surrounding device after the two devices are separated, receiving a simulation load data frame generated by the lander load simulation source device, carrying out channel coding, scrambling, modulation and up-conversion, and then sending the simulation load data frame to the deep space detection surrounding device X-frequency-band relay communication machine.

In the test system, the lander load simulation source equipment can generate a data frame with fixed content, supports reading a load data file, performs frame format encapsulation according to a CCSDS advanced on-orbit system protocol format to form a simulation load data frame, and sends the simulation load data frame to the lander X-band communication simulation equipment through a synchronous RS422 interface.

The deep space detection surrounding device to lander interface test system provided by the invention can carry out self-inspection on the interface modules of the two devices on the surrounding device before the deep space detection surrounding device and the lander are assembled and butted, check the matching performance and the working coordination of the surrounding device to a lander power supply and distribution interface, a low-frequency wired measurement and control interface and a radio frequency communication interface, and avoid the abnormal function and the potential safety hazard of the interfaces between the two devices caused by the unmatched interfaces after the two devices are butted.

Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.