Space launch systems cost estimation as design tool

1994 ◽  
Vol 34 ◽  
pp. 175-181 ◽  
Author(s):  
D.E. Koelle
2014 ◽  
Vol 629 ◽  
pp. 382-387
Author(s):  
Alexander Nebylov

Integrated launch systems that include aerospace plane (ASP) and another heavy winged vehicle (plane or better Wing-in-Ground effect vehicle) as a booster are reviewed. It is shown that WIG-vehicle with a mass of 1500 ton or more is capable to carry ASP with initial mass of 500 ton and landing mass of 60-70 ton. Ekranoplane can provide ASP with the primary speed of Mach 0.5-0.65 in the required direction that allows lowering the design requirements to ASP's wing area and engines. A number of other advantages from the offered transport system are linked to possible use of WIG-vehicle at ASP landing. Heavy WIG-vehicle is unique vehicle for realizing the progressive idea of docking to descending ASP, allowing expanding opportunities of its landing. The problem of ASP horizontal landing without undercarriage by docking with other flying vehicle at the last stage of decent and the requirements to control systems for relative motion control of both vehicles are discussed. The progressive idea of joining space launch technologies with marine technologies is developed. It is especially important for countries with strongly limited areas of land territory but with easy access to the ocean.


2019 ◽  
pp. 38-50
Author(s):  
Виталий Леонидович Ястремский ◽  
Дмитрий Андреевич Попов ◽  
Олег Яковлевич Комаченко ◽  
Александр Владимирович Аксененко ◽  
Дмитрий Сергеевич Калиниченко ◽  
...  

The subject of study is the possibility of creating (generation) of the space launch systems based on perspective Ukrainian cargo aircrafts.The goal of the work is to consider the main aspects of an air launch and determine the keyword parameters of space launch systems. In the process, the following tasks were completed: an analysis of the Ukrainian air fleet cargo aircrafts; determine the transport aircraft which should be used as carrier-aircraft for launching of the integrated launch vehicles; analyzed the possibility of airdrop integrated launch vehicles from the cargo compartment of carrier aircraft; the optimal airdrop scheme was chosen; the restrictions imposed on the integrated launch vehicle during airdrop; the location of integrated launch vehicle and auxiliary systems on board carrier aircraft is considered; the maneuver performed by the carrier aircraft during the airdrop process is considered, which allows to increase the mass of the airdrop cargo; the process of airdrop from the cargo compartment of a carrier aircraft is analyzed in detail; the appearance of three-stage solid-propellant rockets, their layout schemes and mass budget are determined; the injection scheme and energy characteristics of the considered integrated launch vehicles are determined; The methods used are: analytical analysis and methods of system analysis. As a result of the research, the appearance of space launch systems was determined. The concept of integrated launch vehicles included in these complexes is defined. Ballistic calculations were carried out, during which the energy capabilities were determined to injection the payload to low circular orbits with different inclinations and heights, including equatorial, polar and solar-synchronous. Conclusions. Studies have confirmed the possibility of creating space launch systems based on perspective Ukrainian transport aircraft An-178 and An-188. The implementation of the proposed projects will allow Ukraine to ensure independence and high efficiency of launches, both of its own spacecraft and commercial, to occupy its own niche in the market for launching spacecraft.


2016 ◽  
Vol 22 (1(98)) ◽  
pp. 3-14 ◽  
Author(s):  
A.V. Degtyarev ◽  
◽  
O.V. Pylypenko ◽  
V.S. Hudramovich ◽  
V.N. Sirenko ◽  
...  
Keyword(s):  

Author(s):  
Dr. Anton Kolozezny ◽  
Mr. Joerg Behrens ◽  
Dr. Alexey Romashkin ◽  
Prof. Vladimir Vakhnichenko

Author(s):  
Claudio Favi ◽  
Federico Campi ◽  
Marco Mandolini ◽  
Irene Martinelli ◽  
Michele Germani

Abstract Development of product architectures is a fundamental task in the conceptual design of complex products such as axial compressor of gas turbines. The definition of cost-effective architectures results from the introduction of conceptual cost estimation models aiming at the assessment of economical performances of different modules. Conceptual cost estimation means the product cost assessment in conceptual design phase. These models vary based on the technical and geometrical features of the defined product modules as well as to the specific manufacturing processes. The paper aims to describe the approach for early design cost estimation of Axial Compressor modules. The approach includes the design workflow and the required steps to build product architectures driven by cost indicator. The main limitation overtaken by the adoption of the proposed approach is the needs of a design tool able to characterize cost-effective design solution and to guide designer in product definition with the right level of confidence. The axial compressor product has been analyzed to retrieve different architectures and a case study of a rotor disc module is presented to demonstrate the feasibility of the proposed approach in the development of conceptual cost models starting from preliminary design information.


1990 ◽  
Author(s):  
HARRY BERNSTEIN ◽  
DARRYL BRANTING ◽  
LEONARD SCHILB

1993 ◽  
Author(s):  
John L. Leingang ◽  
Louis R. Carreiro ◽  
Lourdes Q. Maurice

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