In response to the requirements of lunar sampling and return mission， based on the development of our country’s launch vehicle and the technical foundation in the first and second phases of the lunar exploration project， a multi-planned and multi-round iterative trade-off analysis has been made on the overall plan of the detector， the composition of the functional modules， the launch method， the flight process， etc.， and the module composition， main flight process and “Chang’E-5” engineering design process of “Chang’E-5” detector have been gradually optimized and determined. The result fully proves that the scheme is in line with our country’s lunar exploration project development plan and aerospace technology development expectations， and thus is advanced and feasible. The NAFVO trade-off design method adopted in the design process can provide a useful reference for the design of complex and large-scale aerospace engineering schemes.

The mission trajectories of the Chang’E-5 are complicated with many constraints. Selecting a sampling area is largely determined by inseparable from the trajectory design. In this paper, the sampling area selection method based on the orbital geometry in the Chang’E-5 mission was first proposed and practiced. This method is constrained by principles of the most compact task schedule，the least fuel consumption，the most launch opportunities，and other requirements for sub-systems. First，the feasible sampling area range with the least of engineering implementation cost is calculated. And then the final sampling area range is determined by comprehensively considering the topographic safety and scientific value. Compared with the traditional method，this method considers the strong coupling between the location of the sampling area and the mission trajectory，which is unique to the lunar sampling return mission Besides，this method determines the location and range of the sampling area from the aspects of feasible engineering implementation and wide adaptability，thus ensuring the optimality and wide adaptability of the mission plan. Due to the launch vehicle，the established launch window has been postponed from 2017 to 2020. The designed sampling area range is updated to the new launch date，ensuring that the mission trajectory design remained unchanged. The design laid a solid foundation ensuring the complete success of the Chang’ E-5 Mission.

Limited by the loading capability of launch vehicle，the deep space probe is required to reduce its own weight. Based on the most advanced space power supply technology in China，the power supply and distribution system of Chang’e-5 orbiter adopts ultra-high energy density solar cells and batteries，and invents a new bus topology. Through a series of lightweight power distribution system design，the power to weight ratio of the whole probe reaches the domestic leading level. The power supply and distribution system of spacecraft has passed the ground verification and flight test on in orbit，therefore can be referred for the follow-up research and design of high specific energy of power supply and distribution system of spacecraft.

Facing to the high-safety and high-reliability mission requirement，the high-complexity and high-autonomy function requirement，and the high-real-time and strong-sequential performance requirement of mission Chang’E-5，this paper researches the high confidence develop technology of the application software for GNC Subsystem of Chang’E-5. During the requirement analysis，the sequential safety attribute is added to the formal modeling and verification language，which avoids the requirement duality. In phase of design and coding，program slicing is extracted based on the mission profile，which is used in the source code fault localization，comparing to the manual work，the normalization and correctness of source code is improved. The test case auto generate method base on state chart and sequence diagram is researched，and a Full-Automatic Spacecraft software Testing suite is established for the massive test case，the test coverage and efficiency is obviously improved.

Based on the unmanned lunar surface sampling return mission of Chang’E-5 drilling subsystem，the coring dynamics of spiral drill in shallow loose lunar regolith were studied by experimental method and FEM. Research results are described as follow： the WOB（Weight Of Bit），which is controlled by drilling parameters，is a key parameter in coring dynamics and can influence the effect of coring； The relationship of powder discharge pressure and core resistance is a key factor controlling the sampling effect of auger. Our results improves our understanding of drilling dynamics, therefore will help the designing drilling system for chang’e-6 and other future deep space explorer project.

The deep lunar soil loading process is complicated and volatile; it is difficult to achieve stable and reliable drilling sampling. In order to realize the rotary drive control of low-speed high torque start-up and high-speed cutting dumping of the spiral drilling tool，the redundant double backup winding BLDC motor is used as the driving source of the spiral drilling tool，the mathematical model of torque and speed of the double winding BLDC motor is established，and a dual winding BLDC motor is designed. The drive circuit topology scheme of synchronous operation of winding is simulated and analyzed，and the control performance experiment is carried out combined with the prototype. The test results show that the topological structure of the driving circuit can meet the driving control requirements of lunar soil and lunar rock drilling sampling process，and improve the safety and reliability of the drilling sampling process.

Half-ballistic reentry is one of the key links of deep space exploration mission. It is characterized by many key technologies，many design constrains，and difficulties in experimental verification. According to the idea of System Engineering，aiming at the re-entry and return mission of "Chang'E-5"，the design of constraints，reentry corridor，aerodynamic shape and re-entry trajectory is carried out，the relationship between various design elements is clarified，and the design scheme of "Chang'E-5" re-entry system is put forward，and the reentry and return flight procedure and the design of key tasks are also described in this paper. After the actual flight of the reentry vehicle in orbit，it shows that the analysis and design idea of the reentry mission is accurate ，which lays the foundation for the subsequent deep space reentry mission.

