Research achievements review. Volume 3 - Astrodynamics, guidance and optimization research at MSFC
Orbital analyses for artificial satellites and computer calculations on interplanetary trajectories
Source record↗
SEARCH · Engineering Papers
Results for “astrodynamics”
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.
Determination of astrodynamic constants and a test of the general relativistic time delay with S-band range and Doppler data from Mariners 6 and 7
Earth/moon mass ratio and Mars mass and ephemeris from Mariners range and Doppler tracking data, noting relativistic time delay measurement possibility
Anderson, J. D.↗
Determination of astrodynamic constants and a test of general relativistic time delay with S-band range and Doppler data from Mariners 6 and 7
General relativistic time delay and moon-earth masses and Mars mass-ephemeris ratios from S-band range and Doppler tracking
Anderson, J. D.↗
Astrodynamics. Volume 1 - Orbit determination, space navigation, celestial mechanics.
Essential navigational, physical, and mathematical problems of space exploration are covered. The introductory chapters dealing with conic sections, orientation, and the integration of the two-body problem are followed by an introduction to orbit determination and design. Systems of units and constants, as well as ephemerides, representations, reference systems, and data are then dealt with. A detailed attention is given to rendezvous problems and to differential processes in observational orbit correction, and in rendezvous or guidance correction. Finally, the Laplacian methods for determining preliminary orbits, and the orbit methods of Lagrange, Gauss, and Gibbs are reviewed.
Herrick, S.↗
Astrodynamics 1975; Conference, Nassau, Bahamas, July 28-30, 1975, Technical Papers
Articles are grouped under four headings: (1) dynamics and control of satellites; (2) satellite mission analysis; (3) Aeros-B and Symphonie satellite engineering problems; (4) optimization and control techniques applied to solar space heating and cooling of buildings. Topics covered include: communications and earth survey satellite systems, a system of two counter-orbiting satellites measuring GRT-predicted nodal drag, statistical mechanics studies of the spatial density function of orbiting space junk, attitude control of satellites, nutation dampers, low thrust inertial guidance and ascent inertial guidance, a shuttle-launched multi-comet intercept mission, preflight and in-flight analysis of the Atmosphere Explorer (AE-C) satellite, and launch-encounter strategy for the Mariner 1977 Jupiter-Saturn mission. Individual items are announced in this issue.
Powers, W. F.↗
Astrodynamics 1979; Proceedings of the Conference, Provincetown, Mass., June 25-27, 1979. Parts 1 & 2
Topics are presented on navigation systems, inner planets, comets and asteroids, outer planets, earth orbital applications, and computational methods. Individual subjects include an overview of the Navstar Global Positioning System and the Navy Navigation Satellite System, the solar probe mission, Uranus mission options, as well as a study of lifetimes of geosynchronous transfer orbits, and the price of oil in the year 2000.
Penzo, P.↗
Trajectory Design for a Europa Orbitter Mission: A Plethora of Astrodynamic Challenges
The icy moon of Europa is a hot topic in planetary exploration. This paper discusses the trajectory design of a Europa orbiter mission intended to find out if Europa is a possible habitat for extraterrestrial life.
Jupiter spacecraft trajectory design techniques sa↗
An Update on NAIF's Package of "SPICE" Astrodynamics Tools
"SPICE" is an information system, comprising both data and software, providing engineers and scientists with the geometry data needed to help design robotic solar system missions, conduct mission engineering operations, plan observations from instruments, and analyze the data returned from those observations. The SPICE system has been used on the majority of worldwide planetary exploration missions since the time of NASA's Magellan mission to Venus, and it appears to be the ancillary information system of choice for most future solar system exploration missions. Along with its "free" price tag, portability and the absence of licensing and export restrictions, its stable, enduring qualities and substantial user support in terms of training and consultation help make it a popular choice among scientists and engineers.
