Stability and Control Study of a Small Rocket Lift Device
AEROJET-GENERAL CORP AZUSA CA
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A stability and control study of a Small Rocket Lift Device was performed employing analytic methods. Mathematical definition of the operators control actuation logic and visual orientation sensing capabilities were formulated. These, together with the equations of motion of the system, were programmed for an IBM 704 digital computer and pitch plane trajectories were computed. Additionally, a yaw plane trajectory and a one degree of freedom roll dynamics program were run on an IBM 610 digital computer. The operator was assumed to appraise himself of his orientation through visual reference to the ground. Thrust direction and magnitude were controlled by the manipulation of hand levers. The linkage of these controls was varied to determine the effect on stability and control. It was determined that controllable flight could be achieved for the man-vehicle system studied. The effects of CG shift, wind, a severe body contortion, variation of flight rules, and temporary loss of thrust were investigated. The configuration which was considered consists of two pressure-fed liquid monopropellant motors mounted to a back pack which supports all vehicle components. A single throttle controls the propellant flow to both motors while a thrust differential between the motors is effected by employing a flow dividing valve. Thrust vectoring is affected through both gimballing of the nozzles and the use of a jetavator. Extensions of the pack structure on each side of the operator bring the hand controls to a position convenient to the operator.
- Fluid Mechanics
- Liquid Propellant Rocket Engines
- Human Factors Engineering and Man Machine Systems