First several typical space rendezvous strategies which have been carried out are introduced. Then by analyzing and reviewing two or threeday rendezvous profile and four-orbit short rendezvous profile, the main technical problems in short rendezvous are discussed. According to th- development requirement of Chinese space rendezvous technology, a new short rendezvous profile for autonomous spacecraft is proposed. In this profile, the allowable range of phase angle between chasing spacecraft and target spacecraft is enlarged compared to that of the existing four-orbit short rendezvous profile, however the fuel consumption is almost unchanged. The profile is of great reference value in the field of engineering.

This paper investigates the recursive implementation of adaptive control for flexiblejoint freefloating space manipulators (FFSM). Based on adaptive control for rigid-joint FFSM, joint-space adaptive controller for flexiblejoint FFSM is derived by adding relative damping term, and then the recursive joint-space adaptive control for flexiblejoint FFSM is developed. The recursive jointspace adaptive control consists of two parts, one for the recursive formulation of the manipulator control torques, the other for the recursive updating of the spacecraft reference velocity and acceleration. Simulation is presented to show that the recursive adaptive controller can achieve the joint-space trajectory tracking on a six-DOF FFSM.

Considering parameter identification of onorbit closedloop spacecraft, the periodically timevarying modal parameters and controller gain parameters of a large closedloop spacecraft are identified utilizing subspace method. The coordinate transformations of controller gain matrix in the state space equation are discussed. This approach is used to indentify modal parameters and controller gain matrix of the established ETSⅧ model. The results show that the proposed algorithm is effective in the closedloop identification of modal parameters via verifying closedloop response results in the simulation.

For onorbit autonomous servicing, the relative position and attitude of anear satellites should be controlled accurately. Considering the coupled relation between the relative position and attitude, coupled attitudeorbit dynamics model is established. The deputy satellite is required to close to and finally move around the chief satellite in the task. The expected relative position and attitude are discussed. A control law combined the relative position and attitude is proposed to realize the task requirement. The numerical simulation results show that the control law can overcome the disturbance effects between the relative position and attitude, and finally ensures that the deputy satellite points to and moves around the chief satellite precisely.

The problem of fault diagnosis is concerned with respect to the final phase of the satellite autonomous rendezvous. An unknown input observer is designed based on the open-loop system of the C-W equation, and a H∞ controller is designed based on linear matrix inequality (LMI) for the rendezvous. The simulations are implemented under the robust controller and a PD controller with the presence of disturbance. The results show that the robust controller can realize the autonomous rendezvous well, but the observer represents distinctly under different controllers. Finally, conclusions are drawn and a new research topic for rendezvous is proposed.

The configuration of an X-20-like hypersonic vehicle is researched. By a deep analysis on the relationship of the aerodynamic coefficients with the altitude, Mach number, angle of attack, angle of sideslip and the deflection of the control surfaces, a series of simplified analytical polynomial functions of these variables are fitted. For the controller design, the increments of the control surfaces are treated as the control input. Based on the fitted polynomial expressions and the control inputs, an affine nonlinear model of the hypersonic vehicle is established. This control model is proved to be approximately linearized, thus the feedback linearization method could be designed. Under uncertainties of atmospheric density, aerodynamic moment coefficient and the moment of inertial, the control law for the original dynamic model is simulated. Considering the effect of the earth rotation and the aerodynamic model, simulation of the original model is established by the coefficients lookup tables. The simulation results demonstrate that the control objectives can be achieved and the controller is proved to be robust.

The 3-D space motion dynamic model of a class of airship with constant pressure is presented. Based on the shortest time and the minimum fuel consumption, its route from stratospheric to the ground is designed. In the constructed model and route planning, the atmospheric density, temperature and wind field are considered. The states of the airship, like height, speed, power are also analyzed.

iming at one category of reusable launch vehicle, the guidance problem is investigated for terminal area energy management phase. For a terminal area energy management system, the energy-range-to-go profile is used to guide the vehicle onto the approach and landing interface, and to control the energy dissipation. The height control coefficients in the longitudinal direction and the track control coefficients in the lateral direction are generated based on the linearization method and back-stepping control. The designed parameters are simplified and the constant PD control coefficients are given. On the basis of the off-line programming of the nominal trajectory, the requirements of the approach and landing interface are satisfied via the longitudinal/lateral integration-guidance. The guidance method is proved to be robust against the disturbances and a series of different errors.

In order to study the case that propellant remains in the intracavity of pipeline connector after orbital refueling, the twophase unsteady model of volume of fluid (VOF) is used to simulate the gasliquid flow field during the blowing-off process. The pressure distribution has little range of vibration in the straight pipeline at the initial blowing-off process. There is an eddystyle flow field and the eddy brings the residual propellant from the intracavity of pipeline connector into the straight pipeline, which is the main mechanism of the residue blowing-off process. The results show that most of the residual propellant in the intra-cavity of pipeline connector can be blew out, and prove the fine effect of the blowing-off process.

The temporal correctness has always been a hotspot and difficult problem in the field of space embedded software. With the theory of timed automata, the interrupt management of a certain onboard operating system and the environment interacting with it are modeled respectively to describe the whole interrupt management process. By using the modelchecking tool Uppaal, the performances of interrupt management are verified, including the reachability, the safety, the liveness and the correctness of service behavior.

With the development of space technology in China, the software applied in spacecraft becomes more complex and larger in scale.It is necessary to improve the correctness, reliability and security of software to achieve a high level. Among the approaches, the formal method is an important one.A formal method based on Event-B is introduced to describe the requirement for task model of SpaceOS2.The correctness of this model is formally guaranteed via virtual of invariants. The correctness of the model is verified by using the Rodin platform.