Acton, Charles↗
Distributed Parameter System for Optimization and Filtering in Astrodynamic Software
No abstract available
Smith, Jonathan↗
MONTE Python for Deep Space Navigation; or Astrodynamic Computing with MONTE
No abstract available
Smith, Jonathan↗
Evolution of Astrodynamics for Multibody Environments, Numerical Precision and Dynamical Understanding
The innovative nature of dynamical systems theory and its applications in trajectory design enabled many recent missions by opening up new transfer and capture opportunities to meet mission requirements, reduce fuel costs, and address various launch constraints and contingencies. With a combination of proven numerical methods and an advanced understanding of the dynamics, an ‘experienced’ user can rapidly design multibody and cislunar missions such as Lunar IceCube and Artemis/Themis and relatively quickly conceive trajectory concepts for Sun-Earth mission orbits, such as the Space Weather Follow On-L1 Lissajous orbit—one that can be achieved and maintained.
David C Folta↗
Evolution of Astrodynamics for Multibody Environments, Numerical Precision and Dynamical Understanding
The innovative nature of dynamical systems theory and its applications in trajectory design enabled many recent missions by opening up new transfer and capture opportunities to meet mission requirements, reduce fuel costs, and address various launch constraints and contingencies. With a combination of proven numerical methods and an advanced understanding of the dynamics, an ‘experienced’ user can rapidly design multibody and cislunar missions such as Lunar IceCube and Artemis/Themis and relatively quickly conceive trajectory concepts for Sun-Earth mission orbits, such as the Space Weather Follow On-L1 Lissajous orbit—one that can be achieved and maintained.
Dynamical Systems↗
CubeSat Interplanetary Exploration: A Deep Dive into Propulsion and Astrodynamics for Small Satellites
CubeSats are small satellites often used for university research. • However, entities like NASA are starting to look to CubeSats for interplanetary missions. • Their standardized form makes them economical and therefore desirable.
Belian, Olivia↗
MONTE Python for Deep Space Navigation
The Mission Analysis, Operations, and Navigation Toolkit Environment (MONTE) is the Jet Propulsion Laboratory’s (JPL) signature astrodynamic computing platform. It was built to support JPL’s deep space exploration program, and has been used to fly robotic spacecraft to Mars, Jupiter, Saturn, Ceres, and many solar system small bodies. At its core, MONTE consists of low-level astrodynamic libraries that are written in C++ and presented to the end user as an importable Python language module. These libraries form the basis on which Python-language applications are built for specific astrodynamic applications, such as trajectory design and optimization, orbit determination, flight path control, and more. The first half of this paper gives context to the MONTE project by outlining its history, the field of deep space navigation and where MONTE fits into the current Python landscape. The second half gives an overview of the main MONTE libraries and provides a narrative example of how it can be used for astrodynamic analysis.
aerospace↗
The Mission Accessibility of Near-Earth Asteroids
Astrodynamical Earth departure dates; mission v; mission duration; stay time; etc. Physical I NEO size(?); rotation rate; dust satellites environment; chemistry; etc. Architectural Launch vehicle(s); crew vehicle(s); habitat module(s); budget; etc. Operational Operations experience; abort options profiles; etc. Astrodynamical Accessibility is the starting point for understanding the options and opportunities available to us. Here we shall focus on. Astrodynamical Accessibility.2 Earth departure date between 2015-01-01 and 2040-12-31 Earth departure C3 60 km2s2. Total mission v 12 kms. The total v includes (1) the Earth departure maneuver from a 400 km altitude circular parking orbit, (2) the maneuver to match the NEAs velocity at arrival, (3) the maneuver to depart the NEA and, (4) if necessary, a maneuver to control the atmospheric re-entry speed during Earth return. Total round trip mission duration 450 days. Stay time at the NEA 8 days Earth atmospheric entry speed 12 kms at an altitude of 125 km. A near-Earth asteroid (NEA) that offers at least one trajectory solution meeting those criteria is classified as NHATS-compliant.
Trajectory Optimization↗