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Missile simulated launching testing device

A technology for simulating launch and testing devices, applied in the field of testing, can solve the problem that a single device cannot meet the unit testing and comprehensive missile testing at the same time, and has a single testing function, and achieves the effect of diverse testing functions.

Active Publication Date: 2020-03-20
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In view of this, the embodiment of the present invention provides a missile simulation launch test device, which at least solves the problems in the prior art that the test function is single, and a single device cannot simultaneously satisfy the unit test and missile comprehensive test functions.

Method used

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  • Missile simulated launching testing device
  • Missile simulated launching testing device
  • Missile simulated launching testing device

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Embodiment Construction

[0031] Preferred embodiments of the present invention will be described in more detail below. Although preferred embodiments of the present invention are described below, it should be understood that the present invention can be embodied in various forms and should not be limited by the embodiments set forth herein.

[0032] A missile simulation launch test device, comprising:

[0033] Control circuit, power supply circuit, steering gear differential PWM control drive circuit, steering gear differential position signal processing circuit, power on / off circuit, voltage acquisition circuit, current acquisition circuit, short circuit I / O detection circuit and serial port control circuit;

[0034] The control circuit is electrically connected with the steering gear differential PWM control drive circuit, the steering gear differential position signal processing circuit, the short-circuit ring I / O detection circuit and the serial port control circuit respectively,

[0035] The pow...

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Abstract

The embodiment of the invention discloses a missile simulated launching testing device. The system comprises a control circuit, a power supply circuit, a steering engine differential PWM control drivecircuit, a steering engine differential position signal processing circuit, a power-on / off circuit, a voltage collection circuit, a current collection circuit, a short circuit ring I / O detection circuit and a serial port control circuit, and the power-on / off circuit comprises a first power-on / off circuit and a second power-on / off circuit. A control circuit, a power supply circuit, a steering engine differential PWM control drive circuit, a steering engine differential position signal processing circuit, a power-on / off circuit, a voltage collection circuit, a current collection circuit, a short circuit ring I / O detection circuit and a serial port control circuit are arranged. A plurality of projects in the simulated missile launching process are subjected to simulation test, so that the test functions are diversified, single equipment can meet the unit test and missile comprehensive test functions at the same time, and the simulated missile launching control test function is achieved.

Description

technical field [0001] The invention belongs to the technical field of testing, and more specifically relates to a missile simulation launch testing device. Background technique [0002] Missile unit testing, comprehensive testing, and simulated launch control testing are important links in the development, production, and use of missiles. They are used to test and inspect various functions and main technologies before unit assembly, after missile assembly, and before missile installation and use. Indicators, adjust and replace the faulty unit or the whole under necessary and specific circumstances, so as to ensure that the performance indicators of each unit before assembly and the missile after assembly and production meet the requirements of various performance indicators in actual use. The current test equipment has the following disadvantages: the test function is single, and a single device cannot satisfy the functions of unit test and missile comprehensive test at the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B19/042F42B35/00
CPCF42B35/00G05B19/0423G05B2219/24215
Inventor 丛辉谢长静沙群郑飞李永吴志文
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS