Integrated Guidance System of a Commercial Launch Vehicle

Abstract

This paper proposes a concept of integrated on-board navigation systems for commercial launch vehicles in the context of the current task, and provided mathematical models of its elements for different variants of designing structure and composition. Has been set and simulated the technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to insert small artificial Earth satellites into low and medium circular orbits with application of GPS technologies.

Апріорний Аналіз Точності Виведення Ракети Космічного Призначення На Екваторіальну Орбіту

“…The article [23] is devoted to the development of a conceptual design of a navigation system for LV with SINS and SNS, which displays small-sized satellites in low and medium Earth orbits. The analysis of possible motion models of LV and navigation measurements is carried out, the key potential difficulties of their creation are identified and the ways to resolve them using object-oriented software are identified.…”

Smallsat Rational Design

“…• If impulse control of jet engines takes place, the consumption of the propellant, necessary for Smallsat orientation depends on the accuracy of its orientation, disturbing moment, specific thrust and control engine arms, the minimum impulse value and Smallsat moments of inertia [10][11][12][13];…”