Optimum deorbit positioning for minimum impulse reentry.
Optimum deorbit positioning on planetocentric elliptic orbit for single impulse reentry treated by two coupled quartic polynomials
SEARCH · Engineering Papers
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Optimum deorbit positioning on planetocentric elliptic orbit for single impulse reentry treated by two coupled quartic polynomials
Three-impulse orbital transfer from lunar orbits and earth reentry trajectory applications
Optimum deorbit positioning on planetocentric elliptic orbit for single impulse reentry treated by two coupled quartic polynomials
Three-impulse orbital transfer from lunar orbits and earth reentry trajectory applications
Analytic solution obtained for minimum impulse transfer between two neighboring low eccentricity orbits
Error probabilities of matched filter receiver operating in additive combination of impulsive and Gaussian noise
Optimum two-impulse orbital transfer for arbitrary terminal conditions, discussing analytic characteristics
Mariner IV midcourse 50-lb thrust pressure- controlled monopropellant hydrazine propellant system, predicting impulse and velocity error as function of burn time
This paper describes how expansions in leaky (or improper) modes may be used to represent the continuous spectrum in an open radiating waveguide. The technique requires a thorough knowledge of the life history of the improper modes as they migrate from improper to proper Riemann surfaces. The method is illustrated by finding the electric field resulting from an impulsively forced current located in the free space above a grounded dielectric slab.
The design and development of a minimum impulse thruster valve was conducted, by Moog, under contract by NASA's Jet Propulsion Laboratory, California Institute of Technology, for deep space propulsion systems. The effort was focused on applying known solenoid design techniques scaled to provide a 1 -millisecond response capability for monopropellant, hydrazine ACS thruster applications. The valve has an extended operating temperature range of 20(deg)F to +350(deg)F with a total mass of less than 25 grams and nominal power draw of 7 watts. The design solution resulted in providing a solenoid valve that is one-tenth the scale of the standard product line. The valve has the capability of providing a mass flow rate of 0.0009 pounds per second hydrazine. The design life of 1,000,000 cycles was demonstrated both dry and wet. Not all design factors scaled as expected and proved to be the focus of the final development effort. These included the surface interactions, hydrodynamics and driver electronics. The resulting solution applied matured design approaches to minimize the program risk with innovative methods to address the impacts of scale.
Cause of the preliminary reverse impulse of storms
Preliminary reverse impulse of storms - analysis of atmospheric current functions
Similitude requirements in scale model determination of shell buckling under impulsive pressures
Optimum two-impulse orbital transfer and rendezvous between inclined elliptical orbits
Mass flow measurement using orifices in impulse base flow facility
Optimum two-impulse orbital transfer and rendezvous between any pair of unperturbed elliptical orbits
Spacecraft rendezvous trajectory between two elliptical orbits is determined by optimization of the two impulse orbital transfer
Proposed impulsive magnetohydrodynamic device for spacecraft power supplies, using a plasma gun without destructive electrode losses