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5 Level-3 estimate: cargo mass delivered by a two stage vehicle; based on a revised estimate for second stage structural mass fraction During the second stage of the ascent, the single biggest structural component is the external tank that supplies the propellants to the Orbiter’s engines. It can be thought of simply as a very large thin-walled pressurized vessel. 1 Questioning the magnitude of the Level-2 structural mass fraction Our model calculations indicate that once the ﬁrst stage solid propellants have been consumed in the ﬁrst two minutes of ﬂight, the initial mass for the second stage of ﬂight is about 700,000 kg.
To illustrate the process, we developed Quick-Fire case study models for the 747 engine thrust problem, the Space Shuttle launch and cargo calculation problem, and the Hubble Space Telescope sizing problem. We discussed the tradeoﬀ between model complexity and estimation accuracy, and illustrated this issue by working the Shuttle cargo problem at four levels of complexity ranging from a purely empirical rule of thumb estimate to estimates based on two-stage models for the Shuttle launch to orbit derived from the classical Tsiolkovsky rocket equation.
Conﬁguration of the overall Hubble Space Telescope system [14, p. 14]. Sec. 5 Estimating the size of the optical system for the Hubble Space Telescope 29 System requirements for the HST Our primary estimation goals are to calculate the basic optical telescope scales and the optical performance necessary for this unique space telescope to meet the following major resolution and sensitivity system requirements: . High angular resolution—the ability to image ﬁne detail. High sensitivity—the ability to detect very faint objects.