a.i. solutions subject matter experts have authored and presented a wide range of technical papers on topics of specific interest to the mission design community. All papers are available in PDF format, which requires Adobe Acrobat Reader available here.
| Title |
Author(s) |
Conference |
| 2010 |
|
An operational Conjunction Assessment Risk Analysis (CARA) concept is the real-time process of assessing risk posed by close approaches and reacting to those risks if necessary. The most effective way to completely mitigate conjunction risk is to perform an avoidance maneuver. This paper identifies and presents these experiences as general concepts in the description of the Conjunction Assessment, Flight Dynamics, and Flight Operations methodologies and processes.
|
R. Frigm, J. Levi, D. Mantziaras |
AIAA SpaceOps 2010 Conference
25-30 April 2010
Huntsville, AL
|
| 2009 |
|
The Magnetospheric Multiscale (MMS) program involves a four-spacecraft tetrahedral formation flying mission intended for launch in 2014. The first of two main science mission phases requires a 1.2 by 12 Earth radii (Re) orbit, while the second phase requires a 1.2 by 25 Re orbit. A variety of stringent operational requirements and constraints, plus design features of these spinning spacecraft, pose significant challenges to the apogee raising design. This paper focuses on the strategy and methodology for, and the solutions to, the apogee raising design problem, and presents and discusses nominal solutions to the problem of recovery from off-nominal finite burns and maneuver contingency scenarios.
|
C. Roberts, J. Tichy, C. Gramling |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
The Magnetospheric MultiScale (MMS) Mission is a tetrahedral formation mission designed to study magnetic reconnection in the Earth's magnetosphere. This paper focuses on quantifying the MMS yearly launch window opportunities defined by the associated science and operating parameters and constraints. This paper will present the MMS launch window opportunity assessment method, assessment results, and an analysis of the orbit perturbation effects on various science and engineering constraints. The impact of initial launch conditions on the implementation of NASA spacecraft disposal requirements will also be considered.
|
L. Mann, J. Tichy, C. Gramling |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
This document describes the collision risk assessment operations concept that will be employed for the NPOESS project. The NPOESS program is managed by a tri-agency Integrated Program Office, involving personnel from the Department of Commerce, Department of Defense and NASA.
|
A. Bleich, M. Duncan, and J. Wysack |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
Summarizes results from a linear covariance analysis to determine the type and amount of tracking data required to accurately estimate the spacecraft state, plan each perigee raising maneuver, and support thruster calibration during early commissioning phase. The primary focus of this study is the navigation accuracy required to plan the first and the final perigee raising maneuvers. Absolute and relative position and velocity error histories are generated for all cases and summarized in terms of the maximum root-sum-square (RSS) consider and measurement noise error contributions over the definitive and predictive arcs and at discrete times including the maneuver planning and execution times.
|
L. Chung, S. Novak, A. Long, C. Gramling |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
The Conjunction Assessment Team at NASA Goddard Space Flight Center provides conjunction risk assessment for many NASA robotic missions. These risk assessments are based on several figures of merit, such as miss distance, probability of collision, and orbit determination solution quality. However, these individual metrics do not singly capture the overall risk associated with a conjunction, making it difficult for someone without this complete understanding to take action, such as an avoidance maneuver. The goal of this analysis is to introduce a single risk index metric that can easily convey the level of risk without all of the technical details. The proposed index is called the conjunction “F-value.” This paper presents the concept of the F-value and the tuning of the metric for use in routine Conjunction Assessment operations.
|
R. Frigm |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
Phase 2b of the MMS mission has the most challenging navigation requirements because, during this phase, GPS signal acquisition is restricted to less than one day of the 2.8-day orbit. This paper summarizes the results from high-fidelity simulations to determine if the MMS navigation requirements can be met between and immediately following the maintenance maneuver sequence in Phase 2b.
|
P. Scaperoth, A. Long, R. Carpenter |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
Describes analysis that was performed to characterize the debris environment that MMS will encounter and estimate the number of Risk Mitigation Maneuvers (RMM) that could potentially be required over the mission lifetime. Additionally, an assessment of the GSFC Conjunction Assessment (CA) tool suite was performed to determine its applicability for performing conjunction assessment for the MMS mission.
