A BOOST GUIDANCE SCHEME FOR FOLLOWING A TRAJECTORY PROFILE AND SATISFYING INJECTION CONSTRAINTS,
Abstract
Presented in this paper is a guidance philosophy that is useful for rocket booster missions that have complex specifications on injection conditions together with a requirement for closely following a given trajectory profile. The steering philosophy involves the use of position and/or velocity profiles, which are functions of current speed in the initial stages of flight and 'time-to-go' until the desired injection speed is attained in the final stage of powered flight. This type of guidance philosophy makes it possible to satisfy constraints on altitude, flight path angle, speed, orbital inclination, and angle of attack at injection. Both the pre-flight computations on the ground and the airborne computations can be accomplished with a reasonable effort. The main contribution of this paper involves pitch and yaw steering computations. The application of this philosophy to representative injection guidance problems is discussed. The steps needed to determine the parameters in the guidance equations are presented. Finally, some simulation results are given for an injection mission involving a DynaSoar type vehicle. These results demonstrate the high accuracy capability of this guidance philosophy and indicate that it should be applicable to other missions with similar guidance objectives. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 30, 1964
- Accession Number
- AD0603234
Entities
People
- Carl Grubin
- P. R. Schultz
- R. V. Sougl
Organizations
- The Aerospace Corporation