Category: Attitude Estimation and Control

Research is being performed for vision-based attitude and position determination for formation flying applications using a newly-developed sensor by Dr. John L. Junkins employing Position Sensing Diodes to determine line-of-sight vectors to optical beacons.

The vision-based navigation (VISNAV) system comprises of an optical sensor of a new kind combined with specific light sources (beacons) in order to achieve a selective or “intelligent” vision. The sensor is made up of a Position Sensing Diode (PSD) placed in the focal plane of a wide angle lens. When the rectangular silicon area of the PSD is illuminated by energy from a beacon focused by the lens, it generates electrical currents in four directions that can be processed with appropriate electronic equipment. While the individual currents depend on the intensity of the light, their imbalances are weakly dependent on the intensity and are almost linearly proportional to the location of the centroid of the light beam in the PSD.

Spacecraft formation flying is an evolving technology with many possible applications, such as long baseline interferometry, stereographic imaging, synthetic apertures, and distinguishing spatial from temporal magnetospheric variations. A significant advantage of distributed spacecraft platforms over a single multifunctional spacecraft is that single point failures can be rectified through replacement of cheaper and smaller spacecraft to maintain mission capability, thus providing a more reliable and robust system. Many missions (in particular interferometry missions) rely on precise relative position and attitude knowledge in order to maintain mission requirements. To date, most research studies into determining relative positions and attitudes between vehicles have involved using the Global Positioning System (GPS), which restricts the spacecraft formation to near-Earth applications. An application of GPS-like technology to a deep space mission has been proposed, but this requires extensive hardware development and is subject to the generic GPS performance-limiting effects, including multipath, geometric dilution of precision, integer ambiguity resolution, and cycle slip. The main objective of the proposed research is to provide a novel, reliable, and autonomous relative navigation and attitude determination system, employing relatively simple electronic circuits with modest digital signal processing (DSP) requirements, and being fully independent of any external systems.

This work is sponsored by NASA-Goddard Space Flight Center. Results from research can be obtained from:

[1] Andrle, M.S., Hyun, B., Crassidis, J.L., and Linares, R., “Deterministic Relative Attitude Determination of Formation Flying Spacecraft,” AIAA/AAS Astrodynamics Specialist Conference, Honolulu, HI, Aug. 2008, AIAA Paper #2008-6934.

[2] Kim, S.-G., Crassidis, J.L., Cheng, Y., Fosbury, A.M., and Junkins, J.L., “Kalman Filtering for Relative Spacecraft Attitude and Position Estimation,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 30, No. 1, Jan.-Feb. 2007, pp. 133-143.

[3] Banas, W.D., and Crassidis, J.L., “Micro-Arcsecond Line-of-Sight Filtered Performance for Spacecraft Formation Flying Paper Number,” AIAA/AAS Astrodynamics Specialist Conference, Keystone, CO, Aug. 2006, AIAA Paper #2006-6530.

[4] Kim, S.-G., Crassidis, J.L., Cheng, Y., Fosbury, A.M., and Junkins, J.L., “Kalman Filtering for Relative Spacecraft Attitude and Position Estimation,” AIAA Guidance, Navigation, and Control Conference, San Francisco, CA, Aug. 2005, AIAA Paper #2005-6087.

[5] Kappagantula, K., and Crassidis, J.L., “Linearizing Assumptions and Control Design for Spacecraft Formation Flying Maneuvers,” 18th International Symposium on Space Flight Dynamics, Munich, Germany, Oct. 2004, ESA SP-548.

[6] Yim, J.R., Crassidis, J.L., and Junkins, J.L., “Autonomous Orbit Navigation of Two Spacecraft System Using Relative Line of Sight Vector Measurements,” AAS Space Flight Mechanics Meeting, Maui, HI, Feb. 2004, AAS Paper #04-257.

[7] Sun, D., and Crassidis, J.L., “Observability Analysis of Six Degree of Freedom State Determination Using Vector Observations,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 25, No. 6, Nov.-Dec. 2002, pp. 1149-1157.

