Selecting Design Objectives for an Integrated Guidance System of a Commercial Launch Vehicle with Application of GPS Technologies

Abstract

In this article have been proposed the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies and has been set a technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.

Integrated Guidance System of a Commercial Launch Vehicle

“…Clearly, the first of the above schemes using both GINS and GPS receiver is not acceptable for our task, because here the receiver is not consuming for calibration (adjustment) of GINS during the mission by evaluating the drift component. As a result, in the absence of GPS-data errors of GINS grow at the same rate as in the absence of the receiver [8].…”

“…The Rockwell MAGR scheme uses inertial measurement from the SGS receiver made in carrier tracking loop (Fig. 2) [8].…”

“…Tightly coupled systems use the only "evaluator" (as a rule, the Kalman filter) that uses differences between pseudoranges and/or pseudovelocities, calculated (predicted) by INS and measured by Self-Guided System. Advantages of such a scheme described in next publications [6,8,12]. The disadvantages of closely coupled systems are the following [6,8]:…”

“…Advantages of such a scheme described in next publications [6,8,12]. The disadvantages of closely coupled systems are the following [6,8]:…”

“…Within the framework of this study we shall consider a light launch vehicle which has been jointly developed by the European Space Agency (ESA) and the Italian Space Agency (ASI) since 1998 [8,9]. It is qualified to launch satellites ranging from 300 kg to 2000 kg into low circular polar orbits.…”