scholarly journals Development Status and Plan of the High Performance Upper Stage Engine for a GEO KSLV

2018 ◽  
Vol 22 (2) ◽  
pp. 125-130
Author(s):  
Byungil Yu ◽  
Kwang-Jin Lee ◽  
Seongphil Woo ◽  
Ji-Hyuk Im ◽  
Younseok So ◽  
...  
Author(s):  
Boris A. Sokolov ◽  
Nikolay N. Tupitsyn

The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.


Author(s):  
P. Alliot ◽  
J.-F. Delange ◽  
V. De Korver ◽  
J.-M. Sannino ◽  
A. Lekeux ◽  
...  

The intent of this publication is to provide an overview of the development of the VINCI® engine over the period 2014–2015. The VINCI® engine is an upper stage, cryogenic expander cycle engine. It combines the required features of this cycle, i. e., high performance chamber cooling and high performance hydrogen turbopump, with proven design concepts based on the accumulated experience from previous European cryogenic engines such as the HM7 and the VULCAIN®. In addition, its high performance and reliability, its restart and throttle capability offer potential applications on various future launcher upper stages as well as orbital spacecraft. At the end of 2014, the VINCI® successfully passed the Critical Design Review that was held after the major subsystem (combustion chamber, fuel and oxygen turbopump) had passed their own Critical Design Review all along the second half of 2014. In December, a Ministerial Conference at government level gave priority to the Ariane 6 program as Europe future launcher. In the framework of this decision, VINCI® was confirmed as the engine to equip Ariane 6 cryogenic upper stage engine. This publication shows how the VINCI development is progressing toward qualification, and also how the requirements of the new Ariane 6 configuration taken into account, i. e., offering new opportunities to the launch system and managing the new constraints. Moreover, the authors capitalize on the development already achieved for the evolution of Ariane 5. In parallel to completing the engine development and qualification, the configuration and the equipment of the propulsive system for Ariane 6 such as the components of the pressurization and helium command systems, board to ground coupling equipment, are being defined.


Author(s):  
Mojtaba Alavipour ◽  
Amir A Nikkhah ◽  
Jafar Roshanian

In this paper, the problem of minimum time multiple-burn optimization of an upper stage with a limited thrust, and engine restart capability for satellite injection into geostationary orbit are considered. The goals are to find thrust vector angle, times of the engine firings, and optimal duration of active phases of the upper stage to minimize fuel consumption and meet the desired boundary conditions. Various flight sequences with multiple burns, from two burns up to six burns, are considered. Also, the optimal trajectory for each sequence is derived. To solve the multi-point boundary value problem, an improved indirect shooting method with high performance is presented and used for an optimal solution. All in all, this novel method presented for multi-burn problem, not only with a very good accuracy, but also with a very fast convergence to the desired end conditions.


Author(s):  
Arif Karabeyoglu ◽  
Jose Stevens ◽  
Dmitriy Geyzel ◽  
Brian Cantwell ◽  
Dave Micheletti
Keyword(s):  

1999 ◽  
Author(s):  
S. Peery ◽  
R. Branam ◽  
R. Long ◽  
R. Grabowski ◽  
A. Minick

Author(s):  
Stefan Kraft ◽  
M. Collon ◽  
R. Günther ◽  
R. Partapsing ◽  
M. Beijersbergen ◽  
...  

2017 ◽  
Vol 2017 (1) ◽  
pp. 000715-000720 ◽  
Author(s):  
Masahiro Kyozuka ◽  
Takahiko Kiso ◽  
Hiroki Toyazaki ◽  
Koichi Tanaka ◽  
Tetsuya Koyama

Abstract As mobility products, such as smart phones, tablets and wearable devices, continue on the paths of both miniaturization and high performance, components and packaging are likewise driven to become smaller and thinner. In mobile devices, a thinner package is required, especially for the Application Processor and memory combination. The Package-on-Package structure can achieve module thinness by embedding a die (or dies) into a package and is thus attractive for reducing the height of an AP. The Die-Embedded and RDL structure has been in development as a package corresponding to POP structure. This structure has two characteristics of manufacturing method, based on the substrate manufacturing process. One is the RDL-first process, whereby the RDL is manufactured before die attachment. This process decreases the die loss from defects in the RDL formation. The other method is to manufacture the packages in panel form instead of wafer form. The key features of this structure are panel-form manufacturing and via connection between the substrate and the top-RDL. In IMAPS 2016, the Die Embedded and RDL structure on i-THOP®, which was used as the substrate was reported. The die-to-die inter connection was fabricated on i-THOP® for a 2.1D application. Both the die attachment and the RDL formation were successfully performed. The reliability tests proceeded. The results indicated that the i-THOP® with the Die Embedded and RDL structure can be applied to packaging of AP in mobile devices. The next challenge is to make a smaller package using the Die Embedded and RDL structure. To decrease the package area, a finer-pitch via connection that was less than the design rule of 200μm was evaluated. For reduction of package thickness, a thinner substrate, approximately 160μm thickness, was applied. The new test sample with these improvements was designed and proceeded to evaluation. The dimensions of the sample are 15 × 15 mm2 size and 340μm thickness (without solder ball), a 100μm-thick die was embedded and a one-layer of RDL was formed on the die. In this development, the warpage of the thin substrate after die attachment might be large, so there is an issue of package warpage and the handling of a thin substrate. In this report, results of low warpage structure design and development status of fine via connection formation are described.


1999 ◽  
Author(s):  
C. Erickson ◽  
S. Pinkowski ◽  
M. Anderson ◽  
H. Linner ◽  
G. Obermaier ◽  
...  

Sign in / Sign up

Export Citation Format

Share Document