Engineering topics
Publications and source records attributed to Kane, T. R..
A methodology for producing simulations of the docking of a rigid spacecraft with any unrestrained flexible structure was studied. A detailed algorithm for the simulation of the docking of a rigid body with a nonuniform unrestrained beam was sought. The values acquired during docking by the variables characterizing the motions of the rigid body and the unrestrained beam were sought.
A methodology is presented for simulating a docking process involving a rigid body and an unrestrained nonuniform beam in orbit, and the issues that must be faced in the course of producing any such simulation are discussed. An algorithm is produced for the simulation of motions of the unrestrained structure, which necessitates the use of a structural analysis program for the purpose of constructing modal functions. An impulse problem then is solved in order to discover the changes that take place in certain variables in the course of the docking. This information is utilized to determine the initial values of variables used to characterize postdocking motions of the system under consideration, and an algorithm for simulating these motions is created, in which a structural analysis program is again used to produce modal functions. Finally, an extension of the methodology to the simulation of the docking of a rigid body with more complex orbiting structures is discussed.
An algorithm is developed for producing numerical simulations of large motions of a nonuniform cantilever beam in orbit. Special emphasis is given to the effective formulation of equations of motion and to the use of the finite element method to construct modal functions. Finite element methods are used to generate modal functions in such a way as to permit a particularly harmonious relationship to be established between the disciplines of rigid body dynamics and structural analysis. Sufficient information is provided to enable a reader to create, with relatively little effort, his own simulation program; simulation results are reported, both to provide check cases for other investigators and to illustrate certain important facets of the behavior of flexible spacecraft.
An algorithm is developed for the numerical simulation of large motions of an unrestrained, nonuniform beam in orbit. Explicit provisions are made for the accommodation of general, physically significant initial conditions and for the specification of control forces in practical terms. The evaluation of certain constants that appear in the equations of motion is considered, the finite element method being used for this purpose. The importance of initial conditions in the study of spacecraft motions is stressed.
The solution of problems of attitude dynamics of spacecraft and the influence of gravitational forces and moments is examined. Arguments are presented based on Newton's law of gravitation, and employing the methods of Newtonian (vectorial) mechanics, with minimal recourse to the classical concepts of potential theory. The necessary ideas were developed and relationships were established to permit the representation of gravitational forces and moments exerted on bodies in space by other bodies, both in terms involving the mass distribution properties of the bodies, and in terms of vector operations on those scalar functions classically described as gravitational potential functions.
Information about principal axes and moments of inertia is presented in terms of formulas involving solely quantities which can be expressed in literal form whenever central principal axes can be located by inspection for at least one state of a deformable system composed of particles and rigid bodies. Two illustrative examples are worked out in detail.
A new concept for astronaut maneuvering in space is proposed, and an experimental study undertaken to test this concept is described. The series of experiments performed appear to promise advantages over previously proposed schemes in terms of propellant economy, system weight, reliability, and safety. The simulation tests established the feasibility of the proposed maneuvering concept by showing that test subjects were able to place their bodies sufficiently near the reference position to avoid excessive angular momentum build-up; no difficulties were encountered in selecting self-rotation maneuvers suitable for effecting desired changes in orientation; and the execution of these maneuvers produced predicted reorientations without tiring the test subject significantly.
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Rigid rotating body kinematic equations for use in space flight mechanics
Approximative method for predicting motion of symmetric rigid body subjected to body-fixed force
Planar motion of human being subjected to action of body-fixed force
Consideration of the ability of both animals and humans to perform well-controlled self-rotation maneuvers while falling freely for short periods of time in the neighborhood of the earth's surface. Specifically, an analytical theory dealing with the righting movements of falling cats is constructed, and the validity of this theory is tested by reference to photographs. Pitch, yaw, and roll motions generated by arm and leg motions of humans are studied analytically and, in the case of yaw motions, experimentally.
Gyroscopic control of spin rate or orientation of rigid bodies constrained to rotate about fixed axis
Poisson kinematic equations solution of symmetric gyrostat in viscous medium for free rotor and constant angular speed, using perturbation technique
Two body torque free gyrostat equations of rotational motion, relating rotational, spin and precession angular velocities
Dynamic analysis of cat motion related to self rotation maneuvers of free falling astronaut
Weightless astronaut self rotation by limb maneuvers producing pitch and yaw motion
Weightless astronaut maneuvering device for directional and attitude control feasibility study using two body system equations of motion