[8] Alonso, R., Du, J.-Y., Hughes, D., Junkins, J.L., and Crassidis, J.L., “Relative Navigation for Formation Flying of Spacecraft,” Proceedings of the Flight Mechanics Symposium, NASA-Goddard Space Flight Center, Greenbelt, MD, June 2001, pp. 115-129.

[9] Crassidis, J.L., Alonso, R., and Junkins, J.L., “Optimal Attitude and Position Determination from Line-of-Sight Measurements,” The Journal of the Astronautical Sciences, Vol. 48, Nos. 2-3, April-Sept. 2000, pp. 391-408.

[10] Yim, J.R., Crassidis, J.L., and Junkins, J.L., “Autonomous Orbit Navigation of Interplanetary Spacecraft,” AIAA Guidance, Navigation, and Control Conference, Denver, CO, Aug. 2000, AIAA Paper #00-3936.

[11] Alonso, R., Crassidis, J.L., and Junkins, J.L., “Vision-Based Relative Navigation for Formation Flying of Spacecraft,” AIAA Guidance, Navigation, and Control Conference, Denver, CO, Aug. 2000, AIAA Paper #00-4439.

Research is being performed to develop improved spacecraft attitude determination and control algorithms. In particular, robust algorithms are being sought that provide attitude information with a minimal complement of attitude sensors. Also, research is being performed to improve the accuracy of existing hardware sensors through software modifications. Some current and past projects include:

• Wilkinson Microwave Anisotropy Probe (WMAP)
• Solar Anomalous and Magnetospheric Particle Explorer (SAMPEX)
• Tropical Rainfall Measuring Mission (TRMM)
• Geostationary Operational Environmental Satellite (GOES)

This work is sponsored by NASA-Goddard Space Flight Center. Results from research can be obtained from:

[1] Crassidis, J.L., Cheng, Y., and Nebelecky, C.K., “Decentralized Attitude Estimation Using a Quaternion Covariance Intersection Approach,” AAS F. Landis Markley Astronautics Symposium, Cambridge, MD, June-July 2008, AAS Paper #2008-284.

[2] Markley, F.L., Cheng, Y., Crassidis, J.L., and Oshman, Y., “Averaging Quaternions,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 30, No. 4, July-Aug. 2007, pp. 1193-1196.

[3] Crassidis, J.L., Markley, F.L., and Cheng, Y., “A Survey of Nonlinear Attitude Estimation Methods,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 30, No. 1, Jan.-Feb. 2007, pp. 12-28.

[4] Kumar, A., and Crassidis, J.L., “Colored-Noise Kalman Filter for Vibration Mitigation of Position/Attitude Estimation Systems,” AIAA Guidance, Navigation, and Control Conference, Hilton Head, SC, Aug. 2007, AIAA Paper #2007-6516.

[5] Lam, Q., and Crassidis, J.L., “Evaluation of a Multiple Model Adaptive Estimation for Space Vehicle’s Enhanced Navigation Solution,” AIAA Guidance, Navigation, and Control Conference, Hilton Head, SC, Aug. 2007, AIAA Paper #2007-6816.

[6] Cole, C.L., and Crassidis, J.L., “Fast Star Pattern Recognition Using Spherical Triangles,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 29, No. 1, Jan.-Feb. 2006, pp. 64-71.

[7] Cheng, Y., Crassidis, J.L., and Markley, F.L., “Attitude Estimation for Large Field-of-View Sensors,” The Journal of the Astronautical Sciences, Vol. 54, Nos. 3-4, July-Dec. 2006, pp. 433-448.

[8] Crassidis, J.L., Lai, K.-L., and Harman, R.R. “Real-Time Attitude-Independent Three-Axis Magnetometer Calibration,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 28, No. 1, Jan.-Feb. 2005, pp. 115-120.

[9] Crassidis, J.L., and Cole, C.L., “Fast Star Pattern Recognition using Spherical Triangles,” AIAA/AAS Astrodynamics Specialist Conference and Exhibit, Providence, RI, Aug. 2004, AIAA Paper #2004-5389.