|
D. McKinley, D. Rohrbaugh, R. Carpenter |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
There is often skepticism about the need for Conjunction Assessment from mission operators that invest in the “big sky theory”, which states that the likelihood of a collision is so small that it can be neglected. On 10 February 2009, the collision between Iridium 33 and Cosmos 2251 provided an indication that this theory is invalid and that a CA process should be considered for all missions. This paper presents statistics of the effect of the Iridium/Cosmos collision on NASA’s Earth Science Constellation as well as results of analyses which characterize the debris environment for NASA’s robotic missions.
|
R. Frigm, L. Newman, D. McKinley |
2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA 9-13 August, 2009 |
|
In this paper, the use of cellular automata (CA) models is extended to understand the development of ephemeral regions into sunspots and then, subsequently, the development and motion of larger scale field structures (spots and unipolar magnetic regions, UMRs) to form the solar dynamo.
|
K. Schatten |
Solar Physics |
|
One of the micropropulsion systems produced by Microspace in Trieste-Italy has been subjected to extensive laboratory testing at our Singapore facility. Various manoeuvres have been studied with the software FreeFlyerR (FF), a commercial off-the-shelf spacecraft Mission Design tool developed by a.i. solutions, Inc., and equivalent set of impulses have been performed, thereby completing the laboratory functional test of such micropropulsion EM.
|
Giulio Manzoni, Yesie Lestari Brama, Adam Austin, Rob Conde |
Space Technology Japan |
| 2008 |
|
This paper presents a Kalman filter using a seven-component attitude state vector comprising the angular momentum components in an inertial reference frame, the angular momentum components in the body frame, and a rotation angle.
|
F. L. Markley, J. Sedlak |
Journal of Guidance, Control, and Dynamics, Vol. 31, No. 6, 2008 |
|
Presents an analysis of the determination of the relative velocity threshold below which the assumption of linearity becomes invalid, and a statistical study of conjunction interactions between representative asset spacecraft and the associated debris field environment to determine the likelihood of encountering a low relative velocity close approach. This analysis is performed for both the LEO and GEO orbit regimes.
|
R. Frigm, D. Rohrbaugh |
59th International Astronautical Congress Conference
Glasgow, Scotland |
|
Describes early mission ground attitude support experience with two spinning spacecraft missions: Space Technology-5 (ST-5) and Time History of Events and Macroscale Interactions during Substorms (THEMIS).
|
G. Natanson, J. Sedlak, J. Hashmall, R. Harman |
AIAA/AAS Astrodynamics Specialist Conference and Exhibit
Honolulu, Hawaii |
|
Investigates the use of a Model Reference Adaptive Control (MRAC) direct approach to solve the attitude control problem of an Expendable Launch Vehicle (ELV) during its boost phase of flight.
|
C. Plaisted, A. Leonessa |
AIAA Guidance, Navigation and Control Conference
Honolulu, Hawaii |
|
Analyzes the planning of conjunction Risk Mitigation Maneuvers (RMM) in the presence of ground-track control requirements.
|
D. McKinley |
18th AAS/AIAA Space Flight Mechanics Meeting,
Galveston, TX |
|
Examines the First- and Second-Order Gauss-Markov process as a model that is stable and covers the covariance of current clock models.
|
T. Lee,
R. Carpenter |
18th AAS/AIAA Space Flight Mechanics Meeting,
Galveston, TX |
|
Presents various close approach statistics for the Earth Science Constellation, the percentage of close approach events induced by the Fengyun-1C debris, and analysis results which predict the future effects on the Earth Science Constellation caused by this event.
|
M. Duncan,
D. Rand |
18th AAS/AIAA Space Flight Mechanics Meeting,
Galveston, TX |
| 2007 |
|
Overview of software modifications required to support navigation and orbit determination for NASA’s twin heliocentric science missions, Solar Terrestrial Relations Observatory (STEREO) Ahead and Behind, including the processing of Deep Space Network X-band tracking data.
|
N. Ottenstein, A. Nicholson, M. Nicholson, D. Ward, M. Mesarch, M. Robertson, J. Cosgrove, D. German, S. Hendry |
20th International Symposium on Space Flight Dynamics, Annapolis, MD |
|
Proposes levels of simulation to enhance the proficiency of the Flight Dynamics Facility (FDF) and supporting elements in recovery from a TDRS contingency situation.
