QQ客服 官方微博 反馈留言

浏览/检索结果: 共9条，第1-9条 帮助 限定条件 专题：长春光学精密机械与物理研究所    第一署名单位    第一作者单位    通讯作者单位     已选(0)清除 条数/页：5101520253035404550556065707580859095100   排序方式：请选择作者升序作者降序题名升序题名降序发表日期升序发表日期降序提交时间升序提交时间降序 Study on loss of performance in inertial sensors due to electrode asymmetry 期刊论文 Chinese Optics, 2019, 卷号: 12, 期号: 3, 页码: 455-462 作者:  S.-X.Wang;  K.-Q.Qi;  Y.-K.Wang;  Z.Wang;  L.-H.Chen 收藏  |  浏览/下载：1/0  |  提交时间：2020/08/24 Inertial navigation systems,Earth (planet),Electrodes,Electrostatic force,Gravitation,Gravity waves   Random vibration analysis on the support of strapdown inertial navigation system (EI CONFERENCE) 会议论文 2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China Hao X.; Li M.; Jia H. 收藏  |  浏览/下载：17/0  |  提交时间：2013/03/25 Vibration of the support is an important factor to the accuracy of strapdown inertial navigation. To get vibration characteristics of the support  FEM model of the support was created with Ansys  and then response characteristics were analyzed on the support under the separated random loads during carrier flight  including the phases of subsonic and subsonic. To validate the analysis method  wide band random vibration test was done on the points of the support  which are used for mounting inertial instruments. The comparison of the analysis and the test data shows that the relative error of analysis result is not more than 13%. According to the two results the support structure was improved. Finally random vibration analysis was carried out on the improved one. The result shows that the acceleration response was largely reduced than before. This research can be a reference of performance improvement of the strapdown inertial support and navigation system precision. 2011 IEEE.   Structure optimization of strap-down inertial navigation system support (EI CONFERENCE) 会议论文 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China Sun H.; Jia H.; Wang J.; Hao X. 收藏  |  浏览/下载：20/0  |  提交时间：2013/03/25 In order to meet the requirement of inertial navigation components and minimizing the system's weight  and topological optimization was conducted. Then  topological optimization and size optimization were conducted under conditions of random vibration and impact. Firstly  according to the dynamic characteristics of missile and requirement of inertial navigation system  the structure of inertial navigation support was designed according to types of missile connection and space arrangement of electronic components  the method of transforming multi-loading cases to multi-loading constraints was used to optimizing the size of the support under conditions of random vibration and impact. Comparing to the original support structures  RMS accelerations in installed points reduced by 25.2% under random vibration  the weight of optimal structures reduced by 28.1%  the structures also met the requirement of inertial navigation system under condition of impact. The support structure shows improvements in both dynamic characteristic and light weight comparing with the original one. 2011 IEEE.   The ship-borne infrared searching and tracking system based on the inertial platform (EI CONFERENCE) 会议论文 International Symposium on Photoelectronic Detection and Imaging 2011: Advances in Infrared Imaging and Applications, May 24, 2011 - May 24, 2011, Beijing, China Li Y.; Zhang H. 收藏  |  浏览/下载：25/0  |  提交时间：2013/03/25 As a result of the radar system got interferenced or in the state of half silent  it can cause the guided precision drop badly In the modern electronic warfare  therefore it can lead to the equipment depended on electronic guidance cannot strike the incoming goals exactly. It will need to rely on optoelectronic devices to make up for its shortcomings  but when interference is in the process of radar leading  especially the electro-optical equipment is influenced by the roll  pitch and yaw rotation  it can affect the target appear outside of the field of optoelectronic devices for a long time  so the infrared optoelectronic equipment can not exert the superiority  and also it cannot get across weapon-control system "reverse bring" missile against incoming goals. So the conventional ship-borne infrared system unable to track the target of incoming quickly  the ability of optoelectronic rivalry declines heavily.Here we provide a brand new controlling algorithm for the semi-automatic searching and infrared tracking based on inertial navigation platform. Now it is applying well in our XX infrared optoelectronic searching and tracking system. The algorithm is mainly divided into two steps: The artificial mode turns into auto-searching when the deviation of guide exceeds the current scene under the course of leading for radar.When the threshold value of the image picked-up is satisfied by the contrast of the target in the searching scene  the speed computed by using the CA model Least Square Method feeds back to the speed loop. And then combine the infrared information to accomplish the closed-loop control of the infrared optoelectronic system tracking. The algorithm is verified via experiment. Target capturing distance is 22.3 kilometers on the great lead deviation by using the algorithm. But without using the algorithm the capturing distance declines 12 kilometers. The algorithm advances the ability of infrared optoelectronic rivalry and declines the target capturing time by using semi-automatic searching and reliable capturing-tracking  when the lead deviation of the radar is great. 2011 Copyright Society of Photo-Optical Instrumentation Engineers (SPIE).   Application of adaptive Kalman filter technique in initial alignment of strapdown inertial navigation system (EI CONFERENCE) 会议论文 29th Chinese Control Conference, CCC'10, July 29, 2010 - July 31, 2010, Beijing, China Huang C.; Su W.; Liu P.; Ma M. 