Matrix transformations for spacecraft attitude determination
نویسندگان
چکیده
منابع مشابه
Matrix Transformations for ' Spacecraft Attitude
A common problem for experimental space physicists is the determination of the "attitude matrix" T which transforms vectors between representations in X and Xl coordinate systems according to Vx = TXX' VXI. Solution of this problem using the standard Eulerian angle techniques is in general tedious and circuitous. A straightforward, simple, and efficient solution for the transformation matrix is...
متن کاملPseudo-Linear Attitude Determination of Spinning Spacecraft
This paper presents the overall mathematical model and results from pseudo linear recursive estimators of attitude and rate for a spinning spacecraft. The measurements considered are vector measurements obtained by sun-sensors, fixed head star trackers, horizon sensors, and three axis magnetometers. Two filters are proposed for estimating the attitude as well as the angular rate vector. One fil...
متن کاملSpacecraft attitude determination and control: Quaternion based method
No wonder you activities are, reading will be always needed. It is not only to fulfil the duties that you need to finish in deadline time. Reading will encourage your mind and thoughts. Of course, reading will greatly develop your experiences about everything. Reading spacecraft attitude determination and control quaternion based method is also a way as one of the collective books that gives ma...
متن کاملPassive Attitude Control for Spacecraft
The stability of spacecraft attitude is studied with considering sinusoidal disturbance. A passive attitude controller without angular velocity measurement for spacecraft described by quaternion is designed. The passive controller has no information related to system parameters. So it has robustness to model error and uncertainty of model parameters. The stability of spacecraft attitude control...
متن کاملSpacecraft Attitude Tracking Control
The problem of reorienting a spacecraft in to acquire a moving target is investigated. The spacecraft is modeled as a rigid body with N axisymmetric wheels controlled by axial torques, and the kinematics are represented by Modified Rodriques Parameters. The trajectory, denoted the reference trajectory, is one generated by a virtual spacecraft that is identical to the actual spacecraft. The open...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Planetary and Space Science
سال: 1972
ISSN: 0032-0633
DOI: 10.1016/0032-0633(72)90186-9