CN106774283A - A kind of general failure simulation device of satellite control system - Google Patents
A kind of general failure simulation device of satellite control system Download PDFInfo
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- CN106774283A CN106774283A CN201710071419.XA CN201710071419A CN106774283A CN 106774283 A CN106774283 A CN 106774283A CN 201710071419 A CN201710071419 A CN 201710071419A CN 106774283 A CN106774283 A CN 106774283A
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- connector
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- connection
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- simulation device
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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
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Test And Diagnosis Of Digital Computers (AREA)
Abstract
The invention provides the failure simulation device that a kind of satellite control system is general, by adding the device between spaceborne computer and spaceborne actual products and product bug simulator, a connection among spaceborne computer end will be connected and spaceborne actual products end or connection product bug simulator end is connected, so as to select spaceborne computer is carried out data interaction with product on star or fault simulation equipment, to meet satellite control system experiment needs, or fault diagnostic test is carried out using product bug simulator.The present invention can realize the free switching of data interaction between spaceborne computer and actual products or fault simulator, and highly versatile.
Description
Technical field
The present invention relates to a kind of failure simulation device, and in particular to a kind of Design of State of utilization spaceborne computer it is general
The good failure simulation device of property.
Background technology
Satellite control system, for the requirement that the long-life is highly reliable, has carried out fault countermeasure and failure in development process
Diagnosis and reconfiguration scheme design；And product bug simulator is devised, for the design of fault diagnostic test proof scheme, and sentence
Correctness and reasonability that disconnected software is realized, so that the problem that thoroughly exposure On-board software is hidden in the hiding, to improve the reliability of system.
However, existing failure simulation device and method have certain limitation：
A) during system test, spaceborne computer can only connect actual products or can only connect product bug simulator, it is impossible to intersect
Coupling part actual products and partial fault simulator；
B) original method needs supporting two sets of cables for setting connection actual products and connecting fault simulator；
C) switch when, it is necessary to system all power-off after carry out, do not possess between actual products and fault simulator without seaming and cutting
Change；
D) test efficiency is low, poor universality, and each model is both needed to develop the standby annex that this model needs.
The content of the invention
Satellite control system is met it is an object of the invention to provide a kind of general failure simulation device of satellite control system
In system experiment and fault diagnostic test, the free switching demand between actual products and fault simulator.
In order to achieve the above object, the technical scheme is that providing a kind of satellite control system general fault simulation
Device, the fault diagnosis simulator includes switching part, and the switching part has three below port：
First port is connection spaceborne computer end, and it is connected with the first connector；First connector and spaceborne computer
Connector be attached；
Second port is the spaceborne actual products end of connection, and it is connected with the second connector；Second connector is true with spaceborne
The connector connection of product；
3rd port is connection product bug simulator end, and it is connected with the 3rd connector；3rd connector and product event
Hinder the connector connection of simulator；
Wherein, the first port is connected with second port, carries out spaceborne computer and spaceborne actual products under system test
Data interaction；
Or, the first port is connected with the 3rd port, carries out the lower spaceborne computer of system fault diagnosis experiment and product event
Hinder the data interaction of simulator.
Preferably, when system test is more long than the joint test cycle of fault diagnostic test, the original state of switching part is
First port is set to be connected with second port；
When fault diagnostic test is more long than the joint test cycle of system test, the original state of switching part be make first port with
3rd port is connected.
Preferably, first connector, the second connector, the 3rd connector, at three of the failure simulation device
Different surfaces export respectively.
Preferably, first connector, the second connector, the model of the 3rd connector, connect with spaceborne computer
The model of plug-in unit is consistent.
Preferably, between the second connector of the failure simulation device and the connector of spaceborne actual products, by
One cable connection；
Between 3rd connector and the connector of product bug simulator of the failure simulation device, connected by the second cable
Connect.
Failure simulation device of the invention, compared with prior art, its advantage and effect are：
1st, the free switching of data interaction between spaceborne computer and actual products or fault simulator is realized, i.e., part is true
Real product and other products are fault simulator, simple to operate, efficiency high.