|
A. Dykes, J. Dunham, D. Ward, M. Robertson, G. Nesbit |
20th International Symposium on Space Flight Dynamics, Annapolis, MD |
|
A description of constraints and requirements analysis affecting the handover scheduling of SDO’s High Gain Antennas
|
J. Hashmall, L. Mann |
20th International Symposium on Space Flight Dynamics, Annapolis, MD |
|
Analyzes source of error in long term predictions of meal local time for the members of the Earth observing System Afternoon Constellation. Discusses corrections added to the operational force models by inclusion of a solid Earth tide model.
|
D. McKinley |
20th International Symposium on Space Flight Dynamics, Annapolis, MD |
|
Examines the effects of bi-weekly formation maintenance maneuvers on the absolute and relative orbit determination accuracy for the four-spacecraft Magnetospheric Multiscale (MMS) formation.
|
M. Volle, T. Lee, A. Long, C. Gramling, R. Carpenter |
20th International Symposium on Space Flight Dynamics, Annapolis, MD |
|
Examines a method of optimizing the deployment of a formation of spacecraft about a reference halo orbit using relative dynamics and relative targeting conditions.
|
M. Volle |
AAS/AIAA Astrodynamics Specialist Conference; Mackinac Island, Michigan |
|
Analyzes uncertainties in the predicted semi-major axis change during Aqua inclination maneuvers which led to the development of new analysis tools to ensure that future inclination maneuver plans meet ground-track control requirements.
|
D. McKinley |
AAS/AIAA Astrodynamics Specialist Conference; Mackinac Island, Michigan |
|
An examination of magnetic field sources in the Sun's dynamo.
|
K. Schatten |
The Astrophysical Journal, Supplement Series, March 2007 |
|
Examines the sensitivity of orbit decay predictions to realistic daily variations in solar flux.
|
B. Naasz, K. Berry, K. Schatten |
AAS/AIAA Astrodynamics Specialist Conference; Mackinac Island, Michigan
Aug 19-23, 2007
|
|
Presents a Kalman filter using a seven-component attitude state vector
comprising the angular momentum components in an inertial reference frame, the angular
momentum components in the body frame, and a rotation angle.
|
L. Markley, J. Sedlak |
AIAA Guidance, Navigation, and Control Conference,
Hilton Head, SC. |
| 2006 |
|
A survey of the state of the space industry in implementing autonomous spacecraft on-board and ground systems. Survey includes 88 autonomous space missions.
|
D. LaVallee, C. Olsen, J. Jacobsohn, J. Reilly |
Space 2006, San Jose, CA |
|
Explores techniques including Monte Carlo to adapt the standard linearized propagation of an orbital covariance matrix in calculating collision probability when performing collision risk assessment for low-Earth orbit missions.
|
C. Schiff |
AIAA/AAS Astrodynamics Specialist Conference; Keystone, CO |
|
Presents and iterative method for three-axis magnetometer (TAM) calibration that combines attitude independent and attitude dependent calibration algorithms with a new spinning spacecraft Kalman filter.
|
J. Sedlak |
AIAA/AAS Astrodynamics Specialist Conference; Keystone, CO |
|
Orbital space debris conjunction assessment and risk mitigation process for NASA low-earth satellites.
|
P. Demarest |
|
|
New tools developed to analyze close approach, conjunction assessment and risk mitigation strategies involving orbital space debris for NASA low-earth satellites.
|
L Newman, M. Duncan |
AIAA/AAS Astrodynamics Specialist Conference; Keystone, CO |
|
Extended Kalman Filter for attitude estimation and attitude determination of spinning spacecraft.
|
L. Markley, J. Sedlak |
7th International Conference on Dynamics and Control of Systems and Structures in Space; Greenwich, UK |
|
Uses the Cones Method to compensate for sensor uncertainty in attitude determination of spinning spacecraft.
|
J. Hashmall |
AIAA/AAS Astrodynamics Specialist Conference; Keystone, CO |
|
The development of a new algorithm and a 3D collision probability tool for NASA low-earth satellites.
|
D McKinley |
AIAA/AAS Astrodynamics Specialist Conference; Keystone, CO |
|
Conjunction and risk assessment process by computing orbit space debris collision probability for NASA low-earth satellites.
|
M. Duncan, A. Long |
AIAA/AAS Astrodynamics Specialist Conference; Keystone, CO |
|
The CALIPSO launch ascent, trajectory and mission design to phase with CloudSat.
|
C. Salcedo, L. Mann |
SpaceOps 2006, Rome, Italy |
|
New attitude determination and attitude control algorithm developed after change in TRMM altitude and life-time extension.
