Trajectory analysis of a 1970 mission to Mercury via a close encounter with Venus.
Unmanned spacecraft trajectory and guidance considerations for close flyby of planet Mercury
SPACECRAFT GUIDANCE↗
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An Earth-Mars mission-analysis program
Rapid, flexible computer program for Earth-Mars trajectory and mission analysis
Kibler, J. F.↗
(abstract) Earth-Jupiter-Earth Trajectories and the Europa Ice Clipper Mission
The nature of Earth-Jupiter-Earth trajectories that can flyby close to Europa is described and details of opportunities with launches from 2000 through 2003 are presented.
Europa↗
Trajectory Design and Early Mission Operations for the Lunar IceCube Mission
Explore the source record for details and available documents.
Robert Pritchett↗
Comet rendezvous missions
Jupiter swingby trajectory analysis for comet flyby and rendezvous missions, discussing approach velocity and payloads
Manning, L. R.↗
Navigation and the Mars global surveyor mission
Navigation and trajectory planning aspects for the Mars global surveyor (MGS) mission, are discussed. In the first 205 days of the mission since launch on 7 November July 1996, two trajectory maneuvers were successfully completed. The third maneuver was cancelled due to the accuracy of the targeting of the previous maneuvers. The final trajectory correction maneuver will occur on arrival in order to adjust the arrival conditions for the Mars orbit insertion maneuver. The planned capture orbit is highly elliptical with a 45 hour orbital period, a 300 km periapsis altitude and a descending node. Two-way coherent Doppler and time delay measurements are acquired in the X-band by the Deep Space network and used to navigate the spacecraft. After capture, the orbit will be circularized by aerobraking and propulsive maneuvers. The three-phase aerobraking maneuver is described. During the 687 earth-day observation period, navigation will maintain a 2:00 pm descending node, sun-synchronous low altitude, short periodic orbit. Ground track coverage will remain almost uniform in order to maximize data acquisition.
Esposito, P.↗
New trajectory options for ballistic Mercury Orbiter Mission
This paper reports on recent advances made in obtaining low delta V trajectories to conduct Mercury orbiter missions.
Mercury↗
An analysis of atmospheric entry trajectories for manned and unmanned missions to the planet Venus
A unified atmospheric density model is presented for the planet Venus, and this model is compatible with Russian and American data obtained during the 1967 Venus launch opportunity. Trajectory characteristics involved in atmospheric entry are discussed with reference to roll-control modulation and entry corridor. Subsequent to a trajectory-oriented discussion of potential Venus mission characteristics, a parametric analysis of manned and unmanned vehicle entry trajectories into the Venusian atmosphere is presented. A sensitivity analysis with reference to atmospheric density deviations is included to show the dependence of corridor depth on the atmospheric density profile.
Craig, M. K.↗
Current trajectory options for a comet nucleus sample return mission
A summary of the current trajectory options available for the ESA comet nucleus sample return mission, Rosetta, is presented. These options include direct trajectories, delta-V-EGA trajectories using a Titan IV/Centaur launch vehicle with upgraded solid rocket motors, a trajectory involving a gravity assist of the earth (VEGA) prior to comet rendezvous, and one involving an additional gravity assist of the earth (VEEGA). Other propulsion options proposed and discussed are solar electric propulsion/ballistic trajectory modes and nuclear electric propulsion trajectory modes. Tables of performance data for each of these trajectory options are given.
Sauer, Carl G., Jr.↗
Interplanetary trajectory design for the Galileo mission
The Galileo mission has been reprogrammed to use a direct earth-Jupiter trajectory with a May 1986 launch date and with arrival at Jupiter occurring in mid-1988. Within the constraints of Shuttle/Centaur launch vehicle capability and total spacecraft mass and performance, optimal broken-plane trajectories are generated, and the region of positive propellant margin in the launch/arrival space is determined. Mission constraints are used to define a launch/arrival strategy. It is also shown that a close flyby of any one of several asteroids or a comet is possible on the interplanetary transfer with minimal impact on mission performance.
Damario, L. A.↗
Low-thrust trajectory analysis for the geosynchronous mission
Methodology employed in development of a computer program designed to analyze optimal low-thrust trajectories is described, and application of the program to a Solar Electric Propulsion Stage (SEPS) geosynchronous mission is discussed. To avoid the zero inclination and eccentricity singularities which plague many small-force perturbation techniques, a special set of state variables (equinoctial) is used. Adjoint equations are derived for the minimum time problem and are also free from the singularities. Solutions to the state and adjoint equations are obtained by both orbit averaging and precision numerical integration; an evaluation of these approaches is made.
