Abstract：Aiming at the problem of maneuvering target tracking in the ocean, a monitoring strategy of maneuvering target searching and tracking is proposed via the adjustment of satellite phase reconstruction. The behavior prediction model of maneuvering target in geographic coordinate system and the method of satellite phase modulation based on Hohmann transfer are constructed. And NSGAII algorithm is designed to solve the model. The detection probabilities of the maneuvering target before and after satellite reconfiguration are compared and analyzed. Simulation results show that satellite reconfiguration networking within a certain range can effectively improve the probability of finding maneuvering targets, and the study can provide method support for searching and tracking maneuvering targets.  

Abstract：Aiming at the characteristics of Lunar exploration mission, to enhance the safety during reentry process and avoid adverse weather conditions which may appear on the main landing site, an impulse maneuver strategy in trajectory is put forward and optimized, which particularly aims at some emergency situations happening in prime landing site after transearth injection and having to land in backup landing site. Firstly, a practicable iteration method is proposed, which takes perturbation into account in solving Lambert problem. Subsequently, combining with Primer Vector and Simulated Annealing method, an interactive optimization is proposed, and the optimal energy consuming is 0.025 2 km/s, which is able to meet the constraints of engineering.  

Abstract：The rudder system is an important part of the control of the attitude during the maneuvering of the supersonic reentry vehicle, and the flutter characteristic analysis is the key link to ensure the successful development of the model and the flight test. In this paper, the flutter vibration characteristics of the rudder surface are analyzed by using the local piston flow theory. Firstly, the dynamic equation of the rudder system is established to determine the critical boundary calculation method of rudder surface flutter. Then, the finite element method (FEM) and modal test is used to determine the modal parameters of the rudder surface under different combination conditions of different rudder angel and different loading level. Finally, the critical parameters of rudder surface flutter are determined by flutter analysis, which provides technical support for the design and optimization of rudder system structure.  

Abstract：For attitude keeping control with momentum exchange device system during orbit control stage, the momentum management problem is investigated in the case of the large disturbance resulting from orbit jets. Characteristic of disturbance accumulated momentum is analyzed in detail based on the orbital motion features of the Earthorienting spacecraft, and then a momentum management method is proposed, which includes establishment of biased momentum and determination of symmetrical distributed orbit control positions to selfcounteract the accumulated momentum. With the method utilization, the efficiency of orbit control can be achieved to the maximum degree and meanwhile the momentum saturation phenomenon can be avoided. The proposed method for underactuated spacecraft attitude control, the effectiveness of the method is demonstrated by the numerical simulation results and the practical application.  

Abstract：The golden section controller based on fuzzy segmentation is an effective way to deal with the multiinput and multioutput higherorder nonlinear systems. It is an intelligent autonomous control, which combines the fuzzy control and golden section control. Based on characteristic model, the design process of the golden section controller based on fuzzy segmentation is given in detail, and the stability of the method is theoretically proved. Applying this method to the small satellite attitude control, simulation results show the effectiveness of the method.  

Abstract：Future spacecraft will have much autonomous work. And the utilization of embedded system continues growing with data increasing. In this paper, a nonlinear event triggered control approach is applied for the spacecraft attitude control. By this approach, the utilization of bus bandwidth decreases greatly and a good control performance is achieved. Moreover, the design procedure and stability proof of this algorithm are given via perturbation theorem. Finally, a numerical example is provided to illustrate the efficiency and feasibility of the proposed approach.  

Abstract：An parallelmodel adaptive estimation (PMAE) algorithm is presented for a timevarying system where  model uncertainty may occur occasionally. Generally, an algorithm which is designed for an uncertain system may yield suboptimal performance when the model uncertainty does not occur. To cope with this problem, we propose to use two filters in parallel in a multiplemodel framework. One of the filters, an augmented Kalman filter (AKF), provides estimates of uncertain parameters when the model uncertainties occur, whereas the second filter, a Kalman filter (KF), yields high precision in the absence of the uncertainties. A space surveillance example is given in simulation to show the potential application of the presented algorithm. It indicates that the PMAE is efficient to deal with model uncertainty.    