2nd, existing two sets of cables are made full use of, it is to avoid existing cable is scrapped or gone into operation again, possesses certain economy
Benefit.
3rd, possess certain versatility, in the case of spaceborne computer state consistency, can be borrowed mutually between each model；
4th, possesses certain security.
Brief description of the drawings
Below with reference to drawings and Examples, the present invention is further illustrated.
Fig. 1 is schematic diagram of the present invention under satellite control system experiment.
Fig. 2 is schematic diagram of the present invention under satellite control system fault diagnostic test.
Specific embodiment
The general fault diagnosis simulator of satellite control system, including the design to its following aspect：
First, the determination of spaceborne computer default conditions
According to satellite control system testing program, Compare System tests the length with the fault diagnostic test cycle, determines spaceborne meter
Calculation machine default conditions are joint test cycle experiment long among both.
2nd, the changing method design of failure simulation device：
According to the demand that satellite control system is tested, number between spaceborne computer and actual products or product bug simulator need to be realized
According to interactive handoff functionality, the spaceborne computer that the original state of concurrent fault simulation device can be taken into account described in above-mentioned Section 1 is write from memory
Recognize state.
3rd, failure simulation device connector design
Based on the determination of spaceborne computer connector state, the design of device connector must consider the following aspects：
A) whetheing there is the device does not influence the development of system test；
B) in the case of spaceborne computer state consistency, there is generally applicable property between model；
C) connector mark is identical with corresponding spaceborne computer mark.
4th, failure simulation device connector Anti-misplug design
The device connector is relatively more, and Anti-misplug considers the following aspects when designing：
A) connector is divided into three major types：Connection spaceborne computer end, the spaceborne actual products end of connection, connection product bug simulation
Device end；
B) three faces can arrange connector, be put on one face per class connector；
C) on the basis of Section 3 design, the face mark where increase makes a distinction each connector mark.
Coordinate and tool is set in the fault diagnosis simulator of the present invention of above-mentioned four referring to shown in Fig. 1, Fig. 2, meeting
There are three switching parts of port, first port 1 is connection spaceborne computer end；The connector J2 being connected with the first port 1,
Further the connector J1 with spaceborne computer is attached.Second port 2 is the spaceborne actual products end of connection；With second end
The connector J3 of the connection of mouth 2, are further connected with the connector J5 of spaceborne actual products.3rd port 3 is connection product bug
Simulator end；The connector J4 being connected with the 3rd port 3, is further connected with the connector J6 of product bug simulator.
As shown in figure 1, the first port 1 of switching part is connected with second port 2, realize that spaceborne computer is true with spaceborne
The data interaction of product, for carrying out system test.As shown in Fig. 2 the first port 1 of switching part is connected with the 3rd port 3,
The data interaction of spaceborne computer and product bug simulator is realized, for carrying out system fault diagnosis experiment.
According to the comparison of foregoing Section 1, if the joint test cycle of system test is longer, switching part it is initial
State is first port 1 is connected with second port 2；If the joint test cycle of fault diagnostic test is longer, switching part
The original state of part is first port 1 is connected with the 3rd port 3.
Connector J2, J3, J4 of the failure simulation device, by different three from the failure simulation device of connecting object
Surface exports；The model of connector J2, J3, J4 simultaneously, the model with the connector J1 of spaceborne computer is consistent.
Wherein, original two sets of electricity for being used for that spaceborne computer is connected spaceborne actual products, product bug simulator respectively
Cable, can be used to the connector J3 of difference connecting fault analogue means and the connector of spaceborne actual products in the present invention
J5, and connector J4 and the product bug simulator of connecting fault analogue means connector J6.
In sum, the present invention is effectively simplified data interaction between spaceborne computer and actual products or fault simulator
Free switching process, simple to operate, high working efficiency, highly versatile, security is good.
