NASA Scientific and Technical Aerospace Reports

a 35 percent decline in its external spending during the past decade. It has been able to maintain its level of space system
expenditures during this period, but many other areas have suffered.
DTIC
Aerospace Industry; Cost Analysis; Government Procurement; Procurement
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ASTRODYNAMICS
Includes powered and free flight trajectories; orbital and launching dynamics.
20060000021
Fitting the Fully Coupled ORM for the Fermilab Booster
Huang, X.; Lee, S. Y.; Prebys, E.; January 2004; 8 pp.; In English
Report No.(s): DE2005-15017120; FERMILAB-CONF-05-115; No Copyright; Avail.: Department of Energy Information
Bridge
The orbit response matrix (ORM) method (1) is applied to model the Fermilab Booster with parameters such as the BPM
gains and rolls, and parameters in the lattice model, including the gradient errors and magnet rolls. We found that the gradients
and rolls of the adjacent combined-function magnets were deeply correlated, preventing full determination of the model
parameters. Suitable constraints of the parameters were introduced to guarantee an unique, equivalent solution. Simulations
show that such solution preserves proper combinations of the adjacent parameters. The result shows that the gradient errors
of combined-function magnets are within design limits.
NTIS
Fitting; Matrix Methods; Independent Variables; Booster Rocket Engines
15
LAUNCH VEHICLES AND LAUNCH OPERATIONS
Includes all classes of launch vehicles, launch/space vehicle systems, and boosters; and launch operations. For related information see
also 18 Spacecraft Design, Testing and Performance; and 20 Spacecraft Propulsion and Power.
20060001781 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Investigation of the Performance Characteristics of Re-Entry Vehicles
Bilbey, Charles A.; Sep. 1, 2005; 85 pp.; In English; Original contains color illustrations
Report No.(s): AD-A440191; AFIT/GSS/ENY/05-S01; No Copyright; Avail.: Defense Technical Information Center (DTIC)
When a non-US spacecraft reenters the Earth’s atmosphere, having the ability to accurately determine its performance
characteristics is a primary concern. This study investigated the atmospheric re-entry profiles of a maneuverable re-entry
vehicle. The re-entry vehicle was modeled as a point mass with aerodynamic properties. Equations of motion were numerically
integrated, giving the time histories of position, velocity and flight path angle. The algorithm is able to generate a complete
and feasible entry trajectory of a approximately 25-minute flight time in about 5 to 10 seconds on a desktop computer, given
the entry conditions and values of constraint parameters. This preliminary study shows the feasibility of identifying and further
exploring the technical challenges involved in using a mathemathical model to simulate the performance characteristics of the
maneuvering re-entry vehicle.
DTIC
Maneuverable Reentry Bodies; Reentry Vehicles
20060001809 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
The Effect of Aerodynamic Surfaces Versus Thrust Maneuvers on Reentry Vehicles
Albrecht, Meredith M.; Sep. 1, 2005; 85 pp.; In English; Original contains color illustrations
Report No.(s): AD-A440289; AFIT/GAE/ENY/05-S01; No Copyright; Avail.: Defense Technical Information Center (DTIC)
This research effort analyzes the effect of aerodynamic surfaces versus thrust maneuvers on a reentry vehicle. At high
altitudes the effect of aerodynamic surfaces on the reentry vehicle is small due to low atmospheric density; however as the
vehicle reaches lower altitudes a lift maneuver is very successful in deflecting the vehicle and creating a large impact footprint.
When a continuous thrust maneuver is input in the place of a lift maneuver the results are very similar at the highest maneuver
altitudes, although the impact footprint shrinks rapidly as the maneuver altitude decreases. Additionally, when the thrust
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