Optical technology Apollo extension system. Phase A - Executive summary
Space optics experimental studies for development of optical technology Apollo extension system
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Optical technology Apollo extension system /OTES/, phase A study Summary report
Proposed experiments in optical technology Apollo extension system study
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Optical technology Apollo extension system /OTES/, volume 2 Final report
Subsystem conceptual design for manned optical technology extension system - Apollo spacecraft
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Optical technology Apollo extension system /OTES/, volume 1
Optical design concept, optical communications, ground station requirements, and applications of optical technology Apollo extension system
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Some extensions of the Kuhn-Tucker results in concave programming
Some extensions of Kuhn-Tucker results in concave programming
Moore, J. C.↗
Experimental study of aeroelastic instability of overexpanded rocket nozzle extensions
Aeroelastic instability of overexpanded rocket nozzle extensions
Land, N. S.↗
Optical technology Apollo extension system, phase A. Volume 6, section 6 - Resources analysis Final technical report
Resources analyses and cost estimates of program plan for optical technology Apollo Extension System
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The effect of mean stress on fatigue crack propagation in plates under extension and bending.
Mean stress effect on fatigue crack propagation in thin plates under fluctuating plane extension and cylindrical bending
Erdogan, F.↗
The effect of mean stress on fatigue crack propagation in plates under extension and bending.
Mean stress effect on fatigue crack propagation in thin plates under fluctuating plane extension and cylindrical bending
Erdogan, F.↗
Extension of the finite-difference Newton- Raphson algorithm to the simultaneous optimization of trajectories and associated parameters.
Finite difference Newton-Raphson algorithm extension to solve variational equations for simultaneous optimization of trajectories and associated parameters
Van Dine, C. P.↗
An FM threshold extension technique for the Apollo unified S-band communications system.
FM threshold extension device using principle of click detection and elimination designed for Apollo S band communications system
Loch, F. J.↗
An extension of known results in stochastic control theory by means of equivalence.
Equivalence extension to stochastic control theory based on geometric notions in normed function space
Luh, J. Y. S.↗
Extensions in quasilinearization techniques for for optimal control.
Quasi-linearization for optimal bounded continuous control, analyzing quadratic convergence range extension and free time case
Leondes, C. T.↗
Equivalence of FM threshold extension receivers.
FM threshold extension receivers equivalence, demonstrating phase locked loop /PLL/ and frequency locked loop /FLL/ as limiting forms of frequency demodulator with feedback /FMFB/
Hess, D. T.↗
Wind-tunnel force and pressure tests of rocket-engine nozzle extensions on the 0.0667-scale X-15-2 model at supersonic and hypersonic speeds
Wind tunnel force and pressure tests of rocket engine nozzle extensions on X-15-2 model at supersonic and hypersonic speeds
Montoya, E. J.↗
Application of NASAP to the design of communication circuits and extension of NASAP routines to large scale circuits Final report
Application of NASAP to design of circuits and extension of NASAP routines to large scale circuits
Herskowitz, G. J.↗
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.
Arbic, R. G.↗
BASEL - The base language for an extensible language facility
Basic language for extensible language facility
Fischer, A. E.↗