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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Large scale low speed wind tunnel tests of delta winged supersonic transport model to determine aerodynamic effects of forward and reverse thrust
Liquid insertion thrust vector control system for Voyager project
Solid booster thrust decay control for payload or upper stage separation, noting inert slivers with auxiliary retrorockets as separation control
Necessary conditions for optimal fixed-time powered transfers with multiple coasts and thrusts between circular orbits
Critical mass flow rate existence for maximum thrust from MPD arc jet
Manual thrust vector control development for Apollo Command and Service Module Stabilization and Control System
Optimum thrust nozzle contours for chemically reacting gas flows, obtaining set of partial differential equations for gas dynamic properties
M-1 Engine Thrust Chamber Assembly test facilities and analog computor simulation during checkout
MIRA 150A variable thrust rocket engine applied to manned lunar exploration flying systems
Fuel consumption precision measurements for low thrust auxiliary rockets using impeller wheel and photometric devices
Formulation of problem of guiding low thrust spacecraft back to nominal trajectory
Vehicle mass requirements for optimal high and low thrust propulsion systems for manned and unmanned planetary missions
Design and applications of gas-lubricated journal and thrust bearings of self-acting and externally pressurized types
Trajectory optimization, performance and other factors in analysis of low thrust solar electric propulsion Jupiter flyby mission
Efficiency of conical thrust nozzles with various lengths and cone angles, determining optimization coefficient
I am now proposing a method for the preliminary approximate calculation of the thrust distribution and efficiency of air propellers under any operating conditions. Our task becomes the following, namely, to determine the speed relations and the forces developed on a section with a given direction and velocity of the air current, a problem which can be solved with the aid of the momentum theory.
An investigation was conducted to compare the performance of two 25-ft-diam rotors which had identical dimensions and were similar in construction but different in blade airfoil-sections. Tests were conducted at indicated blade pitch angles from 3 degrees to 11.5 degrees and rotor speeds of 200, 290, and 371 rpm. The 23012.6 rotor required 2 percent less power to hover than the 0012.6. At thrust coefficients above design, the performance of the 23012.6 became better than the 0012.6 rotor.
An application of the new optimization algorithm called Static/Dynamic Control (SDC) to design low-thrust escape and capture trajectories is presented.