Jasper, T. P.↗
On orbit mission planning using the shuttle trajectory and launch window expert system
With the Space Transportation System (STS) entering the operational era, the need for standardized, automated, mission planning computer tools has become apparent. In order to support an increased flight rate without an increase in manpower, quicker and more efficient methods are needed to perform standard tasks. The Shuttle Trajectory and Launch Window Expert System (STALEX) was developed to automate many aspects of early mission planning for space shuttle missions carrying geosynchronous communications satellites. Most of the commercial Shuttle missions planned for the next 3 years will carry at least one of this type of satellite. The applications of STALEX include payload deployment scheduling, launch window analysis, orbital trajectory determination, and landing opportunity selection.
Ahlf, P. R.↗
CEV Trajectory Design Considerations for Lunar Missions
The Crew Exploration Vehicle (CEV) translational maneuver Delta-V budget must support both the successful completion of a nominal lunar mission and an "anytime" emergency crew return with the potential for much more demanding orbital maneuvers. This translational Delta-V budget accounts for Earth-based LEO rendezvous with the lunar surface access module (LSAM)/Earth departure stage (EDS) stack, orbit maintenance during the lunar surface stay, an on-orbit plane change to align the CEV orbit for an in-plane LSAM ascent, and the Moon-to-Earth trans-Earth injection (TEI) maneuver sequence as well as post-TEI TCMs. Additionally, the CEV will have to execute TEI maneuver sequences while observing Earth atmospheric entry interface objectives for lunar high-latitude to equatorial sortie missions as well as near-polar sortie and long duration missions. The combination of these objectives places a premium on appropriately designed trajectories both to and from the Moon to accurately size the translational V and associated propellant mass in the CEV reference configuration and to demonstrate the feasibility of anytime Earth return for all lunar missions. This report examines the design of the primary CEV translational maneuvers (or maneuver sequences) including associated mission design philosophy, associated assumptions, and methodology for lunar sortie missions with up to a 7-day surface stay and with global lunar landing site access as well as for long duration (outpost) missions with up to a 210-day surface stay at or near the polar regions. The analyses presented in this report supports the Constellation Program and CEV project requirement for nominal and anytime abort (early return) by providing for minimum wedge angles, lunar orbit maintenance maneuvers, phasing orbit inclination changes, and lunar departure maneuvers for a CEV supporting an LSAM launch and subsequent CEV TEI to Earth return, anytime during the lunar surface stay.
Condon, Gerald L.↗
Orbit determination results and trajectory reconstruction for the Cassini/Huygens Mission
During Cassini's third orbit around Saturn, the Huygens Probe was successfully released on a trajectory that resulted in the probe entering Titan's atmosphere on January 14, 2005, making it both the most distant spacecraft landing and the first spacecraft to successfully land on the moon of another planet. This paper documents the reconstruction of both the orbiter and probe trajectoriespanning the Titan-B and Titan-C encounters.
reconstruction↗
Estimating trajectory correction requirements for multiple outer planet missions.
General approach to the problem of estimating trajectory correction requirements for multiple outer planet flyby missions when the navigation system uses onboard optical measurements made during approach to each target planet to complement the ground-based radio measurements. The accuracy and reliability of the onboard measurement system plays a critical role in sizing the trajectory correction capability required. An illustration of the combined use of radio and optical measurements is provided for the particular case of a Jupiter-Uranus-Neptune mission. Use of the statistical technique developed for computing the trajectory correction margin required to account for uncertainties in subsystem performance, permits trajectory correction savings of 100 to 20 m/sec over 'worst case' designs. This represents weight savings of about 50% of the science payload. For the example case trajectory correction requirements are estimated for two candidate optical systems and the radio alone case. The use of onboard measurements allows a trajectory correction savings of approximately 140 m/sec.
Friedman, L. D.↗
Updating the Reference Trajectory for the Cassini Solstice Mission
The Cassini-Huygens deep-space probe has successfully completed a four-year prime tour and a two-year extended tour of the Saturnian system. Now in a second extended phase called the Solstice Mission, the Cassini spacecraft will continue to gather data as directed by the reference trajectory until 2017. This paper will describe the process of how a reference trajectory update is prepared and delivered to the project by the navigation team during Solstice Mission flight operations. This paper will also document the timeline of products released and utilized, as well as the study to include an Enceladus occultation observation that occurs in 2016.
navigation operations↗
Spaceflight dynamics 1993; AAS/NASA International Symposium, 8th, Greenbelt, MD, Apr. 26-30, 1993, Parts 1 & 2
A conference on spaceflight dynamics produced papers in the areas of orbit determination, spacecraft tracking, autonomous navigation, the Deep Space Program Science Experiment Mission (DSPSE), the Global Positioning System, attitude control, geostationary satellites, interplanetary missions and trajectories, applications of estimation theory, flight dynamics systems, low-Earth orbit missions, orbital mechanics, mission experience in attitude dynamics, mission experience in sensor studies, attitude dynamics theory and simulations, and orbit-related experience. These papaers covered NASA, European, Russian, Japanese, Chinese, and Brazilian space programs and hardware.
Teles, Jerome↗