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An extended optimal guidance law with terminal miss distance and impact angle constrains is derived. The guidance law is obtained as the solution of a linear quadratic optimal control problem with the goal function weighted by a power of the time-to-go. Based on the analytical expression for the change of guidance command with time and the adjoint system analysis method,the command characteristics and dimensionless miss distance of guidance law are analyzed. The result shows that the acceleration command of guidance law can be converged into zero in the final time of guidance,which may create a good situation for terminal angle of attack control. A design principle for selection of guidance law gain is discussed. Finally,according to the requirements of engineering application,the methods on calculating the guidance initial condition and maximal required acceleration are given. The effectiveness and practicality of the guidance law are demonstrated through simulation. [ABSTRACT FROM AUTHOR]

A new maneuvering-deceleration guidance algorithm based on atmosphere estimation is presented for the precise guidance and velocity control of hypersonic reentry vehicle. The maneuvering-deceleration guidance command is composed of optimal guidance command and deceleration command. The optimal guidance command is obtained by guidance law with position and impact angle constraints. Sinusoid maneuvering-deceleration command is used to minimize the position disturbance caused by deceleration. And the parameters of maneuvering command are produced from mismatch between terminal predicted velocity and nominal-velocity by numerical integration method. The atmosphere parameter identification technology is also used to improve the prediction precision. The simulation results show that the maneuvering-deceleration guidance algorithm has strong robustness against uncertain conditions; it can accomplish the integrated design of precise guidance and deceleration control efficiently. [ABSTRACT FROM AUTHOR]

A new solving method called local accurate search was proposed for the calculation of allowable attack area of air-to-surface missiles. Compared with traditional method, the local accurate search can search the area online and reduce the time of search with the required precision. The new method employs the local search to find an accurate result by combining the traditional flight range table with the model calculation method, which meets the requirements for attacking of moving target and fast calculation. [ABSTRACT FROM AUTHOR]