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Spacecraft fault simulation control method and spacecraft fault simulation control device

A technology of fault simulation and control method, applied in the field of computer simulation, can solve the problems of validity dependence, difficulty in controlling efficiency and misoperation rate, inability to automatically implement simulation running state setting and fault state setting in a timely and accurate manner, and improve the general sexual effect

Inactive Publication Date: 2016-12-14
中国人民解放军63920部队
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] When the internal and external state environment changes, the fault simulation exercise system driven by static configuration cannot automatically implement the simulation operation state setting, fault state setting and various data sending and receiving settings in a timely and accurate manner, and can only be set through manual intervention.
The effectiveness of this method depends on the experience and training of the operator, and the efficiency and misoperation rate are difficult to control

Method used

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  • Spacecraft fault simulation control method and spacecraft fault simulation control device
  • Spacecraft fault simulation control method and spacecraft fault simulation control device
  • Spacecraft fault simulation control method and spacecraft fault simulation control device

Examples

Experimental program
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Effect test

Embodiment 1

[0038] figure 1 A flow chart showing a control method for spacecraft fault simulation provided by an embodiment of the present invention, as shown in figure 1 As shown, the method includes:

[0039] Step S1, pre-store script items, said script items include condition items, operation formulas that satisfy the conditions A condition collection for and a behavior collection consisting of behavior items.

[0040] In a possible implementation, the conditional operation formula is satisfied The condition set includes the state variable Maps as a function of conditional satisfaction status, which is either true or false.

[0041] Step S2, monitoring the state variable indicating that the state corresponding to the condition item changes

[0042] Step S3, when it is detected that the state changes, according to the state variable Compute the conditional formula

[0043] Step S4, according to the calculation result, determine whether to perform an action, the type of ...

Embodiment 2

[0047] figure 2 A flow chart showing a control method for spacecraft failure simulation provided by another embodiment of the present invention, such as figure 2 As shown, in a possible implementation, before step S4, it also includes: step S5, preset the correspondence between the type of action to be executed and the time and frequency of action execution, and step S4 specifically includes: according to the calculation result , to determine whether to execute an action, and determine the time and frequency of action execution according to the correspondence between the type of the execution action and the time and frequency of action execution.

example 1

[0048] Instance 1 takes execution failure 1 as an example to illustrate:

[0049] In step S1, a script item 1 is prestored, and the script item 1 defines state variables A1 and B1.

[0050] In step S2, the state variables A1 and B1 are monitored.

[0051] In step S3, a conditional operation expression F1(A1, B1) is calculated.

[0052] In step S4, when the conditional operation expression F1(A1, B1)>0 is satisfied, execute behavior S1;

[0053] In step S5, parameters such as the occurrence timing and object of S1 are preset, and in step S4 an instruction is sent to execute S1.

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Abstract

The invention relates to a spacecraft fault simulation control method and a spacecraft fault simulation control device. The spacecraft fault simulation control method includes: prestoring a script item including a condition item, a condition set satisfying a condition operation formula (as shown in the description) and a behavior set consisting of behavior items; monitoring a state variable (as shown in the description) representing change of a state; when change of the state is monitored, calculating the condition operation formula (as shown in the description) according to the state variable (as shown in the description); deciding whether to execute an action according to a calculation result, determining time and frequency of the action to be executed according to the type of the action to be executed, and sending an action instruction. The spacecraft fault simulation control method and the spacecraft fault simulation control device are capable of monitoring the state of an embedded system according to high real-time performance and complicated interactivity of spaceflight test control, subjecting multi-state branch points of a simulation system to complex calculation by satisfying a calculation method based on mathematical logic conditions and achieving precise control of multipoint and multiple fault behaviors by being supportive to precise situation study and judgment and have the capability of complex spacecraft fault behavior simulation.

Description

technical field [0001] The invention relates to the technical field of computer simulation, in particular to a control method and device for spacecraft failure simulation. Background technique [0002] The commonly used failure simulation mode is stored and managed in a database, and the simulation system is driven by static configuration to perform failure mode drills. [0003] When the internal and external state environment changes, the fault simulation exercise system based on static configuration cannot automatically implement the simulation operation state setting, fault state setting and various data sending and receiving settings in a timely and accurate manner, and can only be set through manual intervention. The effectiveness of this method depends on the experience and training of the operator, and the efficiency and misuse rate are difficult to control. Contents of the invention [0004] technical problem [0005] In view of this, the technical problem to be...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20G06F2111/10
Inventor 苗毅詹磊王磊杨健周倜周立孙军申敬松鲁阳黄钊铁伟涛
Owner 中国人民解放军63920部队
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