TERMINAL GUIDANCE OF A LUNAR PROBE
Abstract
The problem of guiding a lunar probe to a zerovelocity or soft landing the moon is discussed. A self-contained guidance system is proposed, and measurement instruments and accuracies, guidance computer transfer functions, and the magnitude and control of impulse required in the terminal maneuver are treated. It is concluded that guidance in two stages, lateral guidance at a point some 5,000 miles above the surface using optical and inertial instruments as error sensors, and braking along the path near the surface of the moon using a radio altimeter as an error sensor, is feasible. Existing components and techniques are adequate to perform these functions; asid from weight reduction, no new developments are needed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 14, 1958
- Accession Number
- AD0262023
Entities
People
- C.r. Gates
Organizations
- Jet Propulsion Laboratory