Although present disclosure is discussed in detail by above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read the above, for of the invention
Various modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (5)
1. the general failure simulation device of a kind of satellite control system, it is characterised in that
The fault diagnosis simulator includes switching part, and the switching part has three below port：
First port（1）It is connection spaceborne computer end, itself and the first connector（J2）Connection；First connector（J2）With
The connector of spaceborne computer（J1）It is attached；
Second port（2）It is the spaceborne actual products end of connection, itself and the second connector（J3）Connection；Second connector（J3）
With the connector of spaceborne actual products（J5）Connection；
3rd port（3）It is connection product bug simulator end, itself and the 3rd connector（J4）Connection；3rd connector
（J4）With the connector of product bug simulator（J6）Connection；
Wherein, the first port（1）With second port（2）Connection, the spaceborne computer carried out under system test is true with spaceborne
The data interaction of real product；
Or, the first port（1）With the 3rd port（3）Connection, carry out the lower spaceborne computer of system fault diagnosis experiment with
The data interaction of product bug simulator.
2. failure simulation device as claimed in claim 1, it is characterised in that
When system test is more long than the joint test cycle of fault diagnostic test, the original state of switching part is to make first port
（1）With second port（2）Connect；
When fault diagnostic test is more long than the joint test cycle of system test, the original state of switching part is to make first port
（1）With the 3rd port（3）Connect.
3. failure simulation device as claimed in claim 1, it is characterised in that
First connector（J2）, the second connector（J3）, the 3rd connector（J4）, at three of the failure simulation device
Different surfaces export respectively.
4. the failure simulation device as described in claim 1 or 3, it is characterised in that
First connector（J2）, the second connector（J3）, the 3rd connector（J4）Model, connect with spaceborne computer
Plug-in unit（J1）Model it is consistent.
5. failure simulation device as claimed in claim 4, it is characterised in that
Second connector of the failure simulation device（J3）With the connector of spaceborne actual products（J5）Between, by the first electricity
Cable is connected；
3rd connector of the failure simulation device（J4）With the connector of product bug simulator（J6）Between, by second
Cable connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710071419.XA CN106774283A (en) | 2017-02-09 | 2017-02-09 | A kind of general failure simulation device of satellite control system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710071419.XA CN106774283A (en) | 2017-02-09 | 2017-02-09 | A kind of general failure simulation device of satellite control system |
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| CN106774283A true CN106774283A (en) | 2017-05-31 |
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| CN201710071419.XA Pending CN106774283A (en) | 2017-02-09 | 2017-02-09 | A kind of general failure simulation device of satellite control system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110850842A (en) * | 2019-11-05 | 2020-02-28 | 上海航天控制技术研究所 | Satellite full-function single-machine simulation system and method based on hardware-in-the-loop |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101968652A (en) * | 2010-07-21 | 2011-02-09 | 中国航天科技集团公司第九研究院第七七一研究所 | Detection device and method for microcontroller system device |
| CN103970032A (en) * | 2014-05-16 | 2014-08-06 | 中国人民解放军装备学院 | Satellite platform and mechanical arm cooperation simulator |
| CN106155041A (en) * | 2016-06-20 | 2016-11-23 | 北京控制工程研究所 | A kind of reconstruction test equipment adaptive device and method of testing |
-
2017
- 2017-02-09 CN CN201710071419.XA patent/CN106774283A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101968652A (en) * | 2010-07-21 | 2011-02-09 | 中国航天科技集团公司第九研究院第七七一研究所 | Detection device and method for microcontroller system device |
| CN103970032A (en) * | 2014-05-16 | 2014-08-06 | 中国人民解放军装备学院 | Satellite platform and mechanical arm cooperation simulator |
| CN106155041A (en) * | 2016-06-20 | 2016-11-23 | 北京控制工程研究所 | A kind of reconstruction test equipment adaptive device and method of testing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110850842A (en) * | 2019-11-05 | 2020-02-28 | 上海航天控制技术研究所 | Satellite full-function single-machine simulation system and method based on hardware-in-the-loop |
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