LOWER LIMIT ON BOOSTER REQUIREMENTS TO ORBIT AND SUBSEQUENTLY DE-ORBIT A PAYLOAD
Abstract
DESCRIPTORS: (*Booster rockets, Effectiveness, Thrust, Velocity.) (Satellite vehicles, *Launching.) (Orbital flight paths, Mathe matical analysis.) Re-entry aerodynamics, Deceleration. A study is presented of a simplified ap roach to the calculation of minimum booster requirements for a typical earth-launched orbit and subsequent deorbit mission. It is intended primarily as an introduction to the orbital mechanics of such a mission. A two-dimensional inverse square force field centered within a circular nonrotating earth is assumed. The propulsion mechanism is assumed to be 100 percent efficient and capable of directing thrust into any direction. At any instant the masses present are those of useful payload and unburned propellant with no mass assumed for dead casing weight. Atmospheric losses are neglected. The results establish the lower limit on velocity increments below which the mission cannot be accomplished. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1961
- Accession Number
- AD0265375
Entities
People
- Ronald R. Harrington
Organizations
- Air Force Special Weapons Center