Reliability Improvement of Propulsion System in Successful Return-to-Flight of H-2A Launch Vehicle

2006 ◽  
Author(s):  
Iwao Igarashi ◽  
Takashi Nakamura ◽  
Atsutoshi Tamura ◽  
Kimito Yoshikawa ◽  
Youichi Oowada ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Reliability Improvement

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

Activities on Development of H-IIB Launch Vehicle Propulsion System

2007 ◽  
Author(s):  
Yorichika Mihara ◽  
Akihiro Sato ◽  
Iwao Igarashi ◽  
Takanobu kamiya ◽  
Atsutoshi Tamura ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Vehicle Propulsion

scholarly journals Effect of ІІ stage propulsion system shut-down transients on launch vehicle performance capability

2005 ◽  
Vol 11 (1s) ◽  
pp. 21-23
Author(s):  
B.A. Shevchenko ◽  
◽  
E.P. Nazarenko ◽  
О.М. Ivanov ◽  
◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Vehicle Performance ◽  
Performance Capability

Development Status of H-IIB Launch Vehicle Propulsion System

2007 ◽  
Author(s):  
kiyoshi kobayashi ◽  
youichi oowada ◽  
Makoto Arita ◽  
Hiroyuki Nakatsuji ◽  
Akihiro Sato ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Development Status ◽  
Vehicle Propulsion

scholarly journals Solving the problem of minimax closed-loop control of liquid-propellant launch vehicle fuel consumption control

2020 ◽  
Vol 18 (4) ◽  
pp. 129-145
Author(s):  
A. F. Shorikov ◽  
V. I. Kalev
Keyword(s):  
Dynamical System ◽  
Fuel Consumption ◽  
Closed Loop ◽  
Discrete Dynamical System ◽  
Launch Vehicle ◽  
Open Loop ◽  
Propulsion System ◽  
Terminal Control ◽  
Liquid Propellant ◽  
Propellant Consumption

The paper provides mathematical formalization and a method of solving the problem of minimax (guaranteed) closed-loop terminal control of fuel consumption of a liquid-propellant launch vehicle power plant. The initial discrete-continuous nonlinear model of the controlled object is linearized along the given reference phase path and is approximated by a linear discrete-time multistep dynamical system. The approximated system includes the state vector, the control vector and the disturbance vector that defines the error of formation of the approximated model. Taking into account the geometrical constrains of control and disturbance vectors in the approximated system, we formulate the main problem of minimax closed-loop terminal control of propellant consumption of the launch vehicle’s propulsion system. This problem consists in solving a number of auxiliary tasks of minimax open-loop terminal control. To solve each of these tasks we use an instrument of development and analysis of generalized attainability domains of the approximated linear discrete dynamical system. These techniques are implemented by modifying the general recurrent algebraic method. To solve the problems under consideration we propose an approach and an appropriate numerical algorithm that is reduced to the implementation of a finite sequence of only one-step algebraic and optimization operations. The efficiency of the proposed approach to solving the problem under consideration is demonstrated and verified by a computer simulation example. This simulation example consists in controlling the process of propellant consumption for “Soyuz-2.1b” launch vehicle’s third stage propulsion system.

scholarly journals Outline of Liquid Rocket Propulsion System of H-IIA Launch Vehicle.

1998 ◽  
Vol 46 (535) ◽  
pp. 453-457
Author(s):  
Yukio FUKUSHIMA ◽  
Hiroyuki NAKATSUJI ◽  
Ryuuji NAGAO ◽  
Takashi MAEMURA ◽  
Keiichi HASEGAWA
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Rocket Propulsion ◽  
Liquid Rocket Propulsion ◽  
Liquid Rocket

The concept of the auxiliary propulsion system of the III stage of the Soyuz launch vehicle

2021 ◽  
Author(s):  
V.D. Gorokhov ◽  
V.M. Fomin ◽  
V.V. Golubyatnik ◽  
D.A. Scheblykin
Keyword(s):  
Rocket Engine ◽  
Launch Vehicle ◽  
Low Earth Orbit ◽  
Propulsion System ◽  
Low Thrust ◽  
Liquid Propellant ◽  
Preliminary Calculation ◽  
Liquid Propellant Rocket Engine ◽  
Constituent Elements ◽  
Propellant Rocket

The paper introduces a concept of creating an auxiliary propulsion system for the III stage of the Soyuz launch vehicle. The concept is aimed at reducing the cost of launching a payload into low Earth orbit. The study describes the auxiliary propulsion system and its constituent elements and gives the results of a preliminary calculation of the main characteristics of a low-thrust engine. Within the research, we developed a sketch layout of the auxiliary propulsion system integrated into the 14D23 liquid propellant rocket engine and analyzed the mass characteristics of the constituent elements and the greatest contribution to the total mass of the propulsion system. The proposed propulsion system is distinguished by electric drives for the power supply system pumps used instead of the turbine drive. This auxiliary propulsion system, combined with a 14D23 liquid propellant rocket engine, powered by oxygen-naphthyl propellants, is proposed for use in the III stage of the Soyuz-2-1b launch vehicle.

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