Application of a new economic analysis tool to a two-stage-to-orbit RBCC launch vehicle design

AbstractReusable launch vehicles (RLV) currently envisioned incorporate a wide variety of propulsion types. Various propulsion devices have been designed, or are being designed. The Integral-Rocket-Ramjet (IRR) propulsion mainly applies to a tactical missile boost system and few have mentioned this system in RLV design. According to the technological ability of Taiwan and a feasibility study, it shows that the present reusable launch system can exploit the potential benefit of IRR propulsion for the RLV system. A conceptual study of an unmanned two-stage-to-orbit (TSTO) launch vehicle is designed in this paper. The first stage of the vehicle is reusable with IRR engines. The second stage is expendable and rocket powered. The assumed mission is designed to insert a 100kg payload into a low earth circular orbit at various inclination angles. The calculations are made for the case where the TSTO system is used in Taiwan. The fundamentals of launch vehicle design are examined using simplified two-stage performance equations. Launch vehicle design is optimized when the performance and programmatic drivers are balanced. There is an acceptable set of launch and landing sites on islands off the coast of Taiwan.

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Applying Monte Carlo Simulation to Launch Vehicle Design and Requirements Verification

Journal of Spacecraft and Rockets ◽

10.2514/1.52910 ◽

2012 ◽

Vol 49 (1) ◽

pp. 136-144 ◽

Cited By ~ 11

Author(s):

John M. Hanson ◽

Bernard B. Beard

Keyword(s):

Monte Carlo Simulation ◽

Monte Carlo ◽

Launch Vehicle ◽

Vehicle Design ◽

Requirements Verification ◽

Launch Vehicle Design

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Estimating the possibility of designing a small-lift launch vehicle to form satellite constellations

Engineering Journal Science and Innovation ◽

10.18698/2308-6033-2021-2-2055 ◽

2021 ◽

Author(s):

P.A. Kozedra ◽

Yu.A. Matveev ◽

A.A. Pozin ◽

Yu.V. Chikacheva ◽

V.M. Shershakov

Keyword(s):

Circuit Design ◽

Integrated Approach ◽

Launch Vehicle ◽

Vehicle Design ◽

Space System ◽

Satellite Constellations ◽

Information Unit ◽

Launch Vehicle Design ◽

Development Risks ◽

The Cost

The paper estimates the possibility of using the MN-300 meteorological research rocket as the basis for designing a small-lift launch vehicle to form satellite constellations. The paper shows that at present there exist no standard systems of evaluating a project of this type. In order to account for all the meaningful properties of a small-lift launch vehicle to form satellite constellations, we analyse criteria using the initial data available on all the specimens under comparison. We introduced a range of constraints while selecting the criteria, substantiated by upgrading the base option, the logistics of its application and the ultimate goals of the system. While developing the launch system, we also address the problems of possible upgrade in the structural subsystems of the new design by means of circuit design solutions validated during research instrumentation unit development for meteorological research rockets; letting these problems remain unsolved incurs substantial risks to project implementation. We present a non-trivial solution to the problem of increasing the efficiency of existing achievements in research and technology, related to an integrated approach to evaluating the launch vehicle design via operational efficiency of the space constellation by means of minimising the cost of an information unit, decreasing development risks and employing the space system as a whole.

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Hammersley Sampling and Support-Vector-Regression-Driven Launch Vehicle Design

Journal of Spacecraft and Rockets ◽

10.2514/1.22200 ◽

2007 ◽

Vol 44 (5) ◽

pp. 1094-1106 ◽

Cited By ~ 9

Author(s):

Mateen-ud-Din Qazi ◽

He Linshu ◽

Permoon Mateen

Keyword(s):

Support Vector Regression ◽

Launch Vehicle ◽

Support Vector ◽

Vehicle Design ◽

Launch Vehicle Design

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Preliminary study on launch vehicle design: Applications of multidisciplinary design optimization methodologies

Concurrent Engineering ◽

10.1177/1063293x17737131 ◽

2017 ◽

Vol 26 (1) ◽

pp. 93-103 ◽

Cited By ~ 4

Author(s):

Loïc Brevault ◽

Mathieu Balesdent ◽

Sébastien Defoort

Keyword(s):

Design Optimization ◽

Design Process ◽

Concurrent Engineering ◽

Multidisciplinary Design Optimization ◽

Launch Vehicle ◽

Multidisciplinary Design ◽

Vehicle Design ◽

Launch Vehicles ◽

Data Set ◽

Launch Vehicle Design

The design of complex systems such as launch vehicles involves different fields of expertise that are interconnected. To perform multidisciplinary studies, concurrent engineering aims at providing a collaborative environment which often relies on data set exchange. In order to efficiently achieve system-level analyses (uncertainty propagation, sensitivity analysis, optimization, etc.), it is necessary to go beyond data set exchange which limits the capabilities of performance assessments. Multidisciplinary design optimization methodologies is a collection of engineering methodologies to optimize systems modelled as a set of coupled disciplinary analyses and is a key enabler to extend concurrent engineering capabilities. This article is focused on several examples of recent developments of multidisciplinary design optimization methodologies (e.g. multidisciplinary design optimization with transversal decomposition of the design process, multidisciplinary design optimization under uncertainty) with applications to launch vehicle design to illustrate the benefices of taking into account the coupling effects between the different physics all along the design process. These methods enable to manage the complexity of the involved physical phenomena and their interactions in order to generate innovative concepts such as reusable launch vehicles beyond existing solutions.

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