Multi-nozzle thrust matching control of STOVL engine
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Shuwei Pang
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Wenxiang Zhou
Abstract
A multi-nozzle thrust matching control method is proposed in this paper to provide the thrust vector required of lift-fan type short takeoff and vertical landing (STOVL) aircrafts during hover. Attitude-matched thrust commands for each nozzle of STOVL engine are generated based on a six-degree-of-freedom aircraft model. The thrust controller is divided into two blocks according to the coupling analysis. Based on the combination of linear matrix inequality and differential evolution algorithm, a multi-target controller parameters optimization method is proposed to achieve stable disturbance suppression and fast command tracking. Simulations results show that the proposed command generated model is effective and the decoupling control method can effectively suppress the coupling between the loops and realize the matching control of thrust.
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Research ethics: Not applicable.
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Informed consent: Not applicable.
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Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Use of Large Language Models, AI and Machine Learning Tools: None declared.
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Conflict of interest: The authors state no conflict of interest.
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Research funding: This study is supported by Industry-Academia-Research Cooperation Project (HFZL2021CXY007), National Natural Science Foundation of China (52306015), Project funded by China Postdoctoral Science Foundation (2021M701692), Jiangsu Funding Program for Excellent Postdoctoral Talent (2022ZB202), Postgraduate Research & Practice Innovation Program of NUAA (xcxjh20230202).
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Data availability: Not applicable.
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
Artikel in diesem Heft
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
