An approximate guidance law for space vehicle injection guidance was studied by means of a digital simulation, using injection of the ELDO launcher into a 300 nm circular orbit as an example. The simulation was restricted to the third stage of flight and to two dimensions. The guidance law is based on continuous re-optimisation of the boost trajectory using measured values of vehicle state (position and velocity) as initial conditions. The approximation introduced corresponds to evaluating solutions which are considered as small departures from a pre-calculated 'reference' or 'nominal' trajectory. The results of the simulation lead to the conclusion that the approximate solution yields adequate guidance performance over a realistic range of vehicle perturbations. (Author)
Simulation of a Linearised Optimum Guidance Law for Space Vehicle Injection, with Application to the Eldo Vehicle
1966
63 pages
Report
Keine Angabe
Englisch
NTIS | 1966
|Inertial Guidance for Eldo Launchers
NTIS | 1968
|European Space Organizations - Eldo
NTIS | 1969
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