CN111506044B - General off-line detection device for spacecraft - Google Patents
General off-line detection device for spacecraft Download PDFInfo
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- CN111506044B CN111506044B CN202010329176.7A CN202010329176A CN111506044B CN 111506044 B CN111506044 B CN 111506044B CN 202010329176 A CN202010329176 A CN 202010329176A CN 111506044 B CN111506044 B CN 111506044B
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- line detection
- power supply
- spacecraft
- test board
- board card
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Abstract
The invention relates to a general off-line detection device for a spacecraft, which comprises: the power supply module is used for being connected with a power supply and distribution system of the spacecraft to supply power to the whole on-orbit off-line detection unit and the detected equipment; the CPCI bus back board realizes the functions of plugging, data transmission and synchronous triggering of each module of the on-track off-line detection unit; the off-line detection main control board is used for coordinating and scheduling each module and the test board card in the whole off-line detection, and realizing data exchange and control between each module and the test board card; the analog quantity output and acquisition test board card is used for testing the AD function of the tested equipment and acquiring the analog quantity of the tested equipment; the 1553B bus test board card is in 1553B bus communication with the tested equipment and can simulate BC and RT functions; the instruction sending and detecting test board card outputs the instruction to the tested equipment through the computer control instruction, and identifies whether the instruction amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements or not.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a universal off-line detection device for a spacecraft.
Background
With the gradual maturity and development of manned spacecraft technology, the spacecraft has larger and larger scale and higher long service life requirement, and a spacecraft is required to participate in fault detection of important equipment in orbit so as to maintain the long service life and high reliability of the spacecraft.
The on-orbit off-line detection is a system project, namely after a product detects a fault, in order to maintain the main functions and tasks of the whole aircraft and ensure the safety of the system and astronauts, equipment needs to be isolated from the system and is set to be in an off-line detection mode, a special off-line detection device is adopted to carry out fault location test on the equipment, the fault reason is further checked and confirmed, and the function recovery condition after maintenance is checked, so that on one hand, the safety of the system is ensured, and the main functions and tasks of the whole aircraft are not influenced by maintenance operation; on the other hand, the safety of the astronaut is required to be ensured, and the on-orbit maintenance test operation of the astronaut is supported to be realized. Meanwhile, because the large-sized long-life spacecraft needs to complete the replacement of the maintainable equipment in orbit, the off-line detection equipment is needed to implement the test and verification of the information interface before the on-orbit maintenance spare part system. Therefore, the on-orbit off-line detection device for the aircraft for the spacecraft is needed to fulfill the above requirements.
Disclosure of Invention
The invention aims to solve the problems and provides a universal off-line detection device for a spacecraft.
In order to achieve the above object, the present invention provides a general off-line detection device for a spacecraft, comprising:
the power supply module is used for being connected with a power supply and distribution system of the spacecraft to supply power to the whole on-orbit off-line detection unit and the detected equipment;
the CPCI bus back board realizes the functions of plugging, data transmission and synchronous triggering of each module of the on-track off-line detection unit;
the off-line detection main control board is used for coordinating and scheduling each module and the test board card in the whole off-line detection, and realizing data exchange and control between each module and the test board card;
the analog quantity output and acquisition test board card is used for testing the AD function of the tested equipment and acquiring the analog quantity of the tested equipment;
the 1553B bus test board card is in 1553B bus communication with the tested equipment and can simulate BC and RT functions;
the instruction sending and detecting test board card outputs the instruction to the tested equipment through the computer control instruction, and identifies whether the instruction amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements or not.
According to one aspect of the invention, the power supply module has a power supply interface protection function, and the power supply interface protection function is a 100V-to- +/-12V and 5VDC/DC module.
According to one aspect of the invention, the CPCI bus backplane provides node definitions for both 12V and 5V power.
According to one aspect of the invention, the analog quantity output and acquisition test board card tests the AD function of the tested equipment, sets corresponding analog quantity, the number of paths is 32, the output range is 0V-5.2V, and the precision is +/-2.5 mV;
and (3) collecting analog quantity of the tested equipment, wherein the channel number is 64 channels of single ends/32 channels of double ends, the output range is 0V-5.2V, and the precision is +/-2.5 mV.