|
S. Bilanow, S. Slojkowski |
19th International Symposium on Space Flight Dynamics, Kanazawa, Japan |
|
Optimizing the rendezvous of two spacecraft on Halo orbits.
|
Michael Volle |
19th International Symposium on Space Flight Dynamics, Kanazawa, Japan |
|
An algorithm for on-orbit gimbaled platform calibration including biases, misalignments and scale factors for the HGA's onboard the SDO spacecraft mission.
|
J.Hashmall |
19th International Symposium on Space Flight Dynamics, Kanazawa, Japan |
|
A study of spacecraft and space mission programs using on-board and on the ground autonomous operations and control; primarily for low earth orbit (LEO) spacecraft.
|
J.Reilly,T.Lee |
AIAA - 4th Responsive Space Conference, Los Angeles, CA |
| 2005 |
|
Flight dynamics techniques and mission design challenges to monitor the status of a constellation and formation of NASA low earth satellites.
|
P. Demarest,
K. Richon,
F. Wright
|
AAS/AIAA Astrodynamics Specialists Conference, Lake Tahoe, California |
|
Multiple spacecraft trajectory designs to achieve a heliocentric orbit including libration point orbit (L1) and double lunar swingby (DLS) orbit.
|
R. Muller,
H. Franz,
C. Roberts
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
New variables called Markley variables are used for attitude determination and estimation in spinning spacecraft in an extended Kalman filter.
|
J. Sedlak |
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt,Maryland |
|
The Solar Dynamo method, also known as the precursor method, of solar activity predictions and forecasting is reviewed.
|
K. Schatten,
H. Franz
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
A flight dynamics analysis to determine accuracy of HST orbit prediction ephemeris to minimize ZOE with CALIPSO spacecraft.
|
A. Nicholson,
G. Dell |
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
A flight dynamics study to develop a technique for TDRS orbit determination that can be automated and meets stricter requirements – using GTDS and RTOD.
|
K. Dang,
S. Slojkowski,
D. Ward,
J. Dunham,
M. Blizzard
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Uses Satellite Tool Kit (STK) and the STK Conjunction Analysis Tool (CAT) to study the effects of altering the TDRS orbit to avoid close approaches, conjunctions and collisions with other TDRS, other satellites and orbit debris.
|
A. Dykes |
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
An investigation of anomalous stars identified by the Aura CCD star trackers using the SKYMAP star catalog.
|
C. Sande,
G. Natanson,
D. Tracewell
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Defines spacecraft sensor pseudonoise as apparent sensor errors due to spacecraft vibration and quantifies its behavior and discusses its effect.
|
J. Hashmall,
S. Lennox
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Describes a three step estimator to calibrate a three axis magnetometer (TAM) for spinning spacecraft.
|
G. Natanson |
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Coordinating inclination maintenance maneuvers for a constellation of NASA low earth satellites.
|
D. Rand,
L. Newman,
K. Work
|
AAS/AIAA Astrodynamics Specialists Conference, Lake Tahoe, California |
|
Flight dynamics mission planning and design to form a constellation of NASA low earth satellites.
|
R. McIntosh,
L. Newman
|
AAS/AIAA Astrodynamics Specialists Conference, Lake Tahoe, California |
| 2004 |
|
Automating flight dynamics attitude sensor calibration at NASA Goddard Space Flight Center.
|
J. Sedlak,
J. Hashmall
|
AIAA/AAS Astrodynamics Specialist Conference, Providence, Rhode Island |
|
Data gathered from the first inclination maneuver to begin phasing with a constellation of NASA low earth satellites.
|
D. Rand,
J. Reilly,
C. Schiff
|
18th International Symposium on Space Flight Dynamics Munich, Germany |
|
An extended Kalman Filter for spinning spacecraft with torques using new variables called Markley variables.
|
J. Sedlak |
18th International Symposium on Space Flight Dynamics Munich, Germany |
|
A flight dynamics analysis to resolve Aqua attitude differences by comparing batch least squares and extended Kalman Filter results.
|
J. Hashmall,
G. Natanson,
J. Glickman,
J. Sedlak
|
18th International Symposium on Space Flight Dynamics Munich, Germany |
|
Navigation and orbit determination approaches for a tetrahedral spacecraft formation of satellites.
|
C. Gramling,
R. Carpenter,
T. Lee,
A. Long
|
18th International Symposium on Space Flight Dynamics Munich, Germany |
|
Spacecraft mission design techniques for transferring trajectories between Libration Point Orbits (LPOs).
