Original Rocket Belt Contractor Reports for the US Army

Stability and Control Study of a Small Rocket Lift Device

Abstract : A stability and control study of a Small Rocket Lift Device was performed employing analytic methods. Mathematical definition of the operator's 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.

Full text : apps.dtic.mil/dtic/tr/fulltext/u2/a063189.pdf

Corporate Author : AEROJET-GENERAL CORP AZUSA CA
Personal Author(s) : Sollow, P A

Report Date : 01 Jul 1960
Pagination or Media Count : 80

Abstract : The design of a manned small rocket lift device (SRLD) is described. The device will be a hydrogen peroxide rocket propulsion system on a molded fiberglass corset, shaped to fit the body of the operator. Actual lift is provided by two gimballed rocket nozzles. Flight stability and control can be achieved by any combination of three methods: (1) pure kinesthetic control by body motions, (2) roll damping only by automatic outward lateral gimballing of the nozzles when excited by lateral rotational accelerations, and (3) a control stick mounted on the left forward arm which operates the gimballed nozzles for pitch, roll, and yaw. As a result of successful component development and system tests the design was deemed safe and reliable enough to proceed with manned tethered and free-flight testing of the SRLD.

Corporate Author : BELL AEROSYSTEMS CO BUFFALO NY
BELL AEROSYSTEMS CO BUFFALO NY
Report Date : 01 Jul 1960
Pagination or Media Count : 150

Abstract : The concept of attaching a rocket propulsion system to a man for transporting him from one place to another was successfully demonstrated. This was done by rigorous static testing of the propulsion system, a manned tethered flight program during which various improvements were incorporated, and finally by a manned free-flight program of various types of maneuvers. Additional quantitative data on stability and control is needed to intelligently establish prototype sp cifications. Hydrogen peroxide, although very successfully utilized, would have a limited tactical use due to its handling characteristics and limitations at low ambient temperatures. A better tactical propellant must be found. The basic concept of distributing the SRLD static weight around the man's body by means of a padded Fiberglas corset proved highly successful. Lifting a man under the arms for a short period of time had no deleterious effects and permits excellent kinesthetic control. 

Corporate Author : BELL AEROSYSTEMS CO BUFFALO NY
BELL AEROSYSTEMS CO BUFFALO NY

Full Text : apps.dtic.mil/dtic/tr/fulltext/u2/267358.pdf

Report Date : 01 Jul 1961
Pagination or Media Count : 185

Abstract : The fabrication and testing of the Small Rocket Lift Device (SRLD) is reported. The effort consisted of 4 fundamental tasks: (1) The development of a suitable propellant quantity warning and indicating system; (2) The design and test of a paraglider lift augmentation device for use with the SRLD; (3) Performance of stability and control studies utilizing data in possession of the Contractor from an instrumented rocket belt flight test program to be conducted by the US Air Force; (4) Performance of a human factors study for the purpose of determining optimum trainee selection criteria and establishing SRLD training requirements.
Corporate Author : BELL AEROSYSTEMS CO BUFFALO NY
BELL AEROSYSTEMS CO BUFFALO NY; Kroll, J ; Borass, S ; Carriero, N
Full Text : apps.dtic.mil/dtic/tr/fulltext/u2/409941.pdf
Report Date : Apr 1963
Pagination or Media Count : 191