During the landing procedure of a recoverable spacecraft，measurement and control information、COSPAS/SARSAT system information and regional location information are often used. According to the deficiencies of above method，the long baseline TDOA technique is suggested. Firstly the principles of TDOA system and the solution of TDOA equations are proposed. The features of the beacon’s sinusoidal envelop are analyzed. High precision frequency estimation method based on modified Rife algorithm and TOA estimation method based on DTFT phase evaluation algorithm are suggested. Simulations on TDOA precision are given. Location precision distribution of the beacon is simulated. The stationary location error is less than 1km when the target range is less than 100km. When the square style of the receiving stations is applied，the dynamical tracking and filtering process is simulated. The results show that range error is less than 1km and azimuth error is less than 1minute during the tracking procedure. Finally the two-dimension velocity estimation method based on the FDOA information is analyzed.

A method based on the reentry trajectory is proposed for analysis the region for ground-based Telemetry，Tracking and Command（TT&C）station，aiming at the problem of multi-day trajectory TT&C station layout optimization and resource allocation in emergency TT&C in the process of the TT&C general analysis and design in reentry. Firstly，the model between the position of the station，the reentry module and the elevation angle of the station is propagated，the detail method of the calculation of the station distribution area，in where reentry module is visible，is put forward，and finally the results of the visible region of the ground station are calculated according to the theoretical reentry trajectory. The method proposed in this paper can quickly obtain the station area visible to the reentry module，which is of great significance for the overall design and of emergency control in reentry.

To achieve the scientific and engineering goals for situ exploration of the sampling area，The payload subsystem of Chang'E-5 explorer is equipped with four types of scientific payloads：the panoramic camera，descending camera，lunar regolith penetrating radar，lunar mineral spectrometer. It is also equipped with the national flag of China exhibition system，the panoramic camera pan-tilt table，and payload data processor as engineering and supporting payloads. This paper introduces the scientific and engineering goals，system composition，function and performance，system design，and operating achievements of the Chang'E-5 payload subsystem.

According to the requirements of multi-load data scheduling，storage multiplexing，storage management and high reliability of lunar exploration project，a management scheme of large-capacity data multiplexing storage module based on NAND Flash chip is designed. Axcelerator series anti-fuse FPGA chip with anti-radiation characteristics is used as the main control chip for scheduling management and storage control of multi-channel load data，and large-capacity NAND Flash chip is used for storage management of multiple loads and on-board telemetry，which realizes the functions of data recording，data management and data playback for multiple data sources as required. The practice results show that the requirements of data multiplexing，storage and playback for deep space exploration can be realized through data transmission frame coding and variable rate playback，which provides reference for the high-speed data downloading for subsequent deep space exploration.

Irregular curves are often used as navigation landmark in the landing of celestial probes. Accurate matching of curves is an important premise for visual navigation. For the problem that curve descriptor matching algorithm are difficult to accurately match and curvature matching algorithm can only handle a pair of curves，an accurate curve matching algorithm combining curve descriptor and curvature is proposed. The curves are extracted by Edge Drawing algorithm first; then the descriptors for curves and supporting regions are built，and the rough matching is completed based on Nearest Neighbor Distance Ratio. After，the unsigned curvature integral is calculated and the curvature is sampled at equal integration intervals. The accurate curve matching is realized based on Normalized Cross Correlation. The experimental results demonstrate that，the algorithm can achieve more than 84% accurate matching rate under scale，rotation and illumination transformations.

Designing a deep-space flexible multi-agent probe capable of autonomous task planning is an important direction for future research and development of deep space exploration technology. Multi-agent deep-space probes involve multiple objects，complex constraints and the uncertain deep space environment in mission planning，but traditional mission planning languages may not describe mission planning accurately，intuitively and concisely. In this paper，a knowledge graph is proposed to represent the planning knowledge for a multi-agent deep space probe. The method first carries out knowledge extraction from the deep space probe，then associates the probe with its state and actions by knowledge fusion，and finally mines the potential relationships between agents by knowledge processing. Compared with MA-PDDL，the method proposed in this paper is simpler and more intuitive，which enables the probe to describe its mission planning autonomously，flexibly，and accurately.

Combined with the configuration and high strength performance requirements of Mars omnidirectional soft landing airbag，the paper focuses on a manufacturing technology for a soft landing airbag to land large load spacecraft. This paper takes Vectran high-performance composite material as an example，and uses the characteristics of manufacturing processes such as sewing and heat sealing to design different overlapping surface structures. Through the control of the sewing and heat-sealing process，the mechanical properties and air tightness of 9 kinds of overlapping surface structures are tested，and the optimal structure of the combined lap joint （20mm） lap surface is obtained，and the strength efficiency is high as 85.9%. The overlapping surface structure is used in the manufacturing process of such a landing airbag，and the spacecraft launch recovery landing test is carried out. In the test，the model landing is stable without rollover and obvious rebound. After the test，the airbag and model structure are in good condition without damage. The results verify that the feasibility of the overlapping surface configuration can be used in the manufacture of a landing airbag for large load spacecraft.