ballis.zip - A method for the determination of the trajectory of a ballistic missile over a rotating, spherical Earth given only the
launch position and impact point has been developed. The iterative solution presented uses a state transition matrix to
correct the initial conditions of the ballistic missile state vector based upon deviations from a desired set of final conditions.
A six-degree-of-freedom simulation of a ballistic missile is developed to calculate the resulting trajectory. Given the initial
state vector of the ballistic missile, the trajectory is simulated and the state transition matrix propagated along the trajectory
to the impact point. The error in the final state vector is calculated and elements of the initial state vector are corrected
using the state transition matrix. The process is repeated,2014-02-12 18:05:09,下载6次
coorsinat.zip - The success of a guided missile is dependent on certain
factors. The most significant error sources affecting the
success of a guided missile are the initial heading error
of the missile and the target maneuvers. Apart from
these, the dynamics of the guidance and control system,
acceleration limit of the missile,2014-02-12 18:02:05,下载3次
spascraft.zip - In this paper, formation control ideas for multiple spacecraft using the virtual structure approach
are presented. If there is no formation feedback from the spacecraft to the virtual structure, the
spacecraft will get out of formation when the virtual structure moves too fast for the spacecraft to
track due to spacecraft control saturation or the total system must sacriˉce convergence speed in
order to keep the spacecraft in formation. The spacecraft may also get out of formation when the
system is a® ected by internal or external disturbances. To overcome these drawbacks, an idea of
introducing formation feedback from the spacecraft to the virtual structure is illustrated in detail.
An application of these ideas to multiple spacecraft interferometer,2014-02-12 17:58:55,下载3次
missile.zip - In this paper, formation control ideas for multiple spacecraft using the virtual structure approach
are presented. If there is no formation feedback from the spacecraft to the virtual structure, the
spacecraft will get out of formation when the virtual structure moves too fast for the spacecraft to
track due to spacecraft control saturation or the total system must sacriˉce convergence speed in
order to keep the spacecraft in formation. The spacecraft may also get out of formation when the
system is a® ected by internal or external disturbances. To overcome these drawbacks, an idea of
introducing formation feedback from the spacecraft to the virtual structure is illustrated in detail.
An application of these ideas to multiple spacecraft interferometers in deep space is given.,2014-02-12 17:56:51,下载3次
pgmissile.zip - Project : Missile Target Simulation using Proportional Navigation
Proportional navigation is the guidance law used by most missiles in operational use
today. This method of guidance, generates missile acceleration commands in proportion
to the line-of-sight (LOS) rate. The missile-target geometry is shown in figure 1 below,2014-02-12 17:55:21,下载16次
proportional-guidance.zip - rds: IR scene generation, MATLAB, Simulink, Countermeasure, IR Seeker, .... separation distance between the source and sensor through the duration of the simulation. .... rate of the line of sight angles from the IR imaging missile to the,2014-02-11 04:30:37,下载23次