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We present the discrete algorithms for filtering measurements, in-flight calibration and alignment of an astroinertial system for attitude and angular rate determination of a maneuvering land-survey satellite.
Determination of relative position between two objects is an important task during space activities like automated space rendezvous and docking. The relative orientation measured in terms of six Degree of Freedom (6DOF) vector. The six Degree of Freedom vector can be determined by using a sensor system consists of a passive reflective pattern on the target vehicle, imaging this reflective pattern...
In this study an integrated Algebraic method/ Extended Kalman fitler (EKF) attitude determination system is presented, in which the 2-vector and EKF algorithms are combined to estimate the attitude angles and angular velocities. As a reference directions for algebraic method, the unit vectors toward the Sun and Earth's Magnetic Field are used. The Euler angles produced 2-vector algorithm and their...
Two different methods are compared to estimate attitude in this study. These methods are Single Value Decomposition (SVD) solving Wahba's problem optimally and Algebraic Method using two vector measurements. Selected spacecraft data is used for orbit propagation. Magnetometer and Sun sensor are chosen for this work, also the mathematical models and the measurement models of these sensors are used...
This paper discusses the design and verification of the operating procedure of the Attitude Determination and Control Subsystem (ADCS) of PHOENIX nanosatellite. As one of the satellites which joins the QB50 project, the main objective of PHOENIX is to perform in-situ measurements in the lower thermosphere. In order to meet the mission requirements, the attitude control system is required to stabilize...
The technology of high precision attitude determination with low precision sensors based on data fusion is the objective requirement of modern small satellite. This paper presents a new attitude determination algorithm termed Pre-process EKF(PP-EKF) based on preprocess of sensor data. It can enhance the overall modeling accuracy by using the quadratic penalty function to correct the kinematics model...
A low cost integrated navigation system based on cascaded coupled architecture was developed for mini autonomous helicopter. A novel linear attitude fusion algorithm was introduced to fuse gyros' output with accelerometers' gravity observation and magnetometers' magnetic observation, and the estimation errors were proven to be bounded. By considering the measurement delay of GPS, the velocity and...
Based on traditional satellite attitude determination simulator, the paper studies a state estimation method to determine the satellite attitude, which is simulated in computer. This simulator is mainly composed by two parts: sensor model library and determination algorithm library. The sensor model library contains several sensor models which are implemented in C/C++, so as the determination algorithms...
A new method for orbit and attitude determination of satellite simultaneously based on three-axis-magnetometer (TAM) and gyro data is presented, which is a breakthrough in traditional pattern of treating orbit and attitude of satellite separately. Considering of the nonlinear system, a modified unscented Kalman filter is developed. The magnetic field components are used to update as measurement and...
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