Application of Control Structure Design Methods to a Jet Engine

Harefors, M.

doi:10.2514/2.4740

Cited by 4 publications

(3 citation statements)

References 14 publications

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“…Some turbojet engines currently in production have yet used singleinput single-output (SISO) controllers when having only fuel flow as the input variable and rotational speed as the output variable can have adequate controllers. For most modern turbojet engines with afterburners and variable geometry compressors operating in varied flight segments, a more complex control using multiple-input multiple-output (MIMO) techniques (12) has to be designed due to the strong interactions. The input variables include the main engine fuel flow and the nozzle area; variable geometry and afterburner fuel flow may also be the input variables in more complex engines.…”

Section: Lumped Parameter Control Problems Of Turbojet and Ramjet Engmentioning

confidence: 99%

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An idea of distributed parameter control for scramjet engines

Cui

Bao

2007

Aeronaut. j.

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Scramjet engines are used under extreme temperatures and with wide range of Mach numbers from 3 to 8 or higher and have shown different control properties from other airbreathing engines. New control problems involving distributed parameter control have been found concerning investigations of the control of scramjet engines whose physical states are spatially interacted and whose governing equations are partial differential equations. The work of this paper is based on the application of distributed parameter control conception to study the control problems of scramjet engines with the aim of achieving the desirable design properties and increasing control reliability. A new control idea based on shape control theory is put forward to realise the distributed parameter control of scramjet engines with the preconditions of proper space dimension and frequency-domain simplification. Simulation results and theoretic analysis for an axisymmetric, wall-injection scramjet engine show the feasibility and validity of the control idea.

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Section: Lumped Parameter Control Problems Of Turbojet and Ramjet Engmentioning

confidence: 99%

“…Complex systems, such as aeronautic engines in aerospace, must be controlled in order to achieve designated missions or operational requirements (1) . Fuel control is one of the key technologies to a successful scramjet engine (2) .…”

Section: Introductionmentioning

confidence: 99%

An idea of distributed parameter control for scramjet engines

Cui

Bao

2007

Aeronaut. j.

View full text Add to dashboard Cite

show abstract

“…For most modern turbojet and ramjet engines with variable geometry control in varied flight segments, a more complex control using multiple-input multiple-output (MIMO) techniques (7) has to be designed due to the strong interactions. The input variables include the main engine fuel flow and the nozzle area; variable geometry and afterburner fuel flow may also be the input variables in more complex engines.…”

Section: Introductionmentioning

confidence: 99%

Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

Tao

Bao

2008

Aeronaut. j.

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A cross-sectional area J objective function k ratio of specific heats M Mach number P pressure S sensitivity T temperature W defined by Equation (20) x position co-ordinate along the axis of the channel Z defined by Equation (24) τ stagnation temperature rise ratio Subscripts 2 isolator entry 3 combustor entry 4 nozzle entry c core flow t total * at the critical point ABSTRACTDual-mode scramjet is one of the candidates for hypersonic flight propulsion system which will be used in wide range of flight Mach numbers from 4 to 12 or higher, wherein dual-mode scramjet should be well designed to be suitable for subsonic/supersonic combustion operation according to the flight conditions. Therefore this system is required to operate in a finite number of operational modes that necessitate robust, stable, and smooth transitions between them by which selective operability of supersonic/subsonic combustion modes and efficient combustor operation in these modes may be realised. A key issue in making mode transition efficient and stable is mode transition control. The major problem in mode transition control is the handling of the various flow and combustion coupling effects of dual-mode scramjet whose physical states are spatially coupled and whose governing equations are partial differential equations. Involving these distributed parameter issues, our basic idea is using the shape control theory to study the control problems of mode transition for dual-mode scramjet with the aim of achieving the desirable design properties and increasing control reliabilities. This specific approach is motivated by the promise of novel techniques in control theory developed in recent years. Concrete control arithmetic of this approach, such as shape control model, sensitivity analysis and gradient-based optimisation procedure, are given in this paper. Simulation results for an axisymmetric, wall-injection dual-mode scramjet show the feasibility and validity of the method.

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Simplified procedure for controlling pressure distribution of a scramjet combustor

Cui

2014

Chinese Journal of Aeronautics

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Scramjet engines are used at extreme temperatures and velocity. New control problems involving distributed parameter control have been found concerning investigations of the control of scramjet engines whose physical states are spatially interacted. Succeeding the existing theoretical studies on the distributed parameter control for scramjet engines, this paper puts forward a simplified distributed parameter control approach for scramjet engines aimed at engineering application. The simplified control procedure uses the classical proportional-integral (PI) compensation to control the target pressure distribution of scramjet engines, which is effective and applicable for practical implements. Simulation results show the validation of the simplified distributed parameter control procedure.

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Application of Control Structure Design Methods to a Jet Engine

Cited by 4 publications

References 14 publications

An idea of distributed parameter control for scramjet engines

An idea of distributed parameter control for scramjet engines

Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

Simplified procedure for controlling pressure distribution of a scramjet combustor

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