According to one aspect of the invention, the 1553B bus test board can be set to be in an MT mode, A B two-way bus.
According to one aspect of the invention, the instruction sending and detecting test board card outputs 32-path OC instructions to the tested equipment through a computer control instruction, the instruction amplitude is greater than 28V, and the driving current is greater than 200 mA;
and identifying whether the command amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements, and the precision is +/-1 ms.
According to one aspect of the invention, the power supply module provides power supply conversion for the inside of the tested device and power supply and power off functions for the tested device, and comprises a power supply circuit, a power supply conversion circuit and a control circuit;
the power supply conversion circuit consists of a filter and a power supply module;
and the secondary power supplies converted by the plurality of DC/DC modules on the power supply module are directly connected.
According to one aspect of the invention, the system further comprises offline detection control software which is arranged in the computer system and adapts to the test tasks of different ORUs according to user configuration; the off-line detection interface software is operated in the off-line detection main control board and is used for realizing the configuration and management of the off-line detection device hardware interface;
the off-line detection control software is communicated with the off-line detection interface software, and data and detection results are displayed to the astronaut;
the off-line detection interface software receives the off-line detection control software instruction information, sends excitation data to the test board card, drives the corresponding test board card to complete the functions of hundred-mega Ethernet port, gigabit Ethernet port, 1553B communication, OC door instruction sending and receiving, analog quantity acquisition and the like, and transmits the detected information to the control software to complete the test result feedback.
According to the general off-line detection device, the further checking, positioning and checking of the fault reasons of the existing on-orbit fault equipment of the spacecraft are realized, the function recovery condition after the maintenance is checked is also realized, and the information interface test and verification before the on-orbit maintenance spare part system is completed.
The invention introduces the mature civil test board card into the aerospace product design, improves the system development capability and the production efficiency, reduces the development cost and shortens the development period.
The invention can realize the fault reason of the fault equipment on the spacecraft in the on-orbit mode, further check, position and check the function recovery condition after maintenance, and complete the test and verification of the information interface before the on-orbit maintenance spare part system is installed.
Drawings
Fig. 1 schematically shows a structural relationship diagram of a general off-line detection device for a spacecraft according to the present invention;
FIG. 2 is a block diagram of a power module assembly;
FIG. 3 is a diagram illustrating a grounding relationship of the general offline inspection apparatus;
fig. 4 is a view schematically showing a connection relationship of a general off-line detecting apparatus for a spacecraft according to the present invention;
fig. 5 schematically shows an on-orbit off-line detection working sequence diagram of a space station of the general off-line detection device for the spacecraft according to the invention;
fig. 6 schematically shows a principle view of an off-line inspection apparatus according to the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a structural relationship diagram of a general off-line detection device for a spacecraft according to the invention. As shown in fig. 1, the general offline detection apparatus for a spacecraft according to the present invention includes:
the power supply module is used for being connected with a power supply and distribution system of the spacecraft to supply power to the whole on-orbit off-line detection unit and the detected equipment;
the CPCI bus back board realizes the functions of plugging, data transmission and synchronous triggering of each module of the on-track off-line detection unit;
the off-line detection main control board is used for coordinating and scheduling each module and the test board card in the whole off-line detection, and realizing data exchange and control between each module and the test board card;
the analog quantity output and acquisition test board card is used for testing the AD function of the tested equipment and acquiring the analog quantity of the tested equipment;
the 1553B bus test board card is in 1553B bus communication with the tested equipment and can simulate BC and RT functions;
the instruction sending and detecting test board card outputs the instruction to the tested equipment through the computer control instruction, and identifies whether the instruction amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements or not.
In the invention, the offline detection device adopts a CPCI standard case, 8 slots and one system slot are selected for the case, all other card slots can be used in common, the interior of one case can be expanded, and if the function expansion exceeds the range of one case, the case interconnection can be realized through a network switch and a network cable. The inside has the backplate, and the function integrated circuit board can be inserted in the backplate groove, and the front panel is walked the line, and the power supply of rear panel and ground connection.
