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This article presents a method for testing and identification of a recovery material of certain missile, systematically analyzes the diagnostic approach and technology of PCB faults, expounds in detail design concept of the system, sets forth the solution using C8051F020 chip as microprocessor and testing of analog and digital I/O with built-in converter, contrives polarity discrimination circuit, provides software design process and main program by means of design thinking of modularized software, which help increasing program reliability and lowering development cost. The experimentation proves that this system is able to precisely position the faulty module of PCB to be identified, as well as make correct and reasonable opinion for maintenance. The design method and concept of this article is of significant value for reference in the research and development of similar testing and identification system.

One method for diagnosis of faults with generator rotor is contrived by combining local wave method and blind source separation. Time-frequency image varies with local wave of different fault signals, and this feature is applied to identify different faults. In order to realize automatic classification of faults, blind source separation is employed for separation of independent components in time-frequency image of local wave of different fault signals, so as to derive projection coefficients for a set of source images. On the basis of this, automatic classification of faults is realized with probability nerve network. Taking fault signal of rotor as an example, this method is investigated, and the validity is proved by experimental results.

Research and development of fault diagnosis system in application of integrated neural network information fusion is based on information fusion technology, with which preliminary analysis of equipment fault is made in different perspectives in terms of neural network, so as to identify the fault on the basis of fusion outcome. This technique is applied in fault diagnosis of one type of missile launching control unit, leading to sufficient use of various information and substantially increased fault diagnosis rate.

In order to link missile of actuating mechanism to CAN bus, an interface between actuating mechanism and CAN bus has been designed. It provides a method for the designing and realization of the hardware and software of interface. This interface has been used in reality. It proves that this design is feasible.

The traditional LPT-based image mosaic algorithm has such problems as huge calculation load and narrow applied fields, etc. In view of that, this paper puts forward a mosaic algorithm based on SUSAN Corner Detection Algorithm and LPT, which will firstly make corner detection, and then, with the corner as the coordinate transform central point, choose proper search strategy to further reduce the calculation load. The result of experimentation shows that this algorithm is effective.

To improve the efficiency and precision of missile servo mechanism testing, as the research object, a certain missile servo mechanism was studied in this paper. Based on PC/104 bus and virtual instrument technique, a missile servo mechanism automatic test system was presented, and the design and development on hardware and software of the system was described in detail. The system, which is featured with its simple operation, high precision, high reliability, scalable and portable test software, has been proved to be feasible by the test result.

According to principles of aero-engine fault diagnosis and flight data,this paper introduces a fault diagnosis method based on reformative ART1 neural network.After data pretreatment,it uses four-circumscription and quadratic-estimation to build fault codes and eliminate inveracious fault,and also ameliorate input layer of ART1 network.So this network can diagnoses not only gusty fault,but also gradual fault.It is proved that this method has high precision,strong restrain against noises,and low rate of inveracious alarms. Foreword With in-depth development in comprehensive integrated control of flight-propeller system for modern airplane, especially battle plane, flight data play a bigger role than ever. By availing and making full use of information on operating condition of airplane reflected by flight data, potential airplane fault can be discovered and removed in early stage with favorable safety reliability and redundancy for longer lifecycle of airplane and aero-engine on board. However, due to impact from external foul flight environment, aging of relevant sensors, as well as causes such as random noise interference in fight data recording system and etc, certain error exists with flight data. To deal with it, a set of fault code extracting method is designed herein, and modified ART1 neural network is applied for fault diagnosis. ART1 neural network is highly effective for pinpoint and real-time diagnosis of accidental fault with aero-engine, together with foresighted forecast function for progressive fault.

The present paper reports the high resolution transient Raman laser testing technology under two-stage light gas-gun loading experiment, and its application to studying the Raman spectroscopy of shocked benzene. In the experiments, the frequency shift of C-C stretching vibration (992 cm(-1)) and C-H stretching vibration peak (3 061 cm(-1)) in the low pressure section (less than 8 GPa) varies linearly with the pressure, and the results agree well with reported data in the literature. The structural changes in liquid benzene about 13 GPa were clarified firstly by the Raman spectral technique; the experimental results show that at a pressure of 9.7 GPa, the structural change of liquid benzene has taken place, not reported in the literature about 13 GPa. But the composition in the production is not clear. The measurement system provides an effective means to study the microstructure changes of transparent and translucent material under dynamic loading experiment.

Driving a copper projectile to impact a cryo-target made of aluminous alloy at the speed of 2.21 km x s(-1) with a two stage light gas gun, a proper one dimensional shockwave with a speed of 18.76 km x s(-1) was generated and directly acted on a uniform liquid in target, which was condensed by proportional gaseous carbon monoxide and nitrogen. At the measurement of Hugoniots, the full linear spectrum entirely dissociated with the plasma under the shock pressure of 33.5 GPa was caught by the use of intensified charge coupled device and accurate spectrographic technology. From the analysis of the spectrum, the authors know that the transient spectrograph with six channels can be used to measure and record the course of shock compression-irradiancy reliably, and the emitted spectral lines of shock compressed products indicated that the thermal dissociation and phase transition had occurred in homogeneous liquid of CO-N2. Furthermore, comparing the spectral intensity of lower central wavelength with that of higher, the fact of stronger intensity of 488 nm also validates that changes from "optic thin" to "optic thick" exist indeed in dense hydrocarbon liquid acted on by shock pressure.