|
C. Roberts |
18th International Symposium on Space Flight Dynamics Munich, Germany |
|
CALIPSO mission planning and design strategies to avoid sun-glint.
|
L. Mailhe,
C. Schiff,
J. Stadler
|
AAS/AIAA Space Flight Mechanics Meeting Maui, Hawaii |
|
Trajectory and mission design strategies for a tetrahedral spacecraft formation of satellites.
|
A. Edery |
Conference Big Sky, Maryland |
|
How to optimize mission design for a spacecraft formation of satellites based on a variety of variables.
|
L. Mailhe,
J. Guzman
|
IEEE Aerospace Conference Big Sky, Montana |
| 2003 |
|
Solving for the sun-earth-vehicle angle to avoid earth shadow for a Lissajous Orbit at the L2 libration point for the MAP mission.
|
A. Edery |
13th AAS/AIAA Space Flight Mechanics Conference Ponce, Puerto Rico |
|
Orbit mission design and autonomous maneuver control for the GPM mission.
|
D. Folta,
C. Mendelsohn,
L. Mailhe
|
AAS/AIAA Astrodynamics Specialist Conference Big Sky, Montana |
|
Development of a general mission design optimization procedure for spacecraft flying in a tetrahedron (or any) formation to be used for MMS mission.
|
J. Guzman |
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Long term solar activity and solar flux predictions.
|
K. Schatten |
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Trajectory and mission design strategy for a tetrahedron spacecraft formation of satellites performing a double lunar swingby.
|
J. Guzman,
A. Edery
|
13th AAS/AIAA Space Flight Mechanics Conference Ponce, Puerto Rico |
|
Compares various mission design and trajectory optimization strategies for solving the impulsive minimum fuel rendezvous problem.
|
S. Hughes,
L. Mailhe,
J. Guzman
|
AAS Rocky Mountain Guidance and Control Conference Breckenridge, Colorado |
|
New methods in solar activity forecasting based on solar dynamo physics using the SODA index.
|
K. H. Schatten |
|
| 2002 |
|
Extends primer vector analysis to formation flying (i.e. a spacecraft formation) such as the MMS mission.
|
L. H. Mailhe,
C. Schiff,
D. Folta
|
Centre National d’Etudes Spatiales Toulouse, France |
|
FreeFlyer implementation of batch least squares and sequential extended Kalman Filter Orbit Determination.
|
T. Tran,
C.Schiff
|
Core Technologies for Space Systems Conference Colorado Springs, Colorado |
|
Derives analytical expressions for outgoing semi-major axis and eccentricity after a lunar gravity assist (i.e. lunar swingby).
|
A. Edery |
|
|
Trajectory design and mission design for spacecraft flying in a tetrahedron formation.
|
J.J. Guzman,
C. Schiff
|
AIAA/AAS Astrodynamics Specialists Conference Monterey, California |
|
Mission design and L2 libration point stationkeeping strategy for the MAP mission.
|
D. Rohrbaugh,
C. Schiff
|
AIAA/AAS Astrodynamics Specialists Conference Monterey, California |
|
Close approaches and other impacts of maintenance maneuver failure for a constellation of NASA low earth satellites.
|
P. Demarest |
AIAA/AAS Astrodynamics Specialists Conference Monterey, California |
| 2001 |
|
Flight dynamics mission analysis to maneuver EO-1 spacecraft in close formation with Landsat-7.
|
R. DeFazio,
S. Owens,
S. Good
|
AAS/AIAA Astrodynamics Specialists Conference Quebec City, Quebec, Canada |
|
Mission design of a tetrahedron spacecraft formation of satellites performing a double lunar swingby (gravity assist).
|
A. Edery,
C. Schiff
|
16th International Symposium on Space Flight Dynamics Pasadena, California |
|
Mission analysis and design to phase a constellation of NASA low earth satellites.
|
P. Demarest,
S. Good,
D. Rand
|
16th International Symposium on Space Flight Dynamics Pasadena, California |
|
Mission and orbit dynamics analysis for spacecraft formation flying.
|
S. Hughes,
L. Mailhe
|
IEEE Aerospace Conference Big Sky, Montana |
|
A Kalman Filter for autonomous orbit determination on-board the spacecraft.