According to one embodiment of the invention, the power supply module has a power supply interface protection function, so that power supply isolation and protection are realized, if the on-rail off-line detection unit is short-circuited during power supply, a superior power supply path can be cut off in time, and the whole aircraft cannot be lost. The 100V-12V and 5VDC/DC modules are adopted for the on-track off-line detection unit internal module and the power supply of the detected device.
In this embodiment, the CPCI bus backplane provides node definitions for 12V and 5V power.
The analog quantity output and acquisition test board card tests the AD function of the tested equipment, corresponding analog quantity is set, the number of paths is 32, the output range is 0V-5.2V, and the precision is +/-2.5 mV;
and (3) collecting analog quantity of the tested equipment, wherein the channel number is 64 channels of single ends/32 channels of double ends, the output range is 0V-5.2V, and the precision is +/-2.5 mV.
The 1553B bus test board can be set to be in an MT mode, and A B buses are divided into two paths.
The instruction sending and detecting test board card is output to the tested equipment through a computer control instruction, the output is 32-path OC instructions, the instruction amplitude is greater than 28V, and the driving current is greater than 200 mA;
and identifying whether the command amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements, and the precision is +/-1 ms.
In the embodiment, the power supply module has power conversion functions of providing power for the inside of the tested device and power on/off functions of providing power for the tested device, and comprises a power supply circuit, a power conversion circuit and a control circuit;
the power supply conversion circuit consists of a filter and a power supply module;
and the secondary power supplies converted by the plurality of DC/DC modules on the power supply module are directly connected. The power module composition block diagram is shown in fig. 2.
The general off-line detection device is a direct user of the primary bus of the aircraft, and the internal grounding needs to meet the grounding specification of the aircraft. It is necessary to ensure complete isolation from the enclosure once and twice. The secondary power supply ground after the conversion of a plurality of DC/DC modules on the power supply module is directly connected, and each module in the device adopts the secondary power supply ground and is isolated from the primary ground and the shell ground. The grounding relationship is as shown in fig. 3.
In this embodiment, the general offline detection device for a spacecraft according to the present invention further includes offline detection control software that is provided in the computer system and is adapted to test tasks of different ORUs according to user configuration; the off-line detection interface software is operated in the off-line detection main control board and is used for realizing the configuration and management of the off-line detection device hardware interface;
the off-line detection control software is communicated with the off-line detection interface software, and data and detection results are displayed to the astronaut;
and the offline detection interface software receives the instruction information of the offline detection control software, sends excitation data to the test board card, drives the corresponding test board card to complete the function detection of the hundred-mega Ethernet port, the gigabit Ethernet port, 1553B communication, OC door instruction sending and receiving, analog quantity acquisition and the like, and transmits the detected information to the control software to complete the feedback of the test result.
In the invention, considering the rapid development of civil test technology, the test board card mostly adopts advanced technology, and is often smaller in weight and volume, lower in price and sufficient in test, so that the test board card can select commercial mature goods shelf products according to the requirements of tested equipment.
Fig. 4 is a schematic diagram showing the connection relationship of the general off-line detection device for the spacecraft according to the present invention.
Fig. 5 schematically shows an on-orbit off-line detection working sequence diagram of the space station of the general off-line detection device for the spacecraft according to the invention.
Fig. 6 schematically shows a principle view of an off-line inspection apparatus according to the present invention.
According to the arrangement of the invention, the further inspection, positioning and inspection of the failure reason of the existing on-orbit failure equipment of the spacecraft are realized, and the condition of function recovery after maintenance is checked, and the information interface test and verification before the on-orbit maintenance spare part system is completed.
The invention introduces a mature civil test board card into the aerospace product design, improves the system development capability and the production efficiency, reduces the development cost and shortens the development period.
The invention can realize the fault reason of the fault equipment on the spacecraft in the on-orbit mode, further check, position and check the function recovery condition after maintenance, and complete the test and verification of the information interface before the on-orbit maintenance spare part system is installed.
