The inertial guidance system used in a satellite launching vehicle basically consists of an onboard guidance computer system and an inertial sensor unit which contains three accelerometers and three gyros. It is necessary for an onboard guidance computer to have functions for computing current position, velocity and attitude of the vehicle, so called navigation computation using outputs from the inertial sensors, and also a function for computing the guidance command to guide the vehicle to an orbit injection point. In this paper a new algorithm for a strapdown inertial guidance system which satisfies the requirements is presented. A high accuracy flight trajectory analysis program for satellite launch vehicles was also developed for the purpose of evaluating the performance of the onboard guidance software and it is combined in the evaluation software system. A summary of the composition and functions of the evaluation system is presented. Evaluation results indicating the degree of navigation accuracy are also shown.
Strapdown Inertial Guidance System: Onboard Software and Its Evaluation
1983
62 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Spacecraft Trajectories & Flight Mechanics , Unmanned Spacecraft , Artificial satellites , Launch vehicles , Inertial guidance , Stabilized platforms , Algorithms , Guidance computers , Spacecraft control , Control theory , Foreign technology , Strapdown guidance
Tactical guidance requirements for strapdown inertial
Tema Archiv | 1977
|Strapdown stellar-inertial guidance system for launch vehicle
Online Contents | 2014
|Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker
British Library Conference Proceedings | 2012
|