A new steering law for redundant control moment gyroscope clusters

Date

2005-10-01

Author

Tekinalp, Ozan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

215
views

0
downloads

A new inverse kinematics algorithm is developed that may provide singularity avoidance or may be used for quick transition through a singularity with small torque errors. To avoid singularities, angular momentum trajectory of the control moment gyro cluster during the maneuver is to be simulated in advance for the calculation of singularity free gimbal histories. The steering law proposed accurately generates the required torques making it suitable to be used in a feedback system. The desired gimbal trajectories are also closely followed as long as the difference between the planned and requested angular momentum histories are close. A numbers of approaches suitable for the spontaneous response of the spacecraft for singularity avoidance or quick transition through singularities are proposed and presented as well. It is also shown that the computational requirements of the new steering law are comparable to the other commonly used steering laws. (c) 2005 Elsevier SAS. All rights reserved.

Subject Keywords

Aerospace Engineering

URI

https://hdl.handle.net/11511/41320

Journal

AEROSPACE SCIENCE AND TECHNOLOGY

DOI

https://doi.org/10.1016/j.ast.2005.06.001

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

NEW FAMILY OF MODAL METHODS FOR CALCULATING EIGENVECTOR DERIVATIVES AKGUN, MA (American Institute of Aeronautics and Astronautics (AIAA), 1994-02-01) A new family of modal methods for the calculation of eigenvector derivatives in non-self-adjoint systems with a singular coefficient matrix is developed. The family contains the modal and modified modal methods as a subset. In the family, the component of the mth eigenvector in the expansion of the derivative of the jth eigenvector is multiplied by various powers of the eigenvalue ratio lambda(i)/lambda(m), thereby accelerating convergence. The family of methods is applied to a self-adjoint example problem,...
Adaptation of a control system to varying missile configurations Ekinci, Özgür; Yavrucuk, İlkay; Department of Aerospace Engineering (2009) Varying missile configurations may create uncertainty for a missile control algorithm developed with linear control theory, for instance the control system performance requirements may not be satisfied anymore. Missile configuration may change during the missile design period due to variations in subsystem locations, subsystem weights and missile geometry. Likewise, burning propellant, deployment of aerodynamic surfaces and wings with varying sweep angle can be considered as in-flight missile configuration ...
Two-dimensional unsteady Navier-Stokes solution method with moving overset grids Tuncer, İsmail Hakkı (American Institute of Aeronautics and Astronautics (AIAA), 1997-03-01) A simple numerical algorithm to localize intergrid boundary points and to interpolate unsteady solution variables across two-dimensional, structured overset grids is presented. Overset grids are allowed to move in time relative to each other. Intergrid boundary points are localized in a triangular stencil on the donor grid by a directional search algorithm. The final parameters of the search algorithm give the interpolation weights at the intergrid boundary point. Numerical results are presented for steady ...
Nonlinear flutter calculations using finite elements in a direct Eulerian-Lagrangian formulation Seber, Guclu; Bendiksen, Oddvar O. (American Institute of Aeronautics and Astronautics (AIAA), 2008-06-01) A fully nonlinear aeroelastic formulation of the direct Eulerian-Lagrangian computational scheme is presented in which both structural and aerodynamic nonlinearities are treated without approximations. The method is direct in the sense that the calculations are done at the finite element level, both in the fluid and structural domains, and the fluid-structure system is time-marched as a single dynamic system using a multistage Runge-Kutta scheme. The exact nonlinear boundary condition at the fluid-structure...
A new modal superposition method for nonlinear vibration analysis of structures using hybrid mode shapes Ferhatoglu, Erhan; Ciğeroğlu, Ender; Özgüven, Hasan Nevzat (Elsevier BV, 2018-07-01) In this paper, a new modal superposition method based on a hybrid mode shape concept is developed for the determination of steady state vibration response of nonlinear structures. The method is developed specifically for systems having nonlinearities where the stiffness of the system may take different limiting values. Stiffness variation of these nonlinear systems enables one to define different linear systems corresponding to each value of the limiting equivalent stiffness. Moreover, the response of the n...

Citation Formats

O. Tekinalp, “A new steering law for redundant control moment gyroscope clusters,” AEROSPACE SCIENCE AND TECHNOLOGY, pp. 626–634, 2005, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/41320.