The foregoing is merely exemplary of particular aspects of the present invention and devices and structures not specifically described herein are understood to be those of ordinary skill in the art and are intended to be implemented in such conventional ways.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A general off-line detection device for a spacecraft is characterized by comprising:
the power supply module is used for being connected with a power supply and distribution system of the spacecraft to supply power to the whole on-orbit off-line detection unit and the detected equipment;
the CPCI bus back board realizes the functions of plugging, data transmission and synchronous triggering of each module of the on-track off-line detection unit;
the off-line detection main control board is used for coordinating and scheduling each module and the test board card in the whole off-line detection, and realizing data exchange and control between each module and the test board card;
the analog quantity output and acquisition test board card is used for testing the AD function of the tested equipment and acquiring the analog quantity of the tested equipment;
the 1553B bus test board card is in 1553B bus communication with the tested equipment and can simulate BC and RT functions;
the instruction sending and detecting test board card outputs the instruction to the tested equipment through the computer control instruction, and identifies whether the instruction amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements or not.
2. The universal offline inspection device for spacecraft of claim 1, wherein said power supply module has power supply interface protection function, which is 100V to ± 12V and 5VDC/DC module.
3. The universal offline inspection apparatus for spacecraft of claim 1, wherein said CPCI bus backplane provides node definitions for ± 12V and 5V power.
4. The universal offline detection device for the spacecraft of claim 1, wherein the analog output and acquisition test board card tests the AD function of the tested device, sets corresponding analog, and has 32 paths, an output range of 0V-5.2V, and a precision of ± 2.5 mV;
and (3) collecting analog quantity of the tested equipment, wherein the channel number is 64 channels of single ends/32 channels of double ends, the output range is 0V-5.2V, and the precision is +/-2.5 mV.
5. The universal offline detection device for spacecraft of claim 1, wherein said 1553B bus test board can be set to MT mode, A B two-way bus.
6. The universal offline detection device for the spacecraft of claim 1, wherein the instruction sending and detecting test board is output to the tested device through a computer control instruction, the output is a 32-channel OC instruction, the instruction amplitude is greater than 28V, and the driving current is greater than 200 mA;
and identifying whether the command amplitude, the pulse width and the driving capability sent by the tested equipment meet the requirements, and the precision is +/-1 ms.
7. The universal offline detection device for the spacecraft of claim 1, wherein the power supply module is used for providing power supply conversion for the interior of the tested device and power supply and power off functions for the tested device, and comprises a power supply circuit, a power supply conversion circuit and a control circuit;
the power supply conversion circuit consists of a filter and a power supply module;
and the secondary power supplies converted by the plurality of DC/DC modules on the power supply module are directly connected.
8. The universal offline inspection apparatus for spacecraft of claim 1, further comprising offline inspection control software disposed in the computer system for adapting to test tasks of different ORUs according to user configuration; the off-line detection interface software is operated in the off-line detection main control board and is used for realizing the configuration and management of the off-line detection device hardware interface;
the off-line detection control software is communicated with the off-line detection interface software, and data and detection results are displayed to the astronaut;
the off-line detection interface software receives the off-line detection control software instruction information, sends excitation data to the test board card, drives the corresponding test board card to complete the hundred-mega Ethernet port, the gigabit Ethernet port, 1553B communication, OC door instruction sending and receiving and analog quantity acquisition function detection, and transmits the detected information to the control software to complete the test result feedback.
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| CN112015166A (en) * | 2020-08-31 | 2020-12-01 | 湖北航天技术研究院总体设计所 | Portable survey and control equipment suitable for spacecraft |
| CN113485288B (en) * | 2021-06-23 | 2022-12-13 | 成都飞机工业（集团）有限责任公司 | Airborne system distributed in-situ test equipment and test method |
| CN113740783B (en) * | 2021-08-18 | 2024-02-09 | 上海卫星工程研究所 | Testing system for wired measurement and control interface of deep space exploration circulator against land device |
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