System, synthesized to extend radio command guidance to missions with over-the-horizon orbital injection requirements and its application to mission requiring direct powered ascent into 100-naut-mi circular parking orbit, free fall through 205° of parking orbit, and transfer burn to place vehicle on lunar trajectory or Hohmann transfer ellipse for synchronous orbit insertion; powered flight guidance equations using computation of required velocity and technique to implement cross-product steering with altimeter and accelerometer measurements are given; computer program, capable of performing error analysis of data processing scheme, was used to assess orbit determination capabilities of system.
Inertially augmented radio altimeter guidance system for space booster vehicles
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 9
1966
7 pages
Article (Journal)
English
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