R.-L. Wu’s scientific contributions

In the multi-market, power suppliers should allocate the bidding electricity to each market reasonably in order to minimize the risk and maximize the profits. Decision-making is a multi-period process in bidding, so power suppliers face the multi-period risks (dynamic risks); the revenue rates of different markets have characteristics of stochastic changing. The model of conditional value at risk (CVaR) can measure the risks and revenues, but single period CVaR only reflects the static risk and the fixed revenue rate of single period. So the multi-period bidding strategy model based on the CVaR is applied in bidding, which can rationally reflect the dynamic risks and the stochastic changing characteristics of revenue rates. Applying the model, power suppliers allocate the bidding electricity volume in different periods and different markets rationally to minimize the risk and maximize the expect profits. The calculation results show the validity of the multi-period CVaR model, and provides a new way for bidding strategy and risk valuation.

When the scheduling parameters vary fast, the system which was designed by the traditional methods may be unstable. Aiming at the limitations, the paper designs the attitude control system of the kinetic interceptor whose parameters vary fast by applying the gain scheduling robust control theory. The dynamics model of the kinetic interceptor is first established, and then, the quadratic H∞ performance theorem based on state feedback is introduced and proved. To guarantee the satisfying dynamic performances of the closed loop system, the method of the pole region placement is applied. The last simulation results show the gain scheduling robust control method has good tracking and switching performances, anticipative dynamic responses and assuring system to be globally stable.

Based on the working characteristic of the pulse vector motors, the design methods of control force of the different phase of the tracking process during the end guidance phase are proposed, whose transition phase use optimal control to minimize the motors, and introduce the neural net to assure the real-time. During the initial flight phase, the method which regulates the ballistic trajectory to reduce the overload requirement of the flight middle phase using the direct force is presented. Ignition control algorithm is based on the polar coordinates, which can take full advantage of the motors, and regulate the direction of the direct force. The last simulation shows that the methods which presented in the paper make the attitude control system track the input, and have high engineering application values.

The kinetic interceptor (KI) attacks target by means of hitting-to-kill. Comparing with the classic missiles, the requirement of the zero miss distance (MD) of the KI presents more severe demands for missiles. The paper firstly analysis the elements which influence the MD, then point out the conditions of the zero miss distance which missile must meets by applying the method of theory deducing and digital simulating. The results of the paper have values in engineering applications.

Considering that the atmospheric kinetic interceptor with invariable rolling rate has quick response and strong coupling, this paper firstly analyzes the advantage and disadvantage of the classic design method of the control system, and then it proposes the gain scheduling method based on the regional pole placement, which finds a Lyapunov function in the whole parameter space to guarantee system stability. Compared with the classic method, the new method is not only stable theoretically, but also convenient in calculation. Simulation results show that the controller based on the method which be proposed in this paper has good performance.

Three new cobalt complexes were synthesized by solid-state reaction at room temperature. It was found that one mole of complex reacted with two moles of oxygen at room temperature. And the oxygenated complexes [Co·(L 1)2·2O2](NO3) 2·2H2O (L1=N,N′-bis(4-hydroxyl-3- methoxy-benzyl)-triethylenetetramine), [Co·(L2) 2·2O2](NO3)2 ·2H 2O (L2=N,N′-bis(4-hydroxyl-benzyl)- triethylenetetramine) and [Co·L3·2O2] (NO3)2·2H2O (L3=N,N′- bis(2-hydroxyl-benzyl)-triethylenetetramine) were obtained and characterized by elemental analysis, IR spectra, 1H NMR, TG/DTA, UV-Vis and molar conductance. The coordinated oxygen contents in the oxygenated complex were also determined by weight method. It was found that one O2 molecule coordinated to the Co ion and formed superoxo type oxygenated complex.

An on-off control law of a divert thruster for an exo-atmospheric interceptor during its terminal course was put forward. The interceptor had sustain constant thrust or impulsive thrust perpendicular to the line-of-sight during the flight, and the target was maneuverable. Firstly the dynamic characteristics of the line-of-sight rate under control of the thrust were analyzed, based on which an on-off control law of the divert thruster was designed according to the requirement of the miss distance, considering the maneuver of the target, the switch of the aim point and the switch from sustain constant thrust to impulsive thrust. Simulations have proved the feasibility of the control law theoretically.

The passive ranging with line-of-sight angle or line-of-sight rate measurement for exo-atmospheric interceptor was studied. The observability index of the relative distance was put forward based on the essence of observability, and the analytical expression of the observability index was deduced, then factors affecting the observability of the relative distance was analyzed and validated by simulations. Studies have shown that: better observability goes with smaller closing velocity and greater lateral acceleration; oscillating line-of-sight rate near zero with alternate control of the two opposite lateral engine help the convergence of the estimation error of the relative distance, but the range of the oscillating line-of-sight rate should not be too narrow when the measurement is line-of-sight angle.

The terminal constrain of the midcourse guidance for an exo-atmospheric interceptor is to be on the zero-effort-intercept manifold. The expression of the zero-effort-intercept manifold for several simplified model of the gravitational acceleration difference between the target and the interceptor was deduced, the quantitative precision analysis was also made. Then the guidance law based on the remaining velocity increment for an interceptor with fuel-exhaustion-shutoff solid rocket motor was put forward, and a virtual remaining velocity increment mapping was introduced to eliminate the singularity coming with the remaining velocity increment, and to improve the robustness of the guidance precision to the burning speed error of the fuel. Simulations have shown that, stable thrust and precision consistent with the corresponding zero-effort-intercept manifold come with the guidance law, and perfect robustness is also guaranteed.