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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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A data combination method for postflight trajectory analysis.
Trajectory measurement errors for powered spacecraft using matrix analysis
Comparative studies of conceptual design and qualification procedures for a Mars probe/lander. Volume V - Subsystem and technical analysis. Book 1 - Trajectory analysis Final report
Trajectory analysis for Mars probe for entry from approach hyperbola or from Mars orbit
An investigation of the aerodynamic characteristics of a 25 deg sphere-cone including a pressure distribution analysis at angles of attack, and a trajectory analysis during a typical reentry trajectory
Aerodynamic characteristics of reentry body - pressure distribution at angles of attack and trajectory analysis
Common Lunar Lander (CLL) trajectory analysis
Common Lunar Lander trajectory analysis is presented in viewgraph format. Trajectory requirements, trajectory characteristics, trajectory timeline, and alternate trajectory advantages and disadvantages are given.
Conference on guidance theory and trajectory analysis
Guidance theory and trajectory analysis conference - research goals and programs in celestial mechanics, astrodynamics, computer utilization, and optimizational calculations
Preliminary trajectory analysis of a Mars probe
Trajectory analysis for Mars atmosphere probe - Voyager Project
On the use of hodographic mapping in trajectory analysis
Hodograph mapping used for trajectory analysis
Orbiter Trajectory Analysis for a Two-Stage Reusable Launch Vehicle
Trajectory analysis performed on NASA's reference two-stage-to-orbit launch vehicle upper stage will be presented. The work was completed in support of the Hypersonics Multidisciplinary Analysis and Optimization effort for the NASA-Air Force Joint System Study. Three degree-of-freedom (3-DOF) untrimmed trajectory analysis was performed for the orbiter ascent, closure and re-entry. An iterative closure process resulted in a 333,000 lb initial mass for the orbiter. The re-entry trajectory satisfied heating constraints for all payload out cases and met the constraints with reduced margins for payload in cases. Abort trajectories for engine out at staging, engine out during ascent, and failure to circularize in orbit, gave insight to the robustness of the orbiter. A trimmed ascent trajectory defined an engine gimbal location and the body flap angle best suited for maximizing injected mass. A trimmed re-entry trajectory revealed a need to update the trim routine to accommodate full flap aerodynamic data.
Trajectory Analysis
The Systems Analysis Branch performs trajectory and systems analysis for next-generation launch vehicle and space transportation technologies. Currently the branch is supporting the Project Prometheus with analysis of nuclear electric and nuclear thermal propulsion missions to a variety of destinations. Within Project Prometheus a proposed mission to Jupiter and three of the planet sized icy moons that orbit it is developing. The Jupiter Icy Moons Orbiter (JIMO) as the project is being called will enable detailed scientific investigation of Jupiter's moons Callisto, Ganymede, and Europa. These moons were choose to orbit for intensive study in particular because they are each believed to have water, energy, and organic material. The JIMO mission will utilize nuclear fission power and electric propulsion in order to allow the spacecraft to orbit the moons at close range for long durations of time. My assignment this summer was to assist in developing a trajectory analysis for the spacecraft system the Jupiter Icy Moons Orbiter by rewriting an inefficient Excel file into a more efficient FORTRAN program. This program has been created for use planning the trajectory of the Jupiter Icy Moons Orbiter Mission. The program uses a database of thousands of data points representing flight time, burn time, thrust, mass of the propellant used, final mass of the spacecraft, ratio of finals mass to initial mass, and change in velocity that a spacecraft experiences during each phase in the Jupiter Icy Moons Orbiter Mission. The trajectory program is capable of taking a specific user entered specific impulse (isp), final mass fraction, and thrust (P(sub J)/m0) and through the use of cubic splines to fit specific data curves, the program can locate the exact flight time linked to the user specified values of specific impulse and final over initial mass fraction. Currently, the database used by the program to calculate flight times for a given thrust is only for isps in the range of 2000 to 9000 seconds. Although the program is specific to the Jupiter Icy Moons Orbiter mission, it can be easily modified to fit any mission with a propulsion system expected isp range between 2000 and 9000 seconds. This program performs the same tasks as the old Excel file but in a more timely fashion. Finally, this FORTRAN program will replace the Excel file as the tool used to calculate trajectory properties in missions and will provide valuable data to mission analysts for years to come.
Spaceflight trajectory analysis at Princeton University.
Space flight trajectory analysis of aerospace systems, discussing Analytical Trajectory Optimization Model
A compilation of current computer programs for low-thrust trajectory analysis
Current computer programs for low thrust trajectory analysis using flyby and rendevous trajectories
A set of uniform variational parameters for space trajectory analysis
Set of uniform variational orbit parameters for space trajectory analysis
Mars lander deorbit trajectory analysis
Mars lander deorbit trajectory sensitivity analysis for fixed flight path and communications angles at atmospheric entry, comparing with Monte Carlo simulation
Sighting and trajectory analysis for periodic comets- 1975-1986
Sighting data and trajectory analysis for mission to periodic comets
Applications of calculus of variations to trajectory analysis Final report
Applying calculus of variations to multistage rocket trajectory analysis
Applications of calculus of variations to trajectory analysis Annual report for 1965
Application of variational calculus to trajectory analysis of multistage vehicle
Buoyant Venus station mission feasibility study for 1972 and 1973 launch opportunities. Volume 2 - Trajectory analysis for 1972 and 1973 missions Final report
Trajectory analysis for 1972 and 1973 buoyant Venus station mission