https://digitalcommons.unl.edu/cgi/viewcontent.cgi?article=1065&context=usafresearch

A review of space robotics technologies for on-orbit servicing

A Treatise on the Analytical Dynamics of Particles and Rigid Bodies: THE GENERAL THEORY OF ORBITS

This paper presents a mathematical framework for discussion of large space structure (LSS) control theory. Within this framework, current trends in LSS control theory and related topics in general control science are surveyed.

Trends in large space structure control theory: Fondest hopes, wildest dreams

Space Vehicle Dynamics and Control, Second Edition

1 Hoffman, W. C, Zvara, J., and Bryson, A. E., Jr., "A Landing Approach Guidance Scheme for Unpowered Lifting Vehicles," Journal of Spacecraft and Rockets, Vol. 7, No. 2, Feb. 1970, pp. 196-202. 2 Duiven, E. M., "Quadratic Cost-Re-Entry Guidance Laws," Internal Memo 2-5482-0100-020, Dec. 1969, Aerospace Group, Boeing Co., Seattle, Wash. 3 Kovatch, G., "Optimal Guidance and Control Synthesis for Maneuverable Lifting Space Vehicles," Transactions of the 9th Symposium on Ballistic Missile and Space Technology, Vol. 1, Air Force Command, San Diego, Calif., 1964, pp. 327-379. 4 Glover, L. A. and Hagan, J. C, "The Motion of Ballistic Missiles," TG1164, July 1971, The Johns Hopkins University, Applied Physics Lab., Baltimore, Md. 5 White, J. S. and Lee, H. Q., "Users Manual for the Variable Dimension Automatic Synthesis Program (VASP)," TM X-2417, Oct. 1971, NASA. 6 Anderson, B. D. O. and Moore, J. B., Linear Optimal Control, Prentice-Hall, Englewood Cliffs, N.J., 1971. 7 Bryson, A. E. and Ho, H. C, Applied Optimal Control, Blaisdell, Waltham, Mass., 1969. 8 Kwakernaak, H. and Si van, R., Linear Optimal Control Systems, Wiley, New York, 1972.

A New Method of Solution of the Eigenvalue Problem for Gyroscopic Systems

We conducted a micro-gravity flight experiment on a space robotic arm, which is a part of the Reconfigurable Brachiating space Robot (RBR) unit arm developed by the authors. We used a 4-d.o.f. arm ...

Micro-gravity experiment of a space robotic arm using parabolic flight

Rotational-Motion-Damper for Capture of an Uncontrolled Floating Satellite

The paper examines the validity of the assumption that certain appendage-distributed (modal) coordinates can be truncated from a system model without unacceptable degradation of fidelity in hybrid coordinate dynamic analysis for attitude control of spacecraft with flexible appendages. Alternative truncation criteria are proposed and their interrelationships defined. Particular attention is given to truncation criteria based on eigenvalues, eigenvectors, and controllability and observability. No definitive resolution of the problem is advanced, and exhaustive study is required to obtain ultimate truncation criteria.

Appendage modal coordinate truncation criteria in hybrid coordinate dynamic analysis

To realize practical orbital servicing missions in the 21/sup st/ century, we have developed a new system concept for an orbital servicing vehicle named Hyper-OSV (Orbital Servicing Vehicle), which has higher speed manipulation capability and larger operation area than OSVs that were proposed in the 1990's. The main feature of Hyper-OSV (HOSV) is the separation of the operation function and the long-term in-orbit surviving functions such as a solar panel and a large communication antenna. This releases HOSV from attitude restrictions and flexible dynamics and provides a large operation area. The second feature of HOSV is the reconfigurable function that allows HOSV to perform various orbital servicing missions. One of the most difficult missions of HOSV is the noncooperative satellite capture. Separation of the operation function and the long-term in-orbit survival functions gives HOSV an agile working ability. Thus, we have proposed a satellite capturing strategy using an agile orbital servicing vehicle like HOSV and have been conducting its feasibility study. This paper outlines Hyper-OSV first, and then presents the satellite capturing strategy using an agile orbital servicing vehicle and feasibility studies of the satellite capturing.

Satellite capturing strategy using agile Orbital Servicing Vehicle, Hyper-OSV

Dynamics of a ball bearing retainer of the reaction wheel is investigated through experimental tests and numerical simulations. Disturbances of normal and abnormal RWs are compared, and then relation between retainer mass imbalances and their dynamics are investigated. As results, a trade-off relation between instability reduction and disturbance reduction is verified and one of the criteria to decide the appropriate mass imbalance is proposed.

Yoshiaki Ohkami

Papers

Micro-gravity experiment of a space robotic arm using parabolic flight

Rotational-Motion-Damper for Capture of an Uncontrolled Floating Satellite

Appendage modal coordinate truncation criteria in hybrid coordinate dynamic analysis

Satellite capturing strategy using agile Orbital Servicing Vehicle, Hyper-OSV

Analysis of Retainer Induced Disturbances of Reaction Wheel