About the classification of launch equipment of the space launch systems for the strength standards justification

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.

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Space launch systems cost estimation as design tool

Acta Astronautica ◽

10.1016/0094-5765(94)90255-0 ◽

1994 ◽

Vol 34 ◽

pp. 175-181 ◽

Cited By ~ 1

Author(s):

D.E. Koelle

Keyword(s):

Cost Estimation ◽

Design Tool ◽

Space Launch ◽

Launch Systems

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International reference guide to space launch systems

Choice Reviews Online ◽

10.5860/choice.38-0035 ◽

2000 ◽

Vol 38 (01) ◽

pp. 38-0035-38-0035 ◽

Cited By ~ 1

Keyword(s):

International Reference ◽

Reference Guide ◽

Space Launch ◽

Launch Systems

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Unification of filling station equipment intented for filling of spacecraft, upper stages and low-thrust propulsion systems of space launch systems

Technology audit and production reserves ◽

10.15587/2312-8372.2017.91689 ◽

2017 ◽

Vol 1 (1(33)) ◽

pp. 4-9

Author(s):

Геннадий Леонидович Поздеев ◽

Виктор Петрович Фролов

Keyword(s):

Low Thrust ◽

Propulsion Systems ◽

Filling Station ◽

Space Launch ◽

Launch Systems

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ИССЛЕДОВАНИЕ ВОЗМОЖНОСТИ СОЗДАНИЯ АВИАЦИОННО-КОСМИЧЕСКОГО РАКЕТНОГО КОМПЛЕКСА НА БАЗЕ ПЕРСПЕКТИВНЫХ УКРАИНСКИХ ТРАНСПОРТНЫХ САМОЛЕТОВ

Aerospace technic and technology ◽

10.32620/aktt.2019.5.05 ◽

2019 ◽

pp. 38-50

Author(s):

Виталий Леонидович Ястремский ◽

Дмитрий Андреевич Попов ◽

Олег Яковлевич Комаченко ◽

Александр Владимирович Аксененко ◽

Дмитрий Сергеевич Калиниченко ◽

...

Keyword(s):

Solid Propellant ◽

System Analysis ◽

High Efficiency ◽

Launch Vehicle ◽

Launch Vehicles ◽

Energy Characteristics ◽

Transport Aircraft ◽

Space Launch ◽

The Subject ◽

Launch Systems

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.

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