Author: 姜義德Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Integration of GPS Carrier Phase Observables and Gyro Measurements for Attitude Determination
Author: 姜義德Tightly Integrated Attitude Determination Methods for Low-cost Inertial Navigation
Author: Yunchun YangPublisher:
ISBN:
Category : Inertial navigation (Aeronautics)
Languages : en
Pages : 414
Book Description
Interferometric GPS/Micro-Mechanical Gyro Attitude Determination System
Author: Antonio GiustinoPublisher:
ISBN: 9781423556541
Category :
Languages : en
Pages : 126
Book Description
The near future will see a proliferation of small low cost communication and science satellites with modest (Æ0.1-0.5 deg) pointing requirements which will use attitude determination Systems (ADSs) of low power, weight, size and cost. This thesis is a study into the integration issues of such a system, that uses micro-mechanical inertial sensors and an interferometric GPS (IGPS) attitude determining receiver that are tightly coupled using "model based" estimation techniques. The integration issues analyzed include: the effect on performance of limited IGPS use, the effect on performance of various gyro qualities and model accuracies, the inherent robustness to failure of the system and a power consumption analysis for a minimum energy IGPS receiver. It was found that attitude performance varied less than 0.05 degrees (RSS) when the interval between GPS phase measurements was varied from once every second to once every 30 seconds. This justifies the development of a minimum energy receiver to take advantage of the power savings of less frequent GPS measurements. During times of low dynamic model accuracy, the IGPS/MM Gyro ADS was bound by the steady state attitude error of the IGPS which averages a 1 sigma RSS error of about 0.28 degrees within the GPS update range mentioned above. Attitude error also depends on the gyro quality, and various projected system accuracies are given using several gyro error models. Real micro-mechanical gyro data from a prototype gyro was successfully integrated with real GPS phase measurements using an Extended Kalman filter. Failure scenarios and power expenditures were also analyzed using steady state linear covariance analysis as well as a space simulation which uses orbital parameters of a telecommunication satellite constellation. Total power expenditure of 200 mWatts can be achieved for this system and still fulfill mission requirements.
Using GPS Carrier Phase Observables on Direction Finding and Attitude Determination
Author: 彭新民An Innovative Attitude Determination Using GPS Carrier Phase Triple Difference Measurements
Author: Chi-Chang J. HoRobust GPS Attitude Determination for Spacecraft
Author: John Carl AdamsAn Integrated GPS Attitude Determination System for Small Satellites
Author: Bruce Carl ChesleyPublisher:
ISBN:
Category : Artificial satellites
Languages : en
Pages : 354
Book Description
New Estimation Methods for Attitude Determination Using GPS Carrier Phase Measurements
Author: Yong LiTightly Coupled GPS-Gyro Integration for Spacecraft Attitude Determination
Author: Varun PuriPublisher:
ISBN: 9781423581420
Category :
Languages : en
Pages : 201
Book Description
A Global Positioning System (GPS) based attitude determination system has never been used as the primary source of attitude information for a spacecraft application. The fundamental reason for this is that a spacecraft attitude determination system must achieve fast attitude acquisition and near perfect solution reliability. Existing GPS based attitude systems cannot meet these requirements, so GPS has only been used as a secondary sensor for spacecraft missions. In this thesis, an attitude determination system is developed which meets spacecraft performance requirements using GPS as the primary source of attitude information. System hardware includes a multiple antenna GPS receiver and a low cost three axis gyro assembly. The attitude determination software consists of an integer ambiguity solution algorithm, an Extended Kalman Filter and an integrity monitoring architecture to improve robustness of the design. The integer solution algorithm resolves GPS integer ambiguity with no a priori attitude knowledge or external aiding. Processing is streamlined by solving the two-dimensional yaw and pitch problem and the one- dimensional roll problem independently.
Proceedings of ION GPS-94
Author: Institute of Navigation. Satellite Division. International Technical MeetingPublisher:
ISBN:
Category : Artificial satellites in navigation
Languages : en
Pages : 796
Book Description