Applied Mechanics and Materials Vols. 568-570

Abstract: With development of the Missile technology, there are more and more challenges for the technology of early-warning satellite detection. The early-warning satellite can compute the data of launch point and impact point of a missile by detecting the changing infrared radiation of the missile. Therefore, the research on the infrared radiation of ballistic missile in boost phase is important for developing the detecting technology of early-warning satellite. In this paper, the dynamical infrared radiation model has been constructed based on the characteristics of trajectory and infrared radiation of a ballistic missile in boost phase, and the model has been verified by simulation based on the data of a two stage ballistic missile.

Abstract: The direction and positioning of the missile could be affected by the vertical deflection which is at the launch point, so the impact point errors will increase. Based on the launch coordination, the target point position deviation formula which is caused by vertical deflection is deduced in this paper. The correction precise of the vertical deflection is also a factor of the impact point error. The simulation based on the deviation formula is conducted to analyze the affection of the vertical deflection and the correction precise of the vertical deflection. And the results show that the vertical deflection can lead to 1km error for the long range missile. In addition, if the precision of vertical deflection were improved , the impact point errors will be reduced 85m.

Abstract: An improved distributed controller for underwater profile monitoring vehicle is investigated. A chattering-free tracking control law based on chattering-free trajectory-tracking control method is proposed to make a automation control of the vehicle and a manual/auto swtiched distributed controller on Underwater Profile Monitoring Vehicle is desinged. We give the designing procedure of hardware and software of the controller.

Abstract: Giant magnetostrictive actuator (GMA) is a new type of vibration control driving device. Since it has a lot of nonlinear, its performance model has been can't descrip good. This paper describes the self-made physical design of GMA, develop the GMA performance research experiment. For different excitation voltage, GMA was studied respectively the dynamic response with or without the bias magnetic field. And according to the application of GMA,verified under the condition of have a bias current, the accuracy of the magnetic coupling force curve of the GMA. According to the results of the validation, its curve can better describe the dynamic performance of giant magnetostrictive actuator.

Abstract: The system designs wireless remote control airplane model, operatie the keys of the remote controller, after the model aircraft receiving the instruction, and handle through the ARM, control the aircraft forward or backward. While the aircraft are working turn left and turn right and straight line, the system makes a judgment on the ultrasonic feedback information, and then control the aircraft’s direction of movement, and display the corresponding information on LCD. after several debugging and operating, System can work stable and reliable. This model can be widely used in the industry and agriculture and daily life, The model can be used in remote wireless detect, and market prospects.

Abstract: There are two options for the state estimation procedure by the integration filter for the integrated SINS/GPS, namely: direct navigation mode and indirect navigation mode. Determining which one of the two navigation modes will be more celebrated than the other under different conditions is an important but so far less seriously treated issue. The two navigation modes were systematically studied in terms of the system model, filtering algorithm and application issues. The car-mounted experiments were carried out to compare two navigation modes under different road conditions. The results show that direct navigation mode performs indirect navigation mode in terms of accuracy and stability. However, indirect navigation mode has low calculation burden and simple filter design.

Abstract: Aiming at the problem of initial attitude determination of aerial platform, a low computational attitude fusion algorithm is proposed based on MIMU. Attitude kinematic equations described by quaternions are developed and the filter structure used in this paper is designed. Real fly test results show that: at different initial deviation, the alignment precision of roll and pitch angles are within 1 °, attitude errors converge to 5 °or less within 12s, which meets the requirements of the aerial platform attitude fast self-determination. The filter algorithm has a small amount of calculation and is easy to be realized.

Abstract: This paper describes an integrated MEMS IMU and GNSS system for vehicles. The GNSS system is developed to accurately estimate the vehicle azimuth, and the integrated GNSS/IMU provides attitude, position and velocity. This research is aimed at producing a low-cost integrated navigation system for vehicles. Thus, an inexpensive solid-state MEMS IMU is used to smooth the noise and to provide a high bandwidth response. The integration system with uncertain dynamics modeling and uncertain measurement noise is also studied. An interval adaptive Kalman filter is developed for such an uncertain integrated system, since the standard extended Kalman filter (SKF) is no longer applicable, and a method of adaptive factor construction with uncertain parameter is proposed for the nonlinear integrated GNSS/IMU system. The results from the actual GNSS/IMU integrated system indicate that the filtering method proposed is effective.

Abstract: The constraints of weight, volume and power for Small unmanned air vehicle (UAV) restrict the application of sensors with heavy and good performance and powerful processors. This paper presents a real-time solution of autonomous flight navigation and its results for small UAV by applying small, cheap, low precision and low-power integrated navigation system, which includes Strap-down Inertial Navigation System (SINS) based on Micro-electro-mechanical system (MEMS) inertial sensors, Global Positioning System (GPS) receiver and magnetometer. The Square-Root Unscented Kalman filter (SR-UKF) for data fusion using in this MEMS-SINS/GPS/ magnetometer integrated navigation system provides continuous and reliable navigation results for the loops of guidance and control for the small UAV with autonomous flight. The whole integrated navigation system algorithm is implemented within low-power embedded microprocessors. The real-time flight test results show that the MEMS-SINS/GPS/magnetometer integrated navigation system is effective and accurate.

Abstract: In this paper, according to the theory of differential orbit improvement, the dynamics equations are deduced for the data of different types, and the weight method is introduced to fuse the multi-source data with different precision and form according to the RMS of condition function associated to different data. The results of simulations and real data processing show that the high precise measure data of different orbit measurement have been brought into full play, and the orbit determination precision is improved obviously.