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Attitude Maneuvers of a Rigid Spacecraft in a Circular Orbit
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TLDR
In this article, a global model is presented that can be used to study attitude maneuvers of a rigid spacecraft in a circular orbit about a large central body, including gravity gradient effects that arise from the non-uniform gravity field and characterizes the spacecraft attitude with respect to the uniformly rotating local vertical local horizontal coordinate frame.Abstract:
A global model is presented that can be used to study attitude maneuvers of a rigid spacecraft in a circular orbit about a large central body. The model includes gravity gradient effects that arise from the non-uniform gravity field and characterizes the spacecraft attitude with respect to the uniformly rotating local vertical local horizontal coordinate frame. An accurate computational approach for solving a nonlinear boundary value problem is proposed, assuming that control torque impulses can be applied at initiation and at termination of the maneuver. If the terminal attitude condition is relaxed, then an accurate computational approach for solving the minimal impulse optimal control problem is presented. Since the attitude is represented by a rotation matrix, this approach avoids any singularity or ambiguity arising from other attitude representations such as Euler angles or quaternions.read more
Citations
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Journal ArticleDOI
Optimal Attitude Control of a Rigid Body Using Geometrically Exact Computations on SO(3)
TL;DR: In this paper, an efficient and accurate computational approach for a nonconvex optimal attitude control for a rigid body is proposed, which is formulated directly as a discrete time optimization problem using a Lie group variational integrator.
Journal ArticleDOI
The Exact Computation of the Free Rigid Body Motion and Its Use in Splitting Methods
TL;DR: Numerical simulations indicate that various matrix and quaternion representations of the solution of the free rigid body equation which involve Jacobi ellipic functions and elliptic integrals can be favorably applied to the numerical integration of torqued rigid bodies.
Journal ArticleDOI
Efficient time-symmetric simulation of torqued rigid bodies using Jacobi elliptic functions
Elena Celledoni,N. Säfström +1 more
TL;DR: D Dullweber et al. as discussed by the authors decompose the vector field of a free rigid body (FRB) problem into a completely integrable vector field and use a strategy similar to the symplectic splitting method.
Proceedings ArticleDOI
Global Attitude Estimation using Single Direction Measurements
TL;DR: In this paper, a deterministic attitude estimator for a rigid body under an attitude dependent potential is studied using small error assumptions, which requires only a single direction measurement to a known reference point at each measurement instant.
Posted Content
Computational Geometric Optimal Control of Rigid Bodies
TL;DR: In this paper, the optimal control problems for rigid bodies are formulated as discrete-time optimization problems for discrete Lagrangian/Hamiltonian dynamics, to which standard numerical optimization algorithms can be applied.
References
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Book
Space Vehicle Dynamics and Control
TL;DR: Space Vehicle Dynamics and Control, Second Edition as discussed by the authors provides a solid foundation in dynamic modeling, analysis, and control of space vehicles featuring detailed sections covering the fundamentals of controlling orbital, attitude, and structural motions.
Proceedings ArticleDOI
A lie group variational integrator for the attitude dynamics of a rigid body with applications to the 3D pendulum
TL;DR: In this paper, a numerical integrator is derived for a class of models that describe the attitude dynamics of a rigid body in the presence of an attitude dependent potential, and applied to the uncontrolled 3D pendulum, that is a rigid asymmetric body supported at a frictionless pivot acting under the influence of uniform gravity.