3 edition of Large-angle slewing maneuvers for flexible spacecraft found in the catalog.
Large-angle slewing maneuvers for flexible spacecraft
by National Aeronautics and Space Administration, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va
Written in English
|Other titles||Large angle slewing maneuvers for flexible spacecraft.|
|Statement||Hon M. Chun and James D. Turner.|
|Series||NASA contractor report -- 4123., NASA contractor report -- NASA CR-4123.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.|
|The Physical Object|
Modeling and Slew-Maneuver Control of a Flexible Spacecraft Jeremy E. Eckhart Embry-Riddle Aeronautical University - Daytona Beach rotational maneuver of flexible spacecraft that is modeled as a rigid body to which flexible appendages such as solar panels or antennae are attached. 5. Dynamics of Flexible Spacecraft. 6. Elements of Optimal Control Theory. 7. Numerical Solution of Two Point Boundary Value Problems. 8. Optimal Maneuvers of Rigid Spacecraft. 9. Optimal Large-Angle Single-Axis Maneuvers of Flexible Spacecraft. Frequency-Shaped Large-Angle Maneuvers of Flexible Spacecraft.
Minimum-Time Eigenaxis Rotation Maneuvers for a Spacecraft With Three Axis Reaction Wheels Haoyu Wang, A Dual-Wheel Multi-Mode Spacecraft Actuator for Near-Minimum-Time Large Angle Slew Maneuvers,” Influence of Stored Angular Momentum on the Modal Characteristics of Spacecraft With Flexible Appendages. J. Appl. Mech (December, ). Integration of mechanism and control for large-angle slew maneuvers of flexible structures. By Meng-Sang Chew. Abstract. A rolling contact noncircular gear system is applied to assist a desired controller in the slewing of a flexible space structure. The varying gear ratio in cooperation with the controller results in lower feedback gains at.
Sun-Gazing Spacecraft Carries Out Never-Before-Tried Slewing Maneuver The fastest path between Point A and Point B is a straight line. Not so fast, says a team of scientists and engineers who recently disproved this commonly accepted notion using a NASA satellite that had not moved more than 15 degrees during its year mission studying the Sun. rotating of the flexible spacecraft and finding an ap propriate method to suppre ss the vibrations. They usually consider each appendages as Euler-Bernoulli beam to simplify the equation of motions. Azadi et. al (Azadi, et al., )studied on three axes slewing maneuver and the vibration of a flexible spacecraft.
Britains naval heritage
Profit and price performance of leading food chains, 1970-74
The gentile sinner, or, Englands brave gentleman characterd in a letter to a friend
Mazhar Husains The Suppression of immoral traffic in women and girls act, 1956
Interim hearing on franchises, Sacramento, California, November 7, 1969.
Ostracoda of the upper Clays Ferry, Kope, and lower Fairview Formations (Middle and Upper Ordovician) at Moffett Road, northern Kentucky
Recipes and menus for resaurant profits.
Long run to freedom
list of British mammals
Canada votes 1791-1891
Sixty years of service: the University of Western Ontario from small beginnings has become one of the great centres of higher education.
Options for combining the Navys and the Coast Guards small combatant programs.
General nonlinear three-axis slewing maneuvers of flexible spacecraft. Under this control scheme, an open-loop rigid body nominal solution is applied to the spacecraft while a perturbation feedback controller reduces the elastic response and causes the system to closely follow the nominal rigid body trajectory.
INTRODUCTION Many authors have considered the problem of large- angle rapid maneuvers of flexible spacecraft[I-5].
The direct solution of the open-loop two-point boundary-value problem (TPBVP) for three-dimen- sional (3-D) slews of flexible spacecraft resulted in numerical problems with rank-deficient matrices as stated by by: 9. Large-angle slewing maneuvers for flexible spacecraft.
Author(s) Chun, Hon Ming. DownloadFull printable version (Mb) Other Contributors. Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. Advisor. Karl Hedrick, Wallace E. Vander Velde and Bruce K.
Walker. Get this from a library. Large-angle slewing maneuvers for flexible spacecraft. [Hon M Chun; United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.]. The perturbation feedback approach is further applied to three-dimensional slewing maneuvers of large flexible spacecraft.
For this problem, the nominal solution is the optimal three-dimensional rigid body slew. The perturbation feedback then limits the deviations from this nominal solution due to the flexible. The authors focus especially upon the large angle nonlinear maneuvers, and also consider large rotational maneuvers of flexible vehicles with simultaneous vibration suppression/arrest.
Each chapter includes a list of references. The book provides much new material which will be of great interest to practising professionals Large-angle slewing maneuvers for flexible spacecraft book advanced graduate Author: John L.