[10] Cheng, Y., and Crassidis, J.L., “Particle Filtering for Sequential Spacecraft Attitude Estimation,” AIAA Guidance, Navigation, and Control Conference, Providence, RI, Aug. 2004, AIAA Paper #2004-5337.

[11] Crassidis, J.L., and Markley, F.L., “Unscented Filtering for Spacecraft Attitude Estimation,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 26, No. 4, July-Aug. 2003, pp. 536-542.

[12] Crassidis, J.L., Lai, K.-L., and Harman, R.R., “Real-Time Attitude-Independent Three-Axis Magnetometer Calibration,” Flight Mechanics Symposium, NASA-Goddard Space Flight Center, Greenbelt, MD, Oct. 2003, NASA CP-2003-212246.

[13] Lai, K.-L., Crassidis, J.L., and Harman, R.R., “In-Space Spacecraft Alignment Calibration Using the Unscented Filter,” AIAA Guidance, Navigation, and Control Conference, Austin, TX, Aug. 2003, AIAA Paper #2003-5563.

[14] Singla, P., Crassidis, J.L., and Junkins, J.L., “Spacecraft Angular Rate Estimation Algorithms for Star Tracker-Based Attitude Determination,” 13th AAS/AIAA Space Flight Mechanics Meeting, Ponce, Puerto Rico, Feb. 2003, AAS Paper # 03-191.

[15] Sun, D., and Crassidis, J.L., “Observability Analysis of Six Degree of Freedom State Determination Using Vector Observations,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 25, No. 6, Nov.-Dec. 2002, pp. 1149-1157.

[16] Crassidis, J.L., “Angular Velocity Determination Directly from Star Tracker Measurements,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 25, No. 6, Nov.-Dec. 2002, pp. 1165-1168.

[17] Kim, J.-R., and Crassidis, J.L., “Robust Spacecraft Attitude Control Using Model-Error Control Synthesis,” AIAA Guidance, Navigation, and Control Conference, Monterey, CA, Aug. 2002, AIAA Paper #02-4576.

[18] Singla, P., Griffith, D.T., Crassidis, J.L., and Junkins, J.L., “Attitude Determination and Autonomous On-Orbit Calibration of Star Tracker for GIFTS Mission,” AAS/AIAA Space Flight Mechanics Meeting, San Antonio, TX, Jan. 2002, AAS Paper #02-101.

[19] Crassidis, J.L., Alonso, R., and Junkins, J.L., “Optimal Attitude and Position Determination from Line-of-Sight Measurements,” The Journal of the Astronautical Sciences, Vol. 48, Nos. 2-3, April-Sept. 2000, pp. 391-408.

[20] Crassidis, J.L., Vadali, S.R., and Markley, F.L., “Optimal Variable-Structure Control Tracking of Spacecraft Maneuvers,” AIAA Journal of Guidance, Control and Dynamics, Vol. 23, No. 3, May-June 2000, pp. 564-566.

[21] Yim, J.R., Crassidis, J.L., and Junkins, J.L., “Autonomous Orbit Navigation of Interplanetary Spacecraft,” AIAA Guidance, Navigation, and Control Conference, Denver, CO, Aug. 2000, AIAA Paper #00-3936.

[22] Crassidis, J.L., and Markley, F.L., “Nonlinear Predictive Control of Spacecraft,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 20, No. 6, Nov.-Dec. 1997, pp. 1096-1103.

[23] Crassidis, J.L., and Markley, F.L., “A Minimum Model Error Approach for Attitude Estimation,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 20, No. 6, Nov.-Dec. 1997, pp. 1241-1247.

[24] Crassidis, J.L., and Markley, F.L., “Predictive Filtering for Attitude Estimation Without Rate Sensors,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 20, No. 3, May-June 1997, pp. 522-527.

