The paper surveys the attitude tracking of aircrafts via Fliess functional expansion. First, one step and ¯nite step predictive controls are considered. Then we show that when the system decoupling matrix is of full row rank, using a proper state feedback, the closed-loop system has a Fliess functional expansion with only ¯nite terms. This approach is particularly suitable for the online design of attitude control of spacecraft.

A composite attitude controller for the base and the manipulator is designed for a free-flying space robot via the backstepping method. The controller ,which feeds back the position and orientation of the manipulator tip in workspace, joint angle and speed in joint space, attitude and velocity of the base, can fulfill the task in workspace directly, avoiding the motion planning from workspace to joint space and complicated differentiating of Jacobian matrix. Meanwhile, attitude control of the base can extend the capacity of space robot and improved the character of dynamical singularity. Finally, the numerical simulation of a free-flying space robot validates the controller.

Rendezvous between two spacecraft is a very important spaceflight mission . Based on the C-W equation, equations with both rectangular coordinates and orbital elements for the impulse maneuvers in long-distance guidance are derived. The iterative processes for solving equations are given. As the maneuvers are applied, the variables are not enough to satisfy all the final-time constraints. This paper gives the partial variable aiming method to satisfy some of the final-time constraints. Numerical simulations show that partial variable aiming method can aim concerned variables.

For the guidance law design problem of lunar spacecraft reentry at the second cosmic velocity, a predictor-corrector guidance method is adopted. The flight characteristic of spacecraft at the balanced attack angel is analyzed, and then the three degrees of freedom motion equation for reentry is established. Furthermore, the theory of predictor-corrector and its longitudinal and lateral guidance laws are introduced in detail. Reentry simulation in such two conditions, one in standard initial condition and other in error initial condition shows that the predictor-corrector can not only acquire higher accuracy, but has strong robustness to the initial errors at all constraints to be satistied, even at the uncertain conditions.

The qualitative model-based fault diagnosis approach can depict the system configuration in qualitative model, and get the predicted behavior qualitatively. The system fault can be diagnosed by determining the differences between the model of an artifact and the artifact itself. This paper investigates the diagnosis mechanism, system modeling, advantages and disadvantages of the qualitative model-based fault diagnosis approach. Its progress, application, and trend developing are also addressed.

A new approach for nonlinear filtering systems is presented in this paper to meet the requirements both on accuracy and computing time. This method, called as approximate second-order extended Kalman filter (AS-EKF), is based on the frame of recursive linear minimum variance estimation. Other than extended Kalman filter (EKF) linearizing all nonlinear models, the new approach estimates the expectation value to the second-order of accuracy. We show that this technique is more accurate than EKF, and it also costs the less computing time than unscented Kalman filter (UKF).It can be used in the nonlinear filtering concerned with both accuracy and computing time.

The attitude control problem of the assembled spacecraft in rendezvous and docking tasks is studied in this paper. Control capability of thrusters whose outputs are bounded is analyzed firstly. Then the controller is designed by using intelligent adaptive control method based on characteristic model. The same controller is applied to the one-shaped and L-shaped assembled spacecraft, and the simulation results are given respectively. In contrast with the robust controller, this method is feasible and of much advantages.

The time-varying parameter estimation is a challenging problem in strapdown inertial navigation system (SINS)/synthetic aperture radar (SAR) integrated navigation systems because SAR measurements are fairly few and have unequal interval. Based on the orthogonality principle, an adaptive recursive least square (RLS) algorithm of SINS/SAR integrated navigation systems is proposed. The adaptive RLS can estimate the time -varying parameters by constructing adaptive fading factors. The adaptive RLS algorithm is deduced and its performance is rigorously analyzed. It is proved that the parameter estimation error of the algorithm is exponentially uniformly bounded. Simulation results demonstrate the feasibility and effectiveness of the proposed approach.

Research involved in this paper focuses on attitude dynamics modeling and control of a spin-stabilized micro-satellite for near-earth space exploration. There are some special requirements for attitude control due to the scientific mission. During modeling, the effect of double-side booms-extended disturbance on the satellite attitude has been considered in detail. Using the nutation characteristics of the spin-stabilized satellite, a controller of attitude control combined with nutation control has been designed. The firing time is determined based on the phase of satellite transverse angular velocity and the orientation of jet torque in the inertial space. Following control strategy has been applied: firstly coarse nutation control and precession control, then fine nutation control. When the satellite nutation angle is large due to the long term action of disturbance torques and orbit maneuver is needed, this controller can be used to adjust the orientation of spin axis conveniently.

The SRAM-based FPGA is one of the on-board electrical devices susceptible to radiation. In addition, effects and errors induced by single event effect on SRAM-based FPGA are distinct from others because of its special structure and operation. This paper analyzes in detail diverse fault modes for SRAM-based FPGA in space applications, and investigates broadly the corresponding fault-tolerant methods by taking the mainstream device in this type of FPGA as objects. Results show that we are able to effectively decrease the possibilities of the radiation-induced faults of SRAM-based FPGA by taking appropriate fault tolerant methods.

The high frequency jitter resulting from high speed rotor of actuators in its rotating process has a serious effect on the attitude control accuracy and stability. In this paper the whirling characteristics of high speed rotors are analyzed by means of building the dynamics model of high speed rotors in flywheel and control moment gyro (CMG). An experiment is also designed to test related results of the theoretical analysis.

There is error of the traditional accelerometer self-calibration method in the presence of an accelerometer bias and it is not easy to validate correctness of calibrated parameters. Based on the contraction mapping theorem, an iterative calibration method for the accelerometer and a simple effective method validating calibrated parameters are brought forward. All these are proved in this paper.