Junkins. The dynamics of slew maneuvers are nonlinear and include the coupling between the rigid orbiter and the flexible appendage. A decentralized control scheme is used to perform a large-angle slew maneuver about an arbitrary axis in space and to suppress the vibrations of the flexible appendage during and after the maneuver.
Optimal Open-Loop Maneuver Profiles for Flexible Spacecraft. R.L. Farrenkopf; Robust Control of Flexible Spacecraft During Large-Angle Attitude Maneuver. Planar, time-optimal, rest-to-rest slewing maneuvers of flexible spacecraft.
GURKIRPAL SINGH. OPTIMAL CONTROL OF LARGE ANGLE ATTITUDE MANEUVERS FOR FLEXIBLE SPACECRAFT R. Longman1 and K. Alf riend Space Systems Division, Naval Research Laboratory, Washington, DC. U.S.A. Abstract. Future satellite projects will require that methods be developed for slewing yery large and very flexible space vehicles through large angles, and simultaneously controlling the.
A dual-wheel multi-mode spacecraft actuator for near-minimum-time large angle slew maneuvers Aerospace Science and Technology, Vol.
12, No. 7 Momentum transfer control of a spacecraft with two wheels by feedback linearization. The primary emphasis herein is upon the most central analytical and numerical methods for determining optimal rotational maneuvers of spacecraft.
The authors focus especially upon the large angle nonlinear maneuvers, and also consider large rotational maneuvers of flexible vehicles with simultaneous vibration suppression/arrest. Kamiya T., Maeda K., Ogura N., Hashimoto T. and Sakai S. Preshaping Profiler for Flexible Spacecraft Rest-to-Rest Maneuvers JAXA-ISAS, 6  Okubo H.
and Kuwamoto S. Integrated Feedback/Feedforward Control of Flexible Spacecraft for Agile Attitude Maneuver and Vibration Suppression 25th International Conference on Adaptive. The control problem of time-optimal, rest-to-rest slewing of a flexible spacecraft through a large angle is consid-ered.
The flexible spacecraft is modeled as a linear, elastic, undamped, nongyroscopic system suitable for analysis of planar rotational maneuvers.
Minimum-time open-loop planar maneuvers are studied. The control histories are found. Some future space missions will require rapid, large angle, 3-D maneuvering of large flexible spacecraft in target acquisition, target tracking, and surveying multi targets, etc. The optimal control problem is studied for the 2-D and 3-D maneuvering (slewing) and vibrational control of large flexible orbiting systems, with the orbiting Spacecraft Control Laboratory Experiment (SCOLE) model as.
Near Real-Time Closed-Loop Optimal Control Feedback for Spacecraft Attitude Maneuvers [C. Mcfarland] on *FREE* shipping on qualifying offers. Optimization of spacecraft attitude maneuvers can significantly reduce attitude control system size and mass.
In this paper, the dynamics and control of arbitrary slew maneuvers of a large flexible spacecraft are developed. The dynamics of slew maneuvers are nonlinear and include the coupling between the rigid orbiter and the flexible appendage. A decentralized control scheme is used to perform a large angle slew maneuver about an arbitrary axis in space and to suppress the vibrations of the flexible.
In certain spacecraft reorientation of the line of sight requires slewing of the whole spacecraft. If the spacecraft is flexible, then the slewing maneuver is likely to cause elastic vibration, as well as perturbations in the maneuvering angular motion.
the latter are. Abstract and Figures The slew-maneuver control problem is studied for a flexible spacecraft consisting of a rigid main body to which a long flexible appendage is attached.
A nonlinear dynamical. Large-angle slewing maneuvers for flexible spacecraft. By Hon Ming Chun. Abstract. by Hon Ming (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, MICROFICHE COPY AVAILABLE IN ARCHIVES AND graphy: leaves axis slew maneuvers of a rigid spacecraft are also pre- sented.
The paper also includes experimental and an- alytical results for Flexible Spacecraft Simulator(FSS) slew maneuvers using classical and modified switching schernes. Rigid Body Case For a rigid body undergoing a single axis slew ma- neuver, the equation of motion is given by.
A fuzzy-neural network sliding mode control (FNNSMC) is proposed for the attitude stabilization of flexible spacecraft during large angle slew maneuver. Th.The paper considers the problem of maneuvering a flexible spacecraft through large angles in finite time.
The basic control problem is divided into two parts. The first part consists of generating.A constraint equation-based control law design for large angle attitude maneuvers of flexible spacecraft is addressed in this paper.
The tip displacement of the flexible spacecraft model is prescribed in the form of a constraint equation. The controller design is attempted in the way that the constraint equation is satisfied throughout the.