|
J. A. Dibble,
M. Nicholson
|
AAS/AIAA Astrodynamics Specialists Conference Quebec City, Quebec, Canada |
|
Mission analysis and design strategies for low earth spacecraft.
|
P. Demarest |
AAS/AIAA Astrodynamics Specialists Conference Quebec City, Quebec, Canada |
|
Orbit mission analysis and mission design for the GPM constellation.
|
C. Schiff,
L. Mailhe
|
16th International Symposium on Space Flight Dynamics Pasadena, California |
|
An agent-based design to automate SOHO ground operations.
|
W. Truszkowski,
N. Netreba,
D. Ginn,
S. Mandutianu
|
14th International FLAIRS Conference Key West, Florida |
| 2000 |
|
Mission analysis and design of spacecraft flying in close formation.
|
L. Mailhe,
C. Schiff,
S. Hughes
|
15th International Symposium on Space Flight Dynamics Biarritz, France |
|
Mission design and ascent plan strategy for the EO-1 spacecraft to fly in close formation with Landsat-7.
|
P. J. Noonan,
S. Good,
R. DeFazio
|
AAS/AIAA Space Flight Mechanics Meeting Clearwater, Florida |
|
Uses FreeFlyer software Monte Carlo analysis to estimate risk probability in orbital parameters.
|
C. Schiff,
S. Good,
D. Rohrbaugh
|
AAS/AIAA Space Flight Mechanics Meeting Clearwater, Florida |
|
Uses FreeFlyer software to automate mission design and optimize maneuvers.
|
P. Noonan,
F. Perkins
|
AAS/AIAA Space Flight Mechanics Meeting Clearwater, Florida |
|
Implementing a ground system to support the TDRS TONS on-board orbit determination system.
|
L. Newman,
P. Noonan,
C. Gramling
|
AAS/AIAA Space Flight Mechanics Meeting Clearwater, Florida |
|
A generalized mission design and analysis of spacecraft formation flying using MATLAB and FreeFlyer software.
|
C. Schiff,
D. Rohrbaugh,
J. Bristow
|
IEEE Aerospace Conference Big Sky, Montana |
|
Automated maneuver planning software tool, AutoCon, is used to automate and validate automated mission design and maneuver planning for spacecraft formation flying.
|
D. Conkey,
G. Dell,
S. Good,
J. Bristow
|
IEEE Aerospace Conference Big Sky, Montana |
|
Discusses Access to Space web site to assist mission planning by providing a searchable database of spacecraft payloads and launch vehicles.
|
J. Leon,
W. Cutlip,
M. Hametz
|
The International Symposium on Optical Science & Technology San Diego, California |
|
Mission design and launch ascent planning to phase with other spacecraft in a NASA low earth constellation of satellites.
|
R. McIntosh,
P. Noonan,
L. Newman
|
AIAA/AAS Astrodynamics Specialist Conference Denver, Colorado |
|
The geometry of coronal and interplanetary magnetic fields.
|
K. H. Schatten |
|
| 1999 |
|
Attitude and orbit control of close spacecraft formations using FreeFlyer software and MATLAB.
|
D. J. Conway,
D. A. Weidow
|
Conference San Diego, California |
|
Mission design and analysis for a tetrahedron spacecraft formation of NASA low earth satellites.
|
M. E. Hametz,
D. J. Conway,
K. Richon
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
|
Describes how the Autocon software tool automates maneuver planning for the formation flying constraints of the E0-1 mission.
|
K. Chapman,
G. Dell,
D. Rosenberg,
J. Bristow
|
Flight Mechanics Symposium Goddard Space Flight Center Greenbelt, Maryland |
| 1998 |
|
Discussion of how FreeFlyer software and Autocon software tools are used to automate spacecraft operations for two NASA missions.
|
G. Dell,
M. E. Hametz,
P. J. Noonan,
L. Newman,
D. Folta,
J. Bristow
|
AAS/AIAA Astrodynamics Specialist Conference, Boston, Massachusettes |
|
Design of a Kalman Filter orbit determination system for SBIRS and compared to GTDS and AGI PODS.
|
D. Conway,
N. Netreba,
J. Bristow
|
|
|
Development of FreeFlyer software to automate flight dynamics spacecraft operations using Fuzzy Logic.
|
D. Conway,
M. Hametz,
J. Bristow,
L. Newman,
D. Folta
|
2nd International Conference on Engineering Design and Automation Maui, Hawaii |
