Thermal conditions during typical boost trajectory
Aerodynamic heating calculation of Atlas Centaur launch vehicle trajectory
TRAJECTORY↗
SEARCH · Engineering Papers
Results for “Boosting”
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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Evaluation of pilot's ability to stabilize a flexible launch vehicle during first-stage boost
Feasibility of manned participation in control of large launch vehicle
LAUNCH VEHICLE↗
Evaluation of pilot's ability to stabilize a flexible launch vehicle during first-stage boost
Ability of pilot to stabilize flexibile launch vehicle during first stage - Saturn V launch vehicle
PILOT PERFORMANCE↗
Present techniques and problems in the determination of the base heating environment of propelled boost and space vehicles.
Short duration technique for determining base heating of tail ends of multiengine rocket vehicle from exhaust jets
BASE HEATING↗
Simple, one transistor circuit boosts pulse amplitude
Simple circuit that uses a single transistor to accomplish capacitor storage followed by common-base switching supplies a pulse voltage, higher than that normally available from emitter-follower circuits, to drive a 100-watt transmitter.
Keon, T.↗
Explicit guidance equations for multistage boost trajectories
Explicit equations for steering Atlas-Centaur multistage launch vehicle to lunar trajectory
MULTISTAGE VEHICLE↗
Solid-boosted Nova Vehicle Study. Volume III - Current-technology Vehicle Final Report
Structures and weight, environment and control, design configuration, and payload growth of Current-Technology Vehicle /T-65/ - Nova launch vehicle
PAYLOAD↗
Minimum Drag of Four Versions of a Swept-wing Fighter Airplane Obtained from Flight Tests of Rocket-boosted Models at Mach Numbers from 0.81 to 1.71
Swept wing fighter aircraft drag coefficient reduction by configuration redesign
AIRCRAFT CONFIGURATION↗
Prediction of the flight acceleration of a spacecraft in the boost configuration.
Prediction of flight transient torsional acceleration at base of Surveyor spacecraft and implementation of pulse qualification testing
TRANSIENT OSCILLATION↗
Panel flutter studies of boost-vehicle full-scale flight insulation panels
Supersonic wind tunnel tests on flutter resistance of Centaur flight insulation panels
FLIGHT TEST↗
Solid boost thrust decay control for stage separation.
Solid booster thrust decay control for payload or upper stage separation, noting inert slivers with auxiliary retrorockets as separation control
THRUST CONTROL↗
Aerodynamic Characteristics of Several Hypersonic Boost-Glide-Type Configurations at Mach Numbers from 2.30 to 4.63
An investigation has been conducted at Mach numbers from 2.30 to 4.63 to determine the static aerodynamic characteristics of several configurations designed for flight at hypersonic Mach numbers. Two all-wing and three wing-body configurations were tested through an angle-of-attack range from about -4 degrees to 33 degrees and an angle-of-sideslip range from about -4 degrees to 8 degrees at a Reynolds number of 3 times 10 (sup 6) per foot (9.84 times 10 (sup 6) per meter). The results of the investigation indicated that the wing-body configurations produced higher values of maximum lift-drag ratio than those produced by the all-wing models. The high wing-body configurations tend to have a self-trimming capability as opposed to that for the low wing-body configurations. Each of the configurations produced a positive dihedral effect that increased with increasing angle of attack and decreased with increasing Mach number. The high wing-body models produced decreasing values of directional stability with increase in angle of attack, whereas the low wing-body models provided increasing values of directional stability with increase in angle of attack.
Graves, Ernald B.↗
An adaptive orbital rendezvous guidance scheme for multi-burn boost vehicles.
Adaptive orbital rendezvous guidance dynamic aspects valid for burn-coast-burn trajectories
Bennett, A. G.↗
Buck-boost dc voltage regulator
Circuit provides voltage regulation through a wide range of operating frequencies without intervals of high power dissipation.
La Vigna, T.↗
Use of Centaur spacecraft flight data in the synthesis of forcing functions at Centaur main engine cutoff during boost of Mariner Mars 1969, OAO 2, and ATS spacecraft. Volume 1 - Analysis and evaluation
Numerical analysis of acceleration flight data of Mariner Mars 69, OAO 2, and ATS to determine disturbing forcing function of Centaur engines at main engine cutoffs
Chisholm, J. R.↗
Use of Centaur spacecraft flight data in the synthesis of forcing functions at Centaur main engine cutoff during boost of Mariner Mars 1969, OAO 2, and ATS spacecraft. Volume 2 - Computer plots
Computer plots of acceleration flight data of Mariner Mars 69, OAO 2, and ATS showing selected gimbal axis forcing functions and dynamic response of Centaur main engine cutoffs
Chisholm, J. R.↗
Structural design considerations for boost-glide and orbital reentry vehicles
The preceding papers have discussed the aerodynamics and heating of several vehicles designed for atmospheric reentry from satellite orbits. Because of large heating inputs, some fundamental questions about the structure of these vehicles are also raised. Although there are many factors which influence structural design, only a brief examination of the relationship between heating input and structural weight is discussed here. For this purpose the heating inputs associated with the four vehicles shown in figure 1 are employed.
William A. Brooks, Jr.↗
Study of aerodynamic surface control of space shuttle boost and reentry, volume 1
The optimization technique is described which was used in the study for applying modern optimal control technology to the design of shuttle booster engine reaction control systems and aerodynamic control systems. Complete formulations are presented for both the ascent and reentry portions of the study. These formulations include derivations of the 6D perturbation equations of motion and the process followed in the control and blending law selections. A total hybrid software concept applied to the study is described in detail. Conclusions and recommendations based on the results of the study are included.
Chang, C. J.↗