NASA Scientific and Technical Aerospace Reports
NASA Scientific and Technical Aerospace Reports
NASA Scientific and Technical Aerospace Reports
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ASTRODYNAMICS<br />
Includes powered <strong>and</strong> free flight trajectories; orbital <strong>and</strong> launching dynamics.<br />
20040111217 <strong>NASA</strong> Langley Research Center, Hampton, VA, USA<br />
Neptune Aerocapture Systems Analysis<br />
Lockwood, Mary Kae; [2004]; 16 pp.; In English; AIAA Atmospheric Flight Mechanics Conference <strong>and</strong> Exhibit, 16-19 Aug.<br />
2004, Providence, RI, USA<br />
Contract(s)/Grant(s): 23-800-90-10<br />
Report No.(s): AIAA Paper 2004-4951; No Copyright; Avail: CASI; A03, Hardcopy<br />
A Neptune Aerocapture Systems Analysis is completed to determine the feasibility, benefit <strong>and</strong> risk of an aeroshell<br />
aerocapture system for Neptune <strong>and</strong> to identify technology gaps <strong>and</strong> technology performance goals. The high fidelity systems<br />
analysis is completed by a five center <strong>NASA</strong> team <strong>and</strong> includes the following disciplines <strong>and</strong> analyses: science; mission<br />
design; aeroshell configuration screening <strong>and</strong> definition; interplanetary navigation analyses; atmosphere modeling;<br />
computational fluid dynamics for aerodynamic performance <strong>and</strong> database definition; initial stability analyses; guidance<br />
development; atmospheric flight simulation; computational fluid dynamics <strong>and</strong> radiation analyses for aeroheating environment<br />
definition; thermal protection system design, concepts <strong>and</strong> sizing; mass properties; structures; spacecraft design <strong>and</strong><br />
packaging; <strong>and</strong> mass sensitivities. Results show that aerocapture can deliver 1.4 times more mass to Neptune orbit than an<br />
all-propulsive system for the same launch vehicle. In addition aerocapture results in a 3-4 year reduction in trip time compared<br />
to all-propulsive systems. Aerocapture is feasible <strong>and</strong> performance is adequate for the Neptune aerocapture mission. Monte<br />
Carlo simulation results show 100% successful capture for all cases including conservative assumptions on atmosphere <strong>and</strong><br />
navigation. Enabling technologies for this mission include TPS manufacturing; <strong>and</strong> aerothermodynamic methods <strong>and</strong><br />
validation for determining coupled 3-D convection, radiation <strong>and</strong> ablation aeroheating rates <strong>and</strong> loads, <strong>and</strong> the effects on<br />
surface recession.<br />
Author<br />
Aerocapture; Neptune (Planet); Systems Analysis; Technology Utilization; Aeroshells<br />
20040111310 <strong>NASA</strong> Langley Research Center, Hampton, VA, USA<br />
Hyper-X Post-Flight Trajectory Reconstruction<br />
Karlgaard, Christopher D.; Tartabini, Paul V.; Blanchard, RobertC.; Kirsch, Michael; Toniolo, Matthew D.; [2004]; 21 pp.;<br />
In English; AIAA Atmospheric Flight Mechanics Conference <strong>and</strong> Exhibit, 16-19 Aug. 2004, Providence, RI, USA<br />
Contract(s)/Grant(s): NAS1-00135; BPA-E05204D; BPA-NNL04AA03Z; NCC1-03024; 745-30-30<br />
Report No.(s): AIAA Paper 2004-4829; No Copyright; Avail: CASI; A03, Hardcopy<br />
This paper discusses the formulation <strong>and</strong> development of a trajectory reconstruction tool for the <strong>NASA</strong> X{43A/Hyper{X<br />
high speed research vehicle, <strong>and</strong> its implementation for the reconstruction <strong>and</strong> analysis of ight test data. Extended Kalman<br />
ltering techniques are employed to reconstruct the trajectory of the vehicle, based upon numerical integration of inertial<br />
measurement data along with redundant measurements of the vehicle state. The equations of motion are formulated in order<br />
to include the effects of several systematic error sources, whose values may also be estimated by the ltering routines.<br />
Additionally, smoothing algorithms have been implemented in which the nal value of the state (or an augmented state that<br />
includes other systematic error parameters to be estimated) <strong>and</strong> covariance are propagated back to the initial time to generate<br />
the best-estimated trajectory, based upon all available data. The methods are applied to the problem of reconstructing the<br />
trajectory of the Hyper-X vehicle from ight data.<br />
Derived from text<br />
Trajectories; Numerical Integration; Equations of Motion<br />
20040111460 Massachusetts Inst. of Tech., Cambridge, MA<br />
Geosynchronous Orbit Determination Using Space Surveillance Network Observations <strong>and</strong> Improved Radiative Force<br />
Modeling<br />
Lyon, Richard H.; Jun. 2004; 376 pp.; In English; Original contains color illustrations<br />
Contract(s)/Grant(s): F19628-00-C-0002<br />
Report No.(s): AD-A425362; No Copyright; Avail: CASI; A17, Hardcopy<br />
Correct modeling of the space environment, including radiative forces, is an important aspect of space situational<br />
awareness for geostationary (GEO) spacecraft. This study is intended to improve orbit determination accuracy for 3-axis<br />
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