Conceptual Design of a Lunar Landing Mission Using Korea Space Launch Vehicle 2

2011 ◽  
Author(s):  
YJ Moon ◽  
Tae Jang ◽  
Chul Park ◽  
Sejin Kwon
Keyword(s):  
Conceptual Design ◽  
Launch Vehicle ◽  
Lunar Landing ◽  
Space Launch

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

2013 ◽  
Vol 6 (1) ◽  
pp. 6-19
Author(s):  
Nickolay Zosimovych
Keyword(s):  
Conceptual Design ◽  
Navigation System ◽  
Technical Problem ◽  
Launch Vehicle ◽  
Guidance System ◽  
Integrated Navigation ◽  
Integrated Navigation System ◽  
Space Launch ◽  
Artificial Earth

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.

An approach for space launch vehicle conceptual design and multi-attribute evaluation

2013 ◽  
Vol 25 (1) ◽  
pp. 65-74 ◽  
Author(s):  
Rizwan Ullah ◽  
De-Qun Zhou ◽  
Peng Zhou ◽  
Mukarrum Hussain ◽  
M. Amjad Sohail
Keyword(s):  
Conceptual Design ◽  
Launch Vehicle ◽  
Space Launch ◽  
Attribute Evaluation

Practical Implications of Integrating Turbomachinery Into the Air Turborocket

2004 ◽  
Author(s):  
Joshua A. Clough ◽  
Mark J. Lewis
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Launch Vehicle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Space Launch ◽  
Practical Implications

The development of new reusable space launch vehicle concepts has lead to the need for more advanced engine cycles. Many two-stage vehicle concepts rely on advanced gas turbine engines that can propel the first stage of the launch vehicle from a runway up to Mach 5 or faster. One prospective engine for these vehicles is the Air Turborocket (ATR). The ATR is an innovative aircraft engine flowpath that is intended to extend the operating range of a conventional gas turbine engine. This is done by moving the turbine out of the core engine flow, alleviating the traditional limit on the turbine inlet temperature. This paper presents the analysis of an ATR engine for a reusable space launch vehicle and some of the practical problems that will be encountered in the development of this engine.

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