Thrust Vector Control System Study for a Large Liquid Booster
Abstract
This effort consisted of evaluating six thrust vector control systems for application on a Large Liquid Booster. The thrust vector control systems evaluated were liquid injection thrust vector control, hot gas secondary injection thrust vector control and the following four movable nozzle thrust vector control systems; Flex-Seal nozzle thrust vector control (both supersonic and subsonic seal), ball and socket nozzle thrust vector control and gimbal nozzle thrust vector control. The designs were compared on the basis of thrust vector control system performance (weight, envelope constraints, etc.) The effort consisted of three tasks. The first was the establishment of the baseline missile trajectory (point mass). The second was the use of the steering coefficients obtained from the baseline trajectory in conjunction with wind profiles, moments of inertia, center of gravity versus time and missile irregularities (C.G. offset, nozzle misalignments, etc.) to obtain duty cycle requirements. The third task was the design of the thrust vector control systems of interest and a comparison of performance of the thrust vector control system for each missile stage. For Stage I of the missile the hot gas secondary injection thrust vector control system was the lightest system, with the Flex- Seal nozzle thrust vector control system second, and the liquid injection thrust vector control system third. For Stage II the Flex-Seal nozzle thrust vector control system was lightest with the hot gas secondary injection thrust vector control system second and the liquid injection thrust vector control system third.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1968
- Accession Number
- AD0394122
Entities
People
- Daniel Stump
- Vernon Olivier
Organizations
- Air Force Research Laboratory