Abstract：In this paper, an advanced neighborhood preserving embedding method combined with exponentially weighted moving average (EWMADNPE) is proposed in incipient fault detection for satellite’s attitude control system (ACS).Considering the artificial set of neighborhood parameters in neighborhood preserving embedding (NPE) algorithm, the dynamic neighborhood selection is introduced, so that the weights reconstruction matrix can be selected according to the sample density of the manifold. On the basis of this, the EWMADNPE algorithm is used to establish the squared prediction error (SPE) statistic in fault detection (FD) by exponentially weighted moving average (EWMA). The case study on a simulated satellite ACS demonstrates the effectiveness and feasibility of the proposed method.    

Abstract：Considering the built Beidou satellite navigation system , constellation performance and reconfiguration methods of satellite navigation system with satellite failure are studied.The service performance of navigation constellation under different failure modes is analyzed;then the optimization model of navigation constellation reconstruction configuration and the optimization design method of navigation constellation reconstruction configuration based on genetic algorithm are established.Maneuver strategy and maneuver model of the satellite are studied during the reconstruction of constellation configuration; finally, a specific failure situation is simulated, the maneuver scheme of reconstruction under this failure condition is given.    

Abstract：In order to achieve the higher requirements and especially the stray light suppression capacity of optical imaging sensor for our future space automated rendezvous and docking task, a new generation cameratype rendezvous and docking sensor (CRDS) is developed. Compared with the CCDbased vision guidance sensor assembled on Shenzhou8, the measured range of CRDS is improved from 150 m~2 m to 250 m~0.9 m and the initial acquisition time for target is reduced to 0.32 s from 10 s. Besides, the stray light suppression capacity  significantly improved, which makes it be adaptive in nearly allweather conditions. CRDS  successfully tested and verified in automated rendezvous and docking tasks of SZ11 & TG2 and TZ1 & TG2. CRDS can be better applied for the rendezvous and docking mission in future China’s space station and lunar exploration project. The measurement principle, system composition, ground test and orbit performance of the product are introduced in detail in this paper, and corresponding conclusions are also revealed.    

Abstract：A method of projector calibration for 3D object measurement system is presented in this paper. In this method, the gray code patterns are projected on a series of scenes to be measured by the projector, shot and then decoded by two cameras meantime. Under the triangle criterion, 3D corner positions of these patterns are computed, using which the projector’s calibration parameters are resolved with the typical camera calibration method. As this process doesn’t rely on a specified calibration plane or target, the projector calibration can be finished during the measurements and the projector parameters can be further updated after the precalibration. The experiment results prove the validness of the method .  

Abstract：A particleincell method with Monte Carlo collision (PICMCC) model is established for the discharge process in pulsed plasma thruster (PPT). The ionization process in LES6 PPT is simulated, considering the ionization collisions. According to the coupling computation of particle movement, collisions and electromagnetic field, the curves of current and resistance are acquired, and the distributions of plasma during the discharge of PPT are presented. Two initial conditions with and without particles predistribution are applied respectively to the numerical computation, implying that the results in the case with the predistribution are closer to the experimental results. The results in the other case tend to be in accordance with the results in the ignition process. The methods and model explored in this work provide a certain reference for PIC simulations in PPT.  

Abstract：In order to meet the requirements of high reliability that is required by many embedded software in aerospace field, a method is designed to analyze and localize the software vulnerability automatically. Based on program slicing technique and improved forward computation algorithm of dynamic slicing, firstly this method collects the program dynamic information at runtime via using dynamic slicing; and then it constructs the program slice spectrum and calculates the likelihood of each slicing statement being vulnerable by some statistics; and last it reports the localization result of software vulnerability. After discovering the vulnerability in the software, this method can analyze and localize the root that causes this vulnerability. We develop a tool to test this method and the experiment proves its effectiveness.