Mission adapted preliminary design of solid propellant rockets for space 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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International Reference Guide to Space Launch Systems, Fourth Edition

10.2514/4.475917 ◽

2004 ◽

Cited By ~ 30

Author(s):

Joseph Hopkins Jr. ◽

Joshua Hopkins ◽

Steven Isakowitz

Keyword(s):

Fourth Edition ◽

International Reference ◽

Reference Guide ◽

Space Launch ◽

Launch Systems

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HTHL Space Vehicles: Concepts and Control Problems

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.629.382 ◽

2014 ◽

Vol 629 ◽

pp. 382-387

Author(s):

Alexander Nebylov

Keyword(s):

Control Systems ◽

Ground Effect ◽

Easy Access ◽

Space Vehicles ◽

Space Launch ◽

Design Requirements ◽

Last Stage ◽

Launch Systems ◽

And Control ◽

Aerospace Plane

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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Conceptual stage separation from widebody subsonic carrier aircraft for space access

The Aeronautical Journal ◽

10.1017/s0001924000009970 ◽

2014 ◽

Vol 118 (1209) ◽

pp. 1279-1309 ◽

Cited By ~ 2

Author(s):

U. Mehta ◽

J. Bowles ◽

S. Pandya ◽

J. Melton ◽

L. Huynh ◽

...

Keyword(s):

Trajectory Analysis ◽

Launch Vehicle ◽

Preliminary Design ◽

Interference Effects ◽

Technical Issue ◽

Rocket Propulsion ◽

Stage Separation ◽

Computational Fluid Dynamics Simulations ◽

Launch Systems ◽

Dynamics Simulations

Abstract Stage separation is a critical technical issue for developing two-stage-to-orbit (TSTO) launch systems with widebody carrier aircraft that use air-breathing propulsion and launch vehicle stages that use rocket propulsion. During conceptual design phases, this issue can be addressed with a combination of engineering methods, computational fluid dynamics simulations, and trajectory analysis of the mated system and the launch vehicle after staging. The outcome of such analyses helps to establish the credibility of the proposed TSTO system and formulate a ground-based test programme for the preliminary design phase. This approach is demonstrated with an assessment of stage separation from the shuttle carrier aircraft. Flight conditions are determined for safe mated flight, safe stage separation, and for the launch vehicle as it commences ascending flight. Accurate assessment of aerodynamic forces and moments is critical during staging to account for interference effects from the proximities of the two large vehicles. Interference aerodynamics have a modest impact on the separation conditions and separated flight trajectories, but have a significant impact on the interaction forces.

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A Multiobjective, Multidisciplinary Design Optimization of Solid Propellant Based Space Launch Vehicle

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference ◽

10.2514/6.2013-1464 ◽

2013 ◽

Author(s):

Naeem Zafar

Keyword(s):

Design Optimization ◽

Multidisciplinary Design Optimization ◽

Solid Propellant ◽

Launch Vehicle ◽

Multidisciplinary Design ◽

Space Launch

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Multifidelity Multidisciplinary Design Optimization of Integral Solid Propellant Ramjet Supersonic Cruise Vehicles

International Journal of Aerospace Engineering ◽

10.1155/2019/5192424 ◽

2019 ◽

Vol 2019 ◽

pp. 1-18 ◽

Cited By ~ 1

Author(s):

Xiaojian Sun ◽

Jianquan Ge ◽

Tao Yang ◽

Qiangqiang Xu ◽

Bin Zhang

Keyword(s):

Design Optimization ◽

Multidisciplinary Design Optimization ◽

Solid Propellant ◽

Multidisciplinary Design ◽

Preliminary Design ◽

Flight Trajectory ◽

Traditional Design ◽

Study Results ◽

Optimization Parameters ◽

Different Levels

Integral solid propellant ramjet (ISPR) supersonic cruise vehicles share the characteristic that they are highly integrated configurations. The traditional design of vehicles cannot achieve a balance between computational expense and accuracy. A multifidelity multidisciplinary design optimization (MDO) platform has been developed in this study. The focus of the platform is on ISPR supersonic cruise vehicles. Firstly, codes of discipline with different levels of fidelity (LoF) were established, such as geometry, aerodynamics, radar cross-section calculations, propulsion, mass, and trajectory discipline codes. Secondly, two MDO frameworks were constructed through discipline codes. A low LoF MDO framework is suitable for conceptual design, and a medium LoF MDO framework is suitable for preliminary design. Finally, taking the optimization problem with the minimum overall detection probability of flight trajectory as an example, the low LoF framework first explores the entire design space to achieve the mission requirements, and then, the medium LoF MDO framework accepts the low LoF framework optimization parameters. Hence, the optimization target is reached with more detailed parameters and higher fidelity. Additionally, an example for a solid propellant missile with minimum total mass is tested by the platform. The study results show that the multifidelity MDO framework not only exploits interactions between the disciplines but also improves the accuracy of optimization results and reduces the iteration time.

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