[25] Crassidis, J.L., and Markley, F.L., “A Predictive Attitude Determination Algorithm,” Proceedings of the Flight Mechanics/Estimation Theory Symposium, NASA-Goddard Space Flight Center, Greenbelt, MD, May 1997, pp. 249-263.

[25] Crassidis, J.L., Markley, F.L., Kyle, A.M., and Blackman, K., “Attitude Determination Designs for the GOES Spacecraft,” Proceedings of the SPIE International Symposium on Optical Science, Engineering, and Instrumentation, Denver, CO, Vol. 2812, Aug. 1996, Paper #74.

[27] Crassidis, J.L., and Markley, F.L., “Attitude Estimation Using Modified Rodrigues Parameters,” Proceedings of the Flight Mechanics/Estimation Theory Symposium, NASA-Goddard Space Flight Center, Greenbelt, MD, May 1996, pp. 71-83.

[28] Crassidis, J.L., Andrews, S.F., Markley, F.L., and Ha, K., “Contingency Designs for Attitude Determination of TRMM,” Proceedings of the Flight Mechanics/Estimation Theory Symposium, NASA-Goddard Space Flight Center, Greenbelt, MD, May 1995, pp. 419-433.

Determining the extent and location of leaks on the International Space Station (ISS) is vital to maintain the operational status and safety of the station. The first indication of a leak on the ISS will likely be a drop in internal pressure. However, the gas leaving the station will likely cause a reaction force. Research is being performed with Dr. Srinivas R. Vadali to develop tools to determine approximate locations and sizes of ISS leaks based on measurements from the attitude determination system. The research has two specific goals:

• Determine force and torque inputs from ISS attitude measurements
• Quantify size and location of leaks from the determined forces and torques

The second item may have multiple solutions. Therefore additional information, such as hatch closures, will be incorporated into the overall system tool in order to help reject spurious solutions.

This work was sponsored by United Space Alliance. Results from research can be obtained from:

[1] Kim, J.-W., Crassidis, J.L., Vadali, S.R., and Dershowitz, A.L., “International Space Station Leak Localization Using Attitude Response Data ,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 29, No. 5, Sept.-Oct. 2006, pp. 1041-1050.

[2] Kim, J.-W., Crassidis, J.L., Vadali, S.R., and Dershowitz, A.L., “International Space Station Leak Localization Using Vent Torque Estimation,” 55th International Astronautical Conference, Vancouver, BC, Oct. 2004, IAC-04-A.4.10.

[3] Kim, J.-W., Crassidis, J.L., Vadali, S.R., and Dershowitz, A.L., “International Space Station Leak Localization Using Attitude Disturbance Estimation,” IEEE Aerospace Conference, Big Sky, MT CA, March 2003, IEEEAC Paper #1391.

[4] Kim, J.-W., Crassidis, J.L., Vadali, S.R., and Dershowitz, A.L., “ISS Leak Localization Using Attitude Response,” AIAA Guidance, Navigation, and Control Conference, Montreal, CA, Aug. 2001, AIAA Paper #01-4272.

Research is being performed to develop new and efficient algorithms for attitude determination using Global Positioning System signals. The goal of this research is to develop fully autonomous algorithms that are robust for any initial attitude. Specific issues to be addressed in the research include:

• Provide optimal attitudes even for coplanar baseline configurations
• Guarantee convergence even for poor initial conditions
• Develop computationally efficient algorithms

At the NASA-Johnson Space Center (JSC), in the Navigation Systems & Technology Laboratory (NSTL), work commenced to demonstrate the use of an indoor pseudolite “constellation” to enable relative attitude determination. Pseudolites, which are radio-frequency transmitters that emit signals similar to the GPS transmissions, are a technology that has become increasingly familiar in the past decade. While pseudolites are still a developing technology, which have not yet been demonstrated in an on-orbit space flight experiment, it is perceived that they hold great promise for augmenting the existing GPS satellite-based navigation and attitude determination technology in local-area applications. The goal of this research is to investigate and develop optimal algorithms that can provide fast and reliable relative attitude information of a moving vehicle.

