Formulas from Lambert's problem in celestial mechanics are presented for use in a computer program to calculate velocity requirements for rapid intercept of an earth satellite by a rocket fired from the earth or from an orbit about the earth. The rocket is assumed to receive an impulsive velocity at launch and the effect of impulsive midcourse corrections are considered. The effects of the earth rotation are included is the rocket is fired from the earth, but those due to the earth's atmosphere are ignored. The rocket and target satellite are assumed to be moving in conic section in the earth's gravitational field. (Author)
Velocity Requirements for Rapid Intercept With Midcourse Corrections
1970
56 pages
Report
No indication
English
Antimissile Defense Systems , Spacecraft Trajectories & Flight Mechanics , Bombardment satellites , Intercept trajectories , Interception probabilities , Midcourse guidance , Guided missiles(Air-to-air) , Guided missisles(Surface-to-air) , Elliptical orbit trajectories , Parking orbit trajectories , Differential equations , Integrals , Integration , Lambert problem
Optimization of midcourse velocity corrections.
NTRS | 1966
|Strategic Intercept Midcourse Guidance Using Modified Zero Effort Miss Steering
Online Contents | 1996
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