OPTIMUM TWO-IMPULSE ORBITAL TRANSFER AND RENDEZVOUS BETWEEN INCLINED ELLIPTICAL ORBITS
Optimum two-impulse orbital transfer and rendezvous between any pair of unperturbed elliptical orbits
ORBITAL TRANSFER↗
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OPTIMUM TWO-IMPULSE ORBITAL TRANSFER AND RENDEZVOUS BETWEEN INCLINED ELLIPTICAL ORBITS
Spacecraft rendezvous trajectory between two elliptical orbits is determined by optimization of the two impulse orbital transfer
ORBITAL TRANSFER↗
A method for determining nodal arrival times at the moon from precessing near-earth parking orbits having various inclinations
Effect of precession of near-earth orbits on timing of inplane launching for nodal encounter with moon
PRECESSION↗
Satellite motion for arbitrary eccentricity and inclination around the smaller primary in the restricted three-body problem.
Perturbation technique to study three-body problem of motion of close satellite
SATELLITE ORBIT↗
Satellite motion for arbitrary eccentricity and inclination around the smaller primary in the restricted three-body problem.
Motion of close satellite of smaller primary in restricted three-body problem referred to conventional rotating frame in which central angle is chosen as independent variable
ORBIT EQUATION↗
Hypersonic viscous interaction on sharp and blunt inclined plates.
Mach 42 test measuring surface pressures, surface heat transfer rates and shock wave shapes in strong interaction regime for sharp and blunt plates
Kemp, J. H., Jr.↗
Quasilinearization program for determining optimum finite-thrust transfers between inclined orbits
Quasi-linearization program for boundary value problem of minimum fuel orbital transfer
Bender, D. F.↗
Theoretical and experimental study of supersonic steady flow around inclined bodies of revolution.
Three dimensional hypersonic steady flow around blunt and pointed cones at nonzero angles of attack calculated by method of characteristics
Cleary, J. W.↗
Hypersonic viscous interaction on sharp and blunt inclined plates.
Mach 42 test measuring surface pressures, surface heat transfer rates and shock wave shapes in strong interaction regime for sharp and blunt plates
Kemp, J. H., Jr.↗
Launch phase abort analysis for a 50 deg orbital inclination trajectory
Launch phase abort analysis for ascent to orbit trajectory
Source record↗
The space radiation environment in low altitude and low inclination orbits
Charged particle dose rates for men and radiation sensitive materials during long-duration flights in low orbit
Burrell, M. O.↗
Film cooling following injection through inclined circular tubes
Film cooling effectiveness measured following air injection through discrete holes into turbulent boundary layer of air on flat plate
Eckert, E. R. G.↗
Theoretical and experimental study of supersonic steady flow around inclined bodies of revolution
Three dimensional hypersonic steady flow around blunt and pointed cones at nonzero angles of attack calculated by method of characteristics
Cleary, J. W.↗
The influence of magnetic total intensity and inclination on directions preferred by migrating European robins (Erithacus rubecula)
The directional orientation of migratory European robins in relation to magnetic cues is analyzed. Major efforts were made to determine what information the birds derive from the fields. It was determined that magnetic fields provide: (1) field intensity which determines whether the magnetic field can be used for orientation, (2) a means by which axial direction may be perceived, and (3) a means by which the bird can find the north direction. The north direction is sensed from the angle between gravity and the magnetic field.
Wiltschko, W.↗
Eccentricity and inclination of Miranda's orbit
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Whitaker, E. A.↗
Relationship between the near-earth inclinations of lunar trajectories to earth's equator and the moon's orbit plane
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Johnson, F.↗
A momentum analysis of helicopters and autogyros in inclined descent, with comments on operational restrictions
A momentum theory was developed for rotors in descending flight. Comparison with available experimental data indicates that the theory, when properly interpreted, yields the optimum performance of the rotor. Power settling can be explained on the basis of the theory. The reasons and the need for operational restrictions on descending flight are discussed. The maximum autorotative performance of a rotor is determined; the theory shows good agreement with flight measurements in autorotation. Similar equations were developed for a wing; it was shown that the ideal performance of an autorotating rotor is identical to that of a wing of equal aspect ratio. A limiting maximum wing lift coefficient which is confirmed by existing experimental data was obtained.
Heyson, H. H.↗