This work is sponsored by NASA-Johnson Space Center. Results from research can be obtained from: Park, K., and Crassidis, J.L., “A Robust GPS Receiver Self Survey Algorithm,” Navigation: Journal of the Institute of Navigation, Vol. 53, No. 4, Winter 2006, pp. 259-268.

[1] Park, K., and Crassidis, J.L., “Attitude Determination Methods Using Pseudolite Signal Phase Measurements,” Navigation: Journal of the Institute of Navigation, Vol. 53, No. 2, Summer 2006, pp. 121-134.

[2] Crassidis, J.L., and Lightsey E.G., “Attitude Determination Using Combined GPS and Three-Axis Magnetometer Data,” Space Technology, Vol. 22, No. 4, 2001, pp. 147-156.

[3] Crassidis, J.L., Lightsey, E.G., and Markley, F.L., “Efficient and Optimal Attitude Determination Using Recursive Global Positioning System Signal Operations,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 22, No. 2, March-April 1999, pp. 193-201.

[4] Crassidis, J.L., Lisano, M., and Lightsey, E.G., “Autonomous Attitude Determination for ISS Applications Using Pseudolite Signals,” Proceedings of the AIAA International Space Station Service Vehicles Conference, Houston, TX, April 1999.

[5] Crassidis, J.L., Markley, F.L., and Lightsey, E.G., “Application of Vectorized Attitude Determination Using Global Positioning System Signals,” Proceedings of the AIAA/AAS Astrodynamics Specialist Conference, Boston, MA, Aug. 1998, AIAA Paper #98-4390.

[6] Crassidis, J.L., and Markley, F.L., “New Algorithm for Attitude Determination Using Global Positioning System Signals,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 20, No. 5, Sept.-Oct. 1997, pp. 891-896.

[7] Crassidis, J.L., Markley, F.L., Lightsey, E.G., and Ketchum, E., “Predictive Attitude Estimation Using Global Positioning System Signals,” Proceedings of the Flight Mechanics/Estimation Theory Symposium, NASA-Goddard Space Flight Center, Greenbelt, MD, May 1997, pp. 107-120.

[8] Lightsey, E.G., Ketchum, E., Flatley, T.W., Crassidis, J.L., Freesland, D., Reiss, K., and Young, D., “Flight Results of GPS Based Attitude Control on the REX II Spacecraft,” ION-GPS-96, Kansas City, MO, Sept. 1996, pp. 1037-1046.

Integer Ambiguity Resolution

Research is being performed at NASA-Johnson Space Center (JSC), in the Navigation Systems & Technology Laboratory (NSTL), to develop optimal algorithms for integer ambiguity resolution using Global Positioning System signals. The goal of this research is to develop fully autonomous algorithms that are attitude independent. Specific issues to be addressed in the research include:

• Sequentially estimate the ambiguities during the vehicle motion
• Provide inherent integrity checks
• Provide optimal attitudes even for coplanar baseline configurations

This work is sponsored by NASA-Johnson Space Center. Results from research can be obtained from:

[1] Lightsey, E.G., and Crassidis, J.L., “Real Time Attitude Independent GPS Integer Ambiguity Resolution,” The Journal of the Astronautical Sciences, Vol. 52, Nos. 1-2, Jan.-June 2004, pp. 251-267.

[2] Lightsey, E.G., and Crassidis, J.L., “Real Time Attitude Independent GPS Integer Ambiguity Resolution,” The John L. Junkins Astrodynamics Conference, College Station, TX, May 2003, AAS Paper #03-266.

[3] Lightsey, E.G., Crassidis, J.L., and Markley, F.L., “Fast Integer Ambiguity Resolution for GPS Attitude Determination,” AIAA Guidance, Navigation, and Control Conference, Portland, OR, Aug. 1999, AIAA Paper #99-3999, pp. 403-412.

[4] Crassidis, J.L., Markley, F.L., and Lightsey, E.G., “Global Positioning System Integer Ambiguity Resolution Without Attitude Knowledge,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 22, No. 2, March-April 1999, pp. 212-218.