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

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.

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

The Journal of the Japan Society of Aeronautical Engineering ◽

10.2322/jjsass1969.46.453 ◽

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

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The Optimal Closed-Loop Terminal Propellant Consumption Control Algorithm for Liquid Propulsion System of Launch Vehicle. Part I

Bulletin of the South Ural State University Ser Computer Technologies Automatic Control & Radioelectronics ◽

10.14529/ctcr190103 ◽

2019 ◽

Vol 19 (1) ◽

pp. 30-39

Author(s):

A.F. Shorikov ◽

V.I. Kalev

Keyword(s):

Control Algorithm ◽

Closed Loop ◽

Launch Vehicle ◽

Propulsion System ◽

Consumption Control ◽

Propellant Consumption

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Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

Kosmičeskaâ tehnika. Raketnoe vooruženie ◽

10.33136/stma2019.01.088 ◽

2019 ◽

Vol 2019 (1) ◽

pp. 88-95

Author(s):

A. V. Golubek ◽

I. M. Filippenko ◽

K. E. Tatarevsky

Keyword(s):

Solid Propellant ◽

Launch Vehicle ◽

Propulsion System ◽

Vehicle Propulsion

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

Engineering Journal Science and Innovation ◽

10.18698/2308-6033-2021-8-2102 ◽

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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