defgf60hv
Cholerny Spammer
Joined: 03 Nov 2010
Posts: 886
Read: 0 topics
Location: England
|
 Posted: Thu 19:33, 06 Jan 2011 Post subject: p90x workout schedule Gyro and magnetometer integr |
|
|
,[link widoczny dla zalogowanych]
Gyro and magnetometer integrated attitude and Application Analysis
0) R = V · V (41) K = P / l · H · R (42) P = (I-K'H) · P a (43) 4 4.1 Application of the feasibility of satellite applications Kalman filter using the R axis magnetometer can measure the accuracy of pre-calculation of the ground, onboard software, matrix binding as a constant, Q is also the default from the ground, onboard software as a constant binding,[link widoczny dla zalogowanych], so the whole Kalman filter matrix inversion does not exist for satellite applications. 4.2 star attitude determination based on the application of simulation calculated IGRF geomagnetic field and the real value of the magnetic field there exists a constant bias 10nT, random deviations 100nT, magnetometer measurements often deviation 100nT, measurement noise 100nT, angular rate gyro constant drift 0. 005 (.) / s, random drift of 0.001 (.) / s, the drift over time 0.0001 ((,[link widoczny dla zalogowanych]。)/ s) / h. Attitude determination simulation results shown in Figure 1 and Figure 2, attitude measurement accuracy of about 0.5. , Gyro constant drift and drift over time was estimated. t | Figure 1 general application of a gyro attitude determination accuracy of 10 output lines estimated drift velocity / \there exists a constant deviation 100nT, random deviations 1O0nT, three-axis magnetometer measurement constant bias lO00nT, measurement noise 1000nT, angular rate gyro constant drift 0.005 (.) / s, random drift of 0.001 (.) / s . The initial attitude estimation error 5., attitude determination simulation results shown in Figure 3, attitude determination accuracy of about 2.. 4.4 Analysis of Orbit Determination Error in satellite orbit determination accuracy of calculation of IGRF geomagnetic field applications, the main effect parameters for power ascension of ascending node, orbital inclination i, longitude of ascending node convergence angle, force, i, u of the orbit determination accuracy can generally be 0.07.,[link widoczny dla zalogowanych], simulation results show that, i, \small to be ignored. 27 No. 5 workers PROCEEDINGS: gyro and magnetometer integrated attitude and engineering applications of 47 · £ \ 5 Conclusion Figure 3 Application of rough precision attitude determination accuracy to establish this equation of state based on satellite kinematics, and was designed for applications in satellite and Magnetometer gyro attitude determination algorithm, simulation results show that the precision engineering to 1. So, for in Namibia Star,[link widoczny dla zalogowanych], Star and other minor skin satellite applications.
More articles related to topics：
[link widoczny dla zalogowanych]
[link widoczny dla zalogowanych]
[link widoczny dla zalogowanych]
The post has been approved 0 times
|
|
FAQ
Search
Memberlist
Usergroups
Galleries
Register
Log in to check your private messages
Log in
