Optimal analytic multiburn trajectories
Fuel optimal analytic multiburn transfer trajectories and shuttle rendezvous, assuming gravity vector linear dependence on position vector for burn arcs
Jezewski, D. J.↗
SEARCH · Search NASA
Results for “RENDEZVOUS TRAJECTORY”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Halley's Comet flythrough and rendezvous missions via solar electric propulsion
Solar electric propulsion application to Halley Comet flythrough and rendezvous missions, describing trajectory characteristics and payload capabilities
Friedlander, A. L.↗
Main-belt asteroid exploration - Mission options for the 1990s
Mission configurations, propulsion systems, and target bodies for possible NASA asteroid exploration projects are examined. Noting that an announced delay in the development of a solar electric propulsion system has led to a consideration of chemical rocket systems, asteroid missions are grouped in terms of five potential areas for investigation, each successively further from the sun. The Shuttle-launched IUS is suggested as the prime candidate for boosting probes into trajectories for asteroid rendezvous with a number of the 3000 known asteroids. Planetary swingbys are mentioned as the only suitable method for satisfying the large energy requirements of the asteroid missions. Performance analyses are presented of the IUS 2-stage/Star-48 and Centaur vehicles, and sample missions to Fortuna, Anahita, and Urania in 1990 and further missions to the middle, outer, and Trojans asteroids are outlined.
Yen, C.-W. L.↗
A Mars sample return mission using a rover for sample acquisition
Mission and vehicle concepts are discussed for obtaining surface and subsurface samples of Mars, acquired by a roving vehicle, and returning those samples to earth for detailed analyses in scientific laboratories. Mission options that were traded off in order to arrive at a baseline mission considered most worthy of further study comprised the following: (1) direct entry vs entry out of Mars orbit; (2) direct return from the Mars surface vs rendezvous in Mars orbit and return to earth from there; and (3) propulsive orbit injection and aeroballistic entry (similar to Viking) vs aerocapture into Mars orbit and aeromaneuvering entry. After a comparison of relative merits - based primarily on mass and cost estimates and secondarily on configurational constraints - a baseline mission was selected: out-of-orbit entry, return after Mars orbit rendezvous, and aerocapture/aeromaneuvering. Trajectory design is based on the 1996 launch opportunity. Launch mass requirements for eight mission options, a mission and vehicle description for the baseline mission, and the outline of a mission sequence of events are presented.
De Vries, J. P.↗
Synergetic plane-change capability of a conceptual aeromaneuvering-orbital-transfer vehicle
The flight strategy for a general low-earth orbit plane-change is analyzed for a conceptual, high-lift, aeromaneuvering-orbital-transfer vehicle, and applied to the important case of the 45 deg plane-inclination change. The study focuses on two principal methods: (1) the procedure to obtain a change in the inclination of the vehicle's orbital plane, and (2) the full rendezvous procedure. Optimal trajectories for minimal propellant use during the synergetic aerotransit are developed, which incorporate best estimates of constraints imposed by reusable thermal-protection requirements and human tolerance to g-load levels. The performance capability for one-way payload delivery to the target orbit is analyzed in detail and the capability for return to the base orbit demonstrated.
Menees, Gene P.↗
MIDAS - Mission design and analysis software for the optimization of ballistic interplanetary trajectories
A patched conic trajectory optimization program MIDAS is described that was developed to investigate a wide variety of complex ballistic heliocentric transfer trajectories. MIDAS includes the capability of optimizing trajectory event times such as departure date, arrival date, and intermediate planetary flyby dates and is able to both add and delete deep space maneuvers when dictated by the optimization process. Both powered and unpowered flyby or gravity assist trajectories of intermediate bodies can be handled and capability is included to optimize trajectories having a rendezvous with an intermediate body such as for a sample return mission. Capability is included in the optimization process to constrain launch energy and launch vehicle parking orbit parameters.
Sauer, Carl G., Jr.↗
Orbit Software Suite
Orbit Software Suite is used to support a variety of NASA/DM (Dependable Multiprocessor) mission planning and analysis activities on the IPS (Intrusion Prevention System) platform. The suite of Orbit software tools (Orbit Design and Orbit Dynamics) resides on IPS/Linux workstations, and is used to perform mission design and analysis tasks corresponding to trajectory/ launch window, rendezvous, and proximity operations flight segments. A list of tools in Orbit Software Suite represents tool versions established during/after the Equipment Rehost-3 Project.
Osgood, Cathy↗
Trajectory design for small-satellite missions to near-earth objects
This paper describes new techniques for use in designing possible trajectories to near-Earth objects (NEOs) given the constraints imposed by the limited propulsive capabilities of small satellites and by being launched as a secondary with larger spacecraft. It illustrates the use of these techniques with the design of a trajectory that achieves rendezvous with the NEO 2007 UN12.
