By Angelo Miele, Aldo Frediani
Complex layout difficulties in Aerospace Engineering, quantity 1: complicated Aerospace structures offers six authoritative lectures at the use of arithmetic within the conceptual layout of assorted varieties of airplane and spacecraft. It covers the subsequent themes: layout of rocket-powered orbital spacecraft (Miele/Mancuso), layout of Moon missions (Miele/Mancuso), layout of Mars missions (Miele/Wang), layout of an experimental information procedure with a point of view flight course exhibit (Sachs), neighboring motor vehicle layout for a two-stage release automobile (Well), and controller layout for a versatile plane (Hanel/Well). this can be a reference e-book of curiosity to engineers and scientists operating in aerospace engineering and similar themes.
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Extra info for Advanced Design Problems in Aerospace Engineering: Volume 1: Advanced Aerospace Systems
Normalized payload weights have been computed and used to assess feasibility. The main results are that: (i) SSSO feasibility does not necessarily imply SSTO feasibility: while SSSO feasibility is guaranteed for all the parameter combinations considered, SSTO feasibility is guaranteed for only certain parameter combinations, which might be beyond the present state of the art. (ii) For the case of uniform structural factor, not only TSTO feasibility is guaranteed for all the parameter combinations considered, but for the same structural factor a TSTO spacecraft is considerably superior to a SSTO spacecraft in terms of payload weight.
Indeed, an attractive TSTO design might be a first-stage structure made of only tanks and a second-stage structure made of engines, tanks, electronics, and so on. 4. Drag Effects. To assess the influence of the aerodynamic configuration on feasibility, a parametric study has been performed. Optimal trajectories have been computed again varying the drag by ± 50% Design of Rocket-Powered Orbital Spacecraft 25 A. Miele and S. Mancuso 26 while keeping the lift unchanged. Namely, the drag and lift of the spacecraft have been embedded into a one-parameter family of the form where is the drag factor.
This result extends to optimal trajectories the theorem of image trajectories formulated by Miele for feasible trajectories in 1960. Key Words. Earth-Moon flight, Moon-Earth flight, Earth-MoonEarth flight, lunar trajectories, optimal trajectories, astrodyamics, optimization. 1. Introduction In 1960, the senior author developed the theorem of image trajectories in Earth-Moon space within the frame of the restricted three-body problem (Ref. 1). For both the 2D case and the 3D case, the theorem states that, if a trajectory is feasible in Earth-Moon space, (i) its image with respect to the Earth-Moon axis is also feasible, provided it is flown in the opposite sense.