收藏  |  浏览/下载：21/0  |  提交时间：2013/03/25 In order to improve the alignment precision and convergence speed of strap-down inertial navigation system  but in the active system most noise statistical characteristics are unknown  an initial alignment method based on Sage-Husa adaptive filter is presented. We also derived the exactitude alignment error model and adaptive Kalman filter equation in the azimuth of small misalignment angle. As usual  in this case  known the noise statistical characteristics  we introduce the adaptive Kalman filter. It uses the information of observed data  Kalman filter is suitable  on-line estimation noise statistical characteristics and state simultaneously in order to improve the filter continuously  so  the filter has a higher estimation accuracy than the conventional Kalman filter. By simulating verifying  the adaptive Kalman filter enhances the convergence speed and alignment accuracy effectively.   Optimal design of strap-down inertial navigation support under random loads (EI CONFERENCE) 会议论文 2010 IEEE International Conference on Information and Automation, ICIA 2010, June 20, 2010 - June 23, 2010, Harbin, Heilongjiang, China Hao X.; Li M.; Jia H.; Xuan M. 收藏  |  浏览/下载：22/0  |  提交时间：2013/03/25 In order to realize miniaturization and light weight of the strap-down inertial navigation system  and then to make sure that it works well under random loads  optimal design is applied to the strap-down inertial navigation support with the methods of topology optimization and size optimization. Firstly  based on the installation requirement of devices and connection requirement of the support and the carrier  the initial structure of the support is designed. Topology optimization with FEA software ANSYS is adopted on the initial structure to get the basic one. Then 5 critical sizes are chosen as design variables  and the support structure is optimized by means of size optimization to reach light weight with satisfying the requirement of dynamic stiffness. Finally  random vibration analysis is applied to the initial structure. In the mean time  random vibration test is carried out to qualify the analysis method. After the qualification  a random vibration analysis is applied to the optimized support structure to get the rms of displacement response and acceleration response of the support to validate whether the optimized structure is appropriate. The results indicate that the dynamic stiffness of the optimized support structure satisfies the design requirements  and its weight is lighter 49.38% than that of the initial one. This research can be a reference to the structure design of supports under random loads  and the result has been applied to the development and manufacture of a prototype aerocraft. 2010 IEEE.   Application of adaptive UKF in initial alignment of MINS/GPS integrated navigation system (EI CONFERENCE) 会议论文 2010 3rd International Conference on Advanced Computer Theory and Engineering, ICACTE 2010, August 20, 2010 - August 22, 2010, Chengdu, China Jiao W.-B.; Gao Q.; Su W.-X.; Wang M. 收藏  |  浏览/下载：27/0  |  提交时间：2013/03/25 In order to overcome the shortcomings of standard unscented Kalman filter (UKF)  which are obviously influenced by the error of initial value and the model error of system  adaptive UKF which is based on the adaptive principle is applied in initial alignment of the MINS/GPS integrated navigation system. Coarse alignment cannot be done by micro inertial measurement unit (MIMU) itself because of its low precision  the method of using magnetometer to assist it with coarse alignment is presented. Simulation results show that the adaptive UKF can overcome the influences of initial values error and inaccurate system model  and improve the convergence speed and alignment accuracy effectively. 2010 IEEE.   Aircraft orientation error correction based on image aided navigation paper (EI CONFERENCE) 会议论文 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010, August 24, 2010 - August 26, 2010, Changchun, China Tao Z.; Yang L.-M. 收藏  |  浏览/下载：12/0  |  提交时间：2013/03/25 In allusion to the character of aircraft orientation error in inertial navigation system increasing with its working time and error accumulation  airborne image aided navigation system is imported in inertial navigation system to combine integrated navigation system. To acquire high orientation accuracy and high matching speed a new algorithm based on multi-scale edge detection and generalized point theory is put forward. At first multi-scale edge detection algorithm is adopted to realize airborne image edge detection  then image matching algorithm is used based on generalized point theory is used to eliminate error accumulation of peg-top excursion and accelerometer error to correction aircraft aircraft pose error to increase navigation accuracy of aircraft. To prove the algorithm is effective and robust  simulative experiment is done. The simulative experiment indicated that aircraft orientation accuracy is better than inertial navigation system  and its orientation error is less than 15 meters after airborne image aided navigation correction. 2010 IEEE.   INS's error compensation on the base of the celestial theodolite (EI CONFERENCE) 会议论文 ICO20: Optical Devices and Instruments, August 21, 2005 - August 26, 2005, Changchun, China Zhao H.-B.; Guo L.-H. 收藏  |  浏览/下载：59/0  |  提交时间：2013/03/25 In recent years there has been a major upsurge of interest in the integrated inertial navigation system (INS)/celestial navigation system (CNS) as a cost-effective way of providing accurate and reliable navigation aid for civil and military vehicles (ships  aircrafts  land vehicles and so on). One of the disadvantages of INS is its errors will grow unbounded. The CNS can be used to improve position estimation resulting from INS measurement. This paper describes the design of this. An error model developed earlier is used for CNS/INS filter (Kalman filter) mechanization. In CNS  celestial theodolite acquires an image of the sky  recognize the most brilliant stars in the image  creates with them a "constellation"  and searches for this pattern in an on board star catalogue of the observed region to get the precise position and attitude information of vehicles. The Kalman filter method is used to fuse measurement from the system. We can use this information to compensate INS's error. The tests carry out with this system show that system will get accurate navigation information.