Sims, Jon A.↗
Introduction To Space Shuttle Rendezvous Guidance, Navigation, and Control
The Rendezvous Intro continues to be used for training and reference purposes almost 17 years after it was first published. While this document does not address Orion rendezvous, some Orion personnel are using it as a reference for rendezvous GNC and trajectory concepts. This edition contains corrections that have been identified since the 3rd edition was published in 2000. In addition, new material has been added that was developed by the author in the 1990s and early part of the first decade of the 21st century. While some of this material is perhaps too detailed for an introduction, it is of value and the author wanted to make it available to JSC personnel. The sections on Lambert targeting guidance have been significantly expanded.
John L Goodman↗
A Comparison of Trajectory Optimization Methods for the Impulsive Minimum Fuel Rendezvous Problem
In this paper we present a comparison of optimization approaches to the minimum fuel rendezvous problem. Both indirect and direct methods are compared for a variety of test cases. The indirect approach is based on primer vector theory. The direct approaches are implemented numerically and include Sequential Quadratic Programming (SQP), Quasi-Newton, Simplex, Genetic Algorithms, and Simulated Annealing. Each method is applied to a variety of test cases including, circular to circular coplanar orbits, LEO to GEO, and orbit phasing in highly elliptic orbits. We also compare different constrained optimization routines on complex orbit rendezvous problems with complicated, highly nonlinear constraints.
Hughes, Steven P.↗
Gemini VI-A rendezvous mission planning
Gemini VI-A rendezvous mission planning, design criteria, and spacecraft trajectory
GEMINI PROJECT↗
Trajectories to Comets Using Solar Electric Propulsion
In situ analysis of a cometary nucleus and return of a sample are high priority scientific goals. Rendezvous and sample return trajectories to comets using low-thrust ion propulsion are presented.
trajectory comet low-thrust propulsion↗
Constant-attitude thrust program optimization.
Optimum thrust programming studies include comparison of constant and variable attitude thrust programs for Earth-Mars rendezvous
TRAJECTORY OPTIMIZATION↗
Some Abort Techniques and Procedures for Manned Spacecraft
Abort techniques for manned spaceflight at launch, suborbital, escape and superorbital velocities - lunar launch & rendezvous
ABORT TRAJECTORY↗
Trajectory options for the Mariner Mark II Tempel 2 rendezvous mission
Recent schedule changes have motivated a reassessment of the mission options for the Mariner Mark II Comet Rendezvous Asteroid Flyby. A new baseline mission has been selected, which will launch in September 1992 and arrive at comet Tempel 2 in December 1996. The geometry of the comet's orbit imposes on the mission total delta-V requirements that can best be met by selection of a delta-V-EGA trajectory, during which an earth gravity assist is used to improve mission performance. There is considerable freedom in the choice of comet arrival date and asteroid flyby targets; associated with each potential asteroid flyby is a different penalty in terms of delta-V and comet arrival data. Analysis of the trajectory and the asteroid flyby options will continue throughout the early phases of the Project.
Stetson, D. S.↗
Solar electric performance data for extra ecliptic and solar probes and Ceres, D'Arrest, and Encke rendezvous missions
Solar electric propulsion performance and trajectory data for indirect solar probes, extra-ecliptic missions, and rendezvous with Ceres, D-Arrest, and Encke
Flanagan, P. F.↗
The comet rendezvous asteroid flyby mission to Comet Kopff - Getting there is half the fun
The goal of the Comet Rendezvous Asteroid Flyby mission (CRAF) is to fly 'outward to the beginning', to examine closely what are thought to be remnants of the origins of the solar system. In particular, the CRAF spacecraft will use a two-year delta-V-earth-gravity-assist (delta-V-EGA) trajectory to reach a rendezvous point near the aphelion of the Comet Kopff, flying by the asteroid 449 Hamburga on the way. This paper discusses the trajectory used to get to the comet. Topics covered include the launch period, possible additional asteroid flybys, the earth flyby, the Hamburga flyby, and the rendezvous with Comet Kopff.
Sweetser, Theodore H.↗
An evaluation of interactive displays for trajectory planning and proximity operations
Rendezvous, docking, and other Space Station proximity operations will be routine in nature in years to come. However, the specific parameters describing each maneuver, such as initial range and position, will vary from mission to mission so a means for depicting and interacting with graphic representations of proposed mission plans is necessary. Orbital operations are inherently non-intuitive due to non-linearities in the equations of motion of orbiting vehicles. Consequently, relative motion between two spacecraft cannot always be easily visualized. For these reasons, real time interactive visual aids and planning tools will be helpful, if not necessary, for future missions both in pre-flight training and on-orbit. Two such displays, Navie and eivaN, are currently available for examination and human factors testing. Since the docking tasks were fundamentally different with each device and because Navie imposed more constraints on the users than eivaN did, the orbital mechanics effects had a more pronounced effect on the Navie results.
Brody, Adam R.↗