scholarly journals Analysis of the operation of the control jet engines of the Cyclone-4M launch vehicle upper stage at sustainer engine startups and shutdowns

2020 ◽  
Vol 2 (2) ◽  
pp. 22-35
Author(s):  
V.I. Tymoshenko ◽  
◽  
Yu.V. Knyshenko ◽  
V.M. Durachenko ◽  
S.O. Asmolovskyi ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Jet Engines ◽  
Upper Stage

Upper Stage Propulsion System for H-IIA Launch Vehicle

2002 ◽  
Author(s):  
Masumi Fujita ◽  
Hiroshi Aoki ◽  
Toshihiko Nakagawa ◽  
Tatsuru Tokunaga ◽  
Masaaki Yasui ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Upper Stage

Thermal-Fluidic Numerical Analysis for the Development of Heat Exchanger in the Propellant Tank Pressurization System of KSLV-II Upper Stage

2015 ◽  
Author(s):  
Sun-Kyung Lee ◽  
Sang Yeop Han ◽  
Dong-Soon Shin ◽  
R. Ray Taghavi
Keyword(s):  
Heat Exchanger ◽  
Numerical Analysis ◽  
Coming Out ◽  
Launch Vehicle ◽  
Liquid Oxygen ◽  
Outlet Temperature ◽  
Liquid Propellant ◽  
Gaseous State ◽  
Technical Requirements ◽  
Upper Stage

KSLV-II (Korea Space Launch Vehicle - II) launch vehicle is a three staged satellite launch vehicle using a liquid propellant propulsion system in all three stages. It will deliver 1,500 kg satellite to Sun Synchronous Orbit (SSO, 700 km, 98.2°) or 2,600 kg satellite to Low Earth Orbit (LEO, 300 km, 80.3°). Propellants for KSLV-II are kerosene as a fuel and liquid oxygen as an oxidizer for propelling. Those fuel and oxidizer are stored in on-board tanks separately. To run a liquid propellant rocket engine on ground or in flight, those propellants should be supplied to LRE’s using so-called Propellant Pressurizing Sub-system, which makes propellants be pressurized in tanks using pressurant. A pressurant for PPSS of KSLV-II is helium, which is stored in tanks located in an oxidizer tank. The stored He is under cryogenic condition (50 K) as gaseous state. Such He is heated and expanded through heat exchanger, which is using a combustion gas coming out from gas generator for turbo-pump as an energy source, to be used as pressurant. This paper contains the results of performance analysis and thermal-fluidic numerical analysis to develop the above-mentioned heat exchanger for KSLV-II upper stage (the 2nd stage). The technical requirements for such heat exchanger are as follows: pressurant mass flow rate for oxidizer tank - 0.127 kg/sec; and for fuel tank - 0.043 kg/sec. The outlet temperature of He from heat exchanger is 550±10 K.

On the feasibility of developing a single-stage acceleration/deceleration unit based on the oxygen-hydrocarbon engine 11D58M for a super-heavy launch vehicle

2021 ◽  
pp. 62-75
Author(s):  
Boris A. SOKOLOV ◽  
Nikolay N. TUPITSYN ◽  
Evgeniy N. TUMANIN ◽  
Igor A. KRYUKOV ◽  
Andrey V. KISELEV ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Launch Vehicle ◽  
Single Stage ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
Gravity Assist ◽  
Upper Stage ◽  
Gravity Assist Maneuver ◽  
Lunar Gravity Assist ◽  
Propellant Rocket

The paper presents results of unsolicited exploratory design studies done by the authors into the feasibility of developing for a super-heavy launch vehicle a single-stage oxygen-hydrocarbon acceleration/deceleration unit (ADU) with two liquid-propellant rocket engines 11D58M developed by RSC Energia, intended for insertion of manned spacecraft into lunar orbit, as well as for insertion of super-heavy spacecraft into geostationary orbit (including the orbital module high-apogee transfer profile using lunar gravity assist maneuver). It demonstrates that the single-stage ADU will have a number of important advantages over both a single-stage oxygen-hydrogen ADU and a functionally similar two-stage acceleration/deceleration system of an orbital module in the form of a tandem stack of an oxygen-hydrogen acceleration stage and correction and braking stage. To assure the start-ups of the main liquid propulsion system of the ADU, it proposes a new method for inertial propellant component phase separation in the tanks in zero-gravity environment using a pre-startup pre-programmed ullage separation turn maneuver of the orbital unit about its transverse axis of inertia. Key words: Integrated launch vehicle, launch vehicle, orbital module, upper stage, orbital transfer vehicle, acceleration/deceleration unit, ullage maneuver, liquid-propellant rocket engine.

Problems of development of controlling liquid jet system, which is powered from lines of a booster of the launch vehicle upper stage

2016 ◽  
Vol 22 (1(98)) ◽  
pp. 20-35 ◽  
Author(s):  
V.I. Timoshenko ◽  
◽  
Yu.V. Knyshenko ◽  
V.M. Durachenko ◽  
V.M. Anishchenko ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Liquid Jet ◽  
Upper Stage

Upper stage options for reusable launch vehicle “pop-up” missions

1997 ◽  
Author(s):  
James B. Eckmann ◽  
Roy B. Cotta ◽  
Leo W. Matuszak ◽  
David R. Perkins
Keyword(s):  
Launch Vehicle ◽  
Reusable Launch Vehicle ◽  
Upper Stage
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