HYBRID MOTOR CONCEPTS III. STATIC TESTING OF BLADDER AND PISTON EXPULSION SYSTEMS FOR A TANDEM SOLID-HYBRID MOTOR
Abstract
A hybrid propulsion system consisting of a five-inch solid/hybrid motor, a bladder expulsion tank and valves, and controls was evaluated in fourteen static tests and one flight test. Four static tests proved the satisfactory operation of the hybrid motor (developed in a previous program) when supplied with inhibited red fuming nitric acid by the bladder expulsion tank, pressure regulator, and nitrogen storage tank. Six motors were static tested to determine the effect of conditioning temperature on hybrid-motor operation. Although the hybrid-fuel regression rate decreased, the oxidizer rate increased with decreasing temperature, resulting in little overall change in the chamber pressure. A control system based on the linear relationship between the integral of pressure over time and the propellant expelled from a rocket motor was evaluated with the low- and high-temperature firings. The system worked well in sequencing the operation of the hybrid motor to follow the solid-booster operation by measuring the integral Pdt for the booster. One solid/hybrid motor was successfully flight tested on March 23, 1967. Operation of the motor consisted of one second of solid boost followed by two seconds of hybrid sustainer thrust. Motor performance was very similar to that of static test motors. A gas-generator-pressurized piston expulsion system was developed and tested at -40, 77, and 140 F. The gas-generator propellant charge was mounted on the piston, inside the tank which it pressurized. All parts of the system performed satisfactorily except the hot-gas relief valve, whose operation was erratic.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1967
- Accession Number
- AD0385867
Entities
People
- William C. Stone