Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
-
JianFeng Zhu
Abstract
Based on the trajectory optimization method of the Gauss pseudospectral, an aircraft/engine matching method is established for the turbine-based combined cycle (TBCC) engine. For a horizontal-takeoff hypersonic aircraft designed at Mach 5, a thrust-matching analysis of the TBCC engine is performed, and a rocket is integrated for further optimization design. The results show that the aircraft for boost missions should adopt the TBCC thrust with a takeoff thrust-to-weight ratio of 99.8 % to reduce the acceleration time and fuel consumption. In contrast, due to the low thrust-to-weight ratio of the TBCC engine, a high-thrust TBCC increases the inert weight in the cruise phase. Therefore, the aircraft designed for cruise missions should adopt the takeoff thrust-to-weight ratio of 92.0 %. Introducing a rocket whose maximum thrust is 10 % of the takeoff weight could assist the aircraft in overcoming the problem of the “thrust pinch” during the transonic and mode transition. With the assistance of rockets, the optimal takeoff thrust-to-weight ratio is 65.3 % for cruise aircraft, and the cruise range is increased by 18 %. While for the boost aircraft, adopting an optimal TBCC of 86.8 % takeoff thrust-to-weight ratio, the introduced rocket could reduce the fuel consumption and the TBCC engine weight by 4 %.
Acknowledgments
The team members of the School of Aerospace Engineering of Xiamen University are gratefully acknowledged.
-
Research ethics: All the necessary ethic and capture permits for these procedures and Analysis were provided from Project base learning Course (PBL) at the Egypt- Japan University of Science and Technology (E-JUST), Department of chemical and Petrochemical Engineering under the supervision of Prof. Ahmed H El-Shazly.
-
Author contributions: KS: Conceptualization, Methodology, validation, formal analysis, investigation, data curation, writing-original draft, writing-review & editing. JA: Conceptualization, Methodology, validation, formal analysis, investigation, data curation, writing-original draft, writing-review & editing. AHE-S: Data curation & Supervision and all authors reviewed and commented on successive versions.
-
Competing interests: The authors declare no conflict of interest.
-
Research funding: The authors would like to acknowledge the support of the National Natural Science Foundation of China (No. 52276040 and No. U20A2069), the National Defense Basic Research Program of China (No. JCKY2022110C107), and the Applied Innovation Program of China Aerospace Science and Technology Corporation (No. 6230112011).
-
Data availability: The raw data can be obtained on request from the corresponding author.
References
1. Liu, J, Yuan, H, Ge, N. Design and flow characteristics analysis of mode transition simulator for tandem type TBCC inlet. Acta Aeronautica Astronautica Sinica 2016;37:3675–84. https://doi.org/10.7527/S1000-6893.2016.0103.Search in Google Scholar
2. Hueter, U, McClinton, C, Cook, S. NASA’s advanced space transportation hypersonic program. In: Proceedings of the 11th AIAA/AAAF international conference space planes and hypersonics systems and technologies conference. Orleans, France: AIAA-2002-5175; 2002.Search in Google Scholar
3. Benson, T, Trefny, C, Walker, J. Interactive design tool for turbine based combined cycle engines. In: 33rd joint propulsion conference and exhibit. Seattle, USA: American Institute of Aeronautics and Astronautics; 1997.10.2514/6.1997-3160Search in Google Scholar
4. Javaid, KH, Serghides, VC. Thrust-matching requirements for the conceptual design of hypersonic waverider vehicles. J Aircraft 2005;42:1055–64. https://doi.org/10.2514/1.8729.Search in Google Scholar
5. Haid, DA, Gamble, EJ. Integrated turbine-based combined cycle dynamic simulation model. Presented at the 58th JANNAF (JPM/CS/APS/EPSS/PHHS) propulsion meeting. Arlington, VA; 2011.Search in Google Scholar
6. Zhang, D, Song, W, Chai, Z, Liu, L, Meng, P. Aircraft/engine performance integrated analysis on combined cycle engine. J Aero Power 2017;32:2498–508.Search in Google Scholar
7. Jiang, C, Chang, J. The coupled modeling and characteristics analysis of TBCC propulsion system and aerocraft. M.E. thesis. Harbin Institute of Technology; 2017.Search in Google Scholar
8. Benson, DA, Huntington, GT, Thorvaldsen, TP, Rao, AV. Direct trajectory optimization and costate estimation via an orthogonal collocation method. J Guid Control Dynam 2006;29:1435–40. https://doi.org/10.2514/1.20478.Search in Google Scholar
9. Ross, IM. A roadmap for optimal control: the right way to commute. Ann N Y Acad Sci 2005;1065:210–31. https://doi.org/10.1196/annals.1370.015.Search in Google Scholar PubMed
10. Du, X, Li, H, Shen, H. Skip reentry trajectory optimization based on analysis of path constraints. Acta Aeronautica Astronautica Sinica 2014;35:1265–75. https://doi.org/10.7527/S1000-6893.2014.0025.Search in Google Scholar
11. Bryson, AE, Desai, MN, Hoffman, WC. Energy-state approximation in performance optimization of supersonicaircraft. J Aircraft 1969;6:481–8. https://doi.org/10.2514/3.44093.Search in Google Scholar
12. Parker, JT, Serrani, A, Yurkovich, S, Bolender, MA, Doman, DB. Control-oriented modeling of an air-breathing hypersonic vehicle. J Guid Control Dynam 2007;30:856–69. https://doi.org/10.2514/1.27830.Search in Google Scholar
13. Brock, M. Performance study of two-stage-to-orbit reusable launch vehicle propulsion alternatives. Theses and Dissertations; 2004, 4121.10.2514/6.2004-3903Search in Google Scholar
14. Zheng, J, Chang, J, Yang, S, Hao, X, Yu, D. Trajectory optimization for a TBCC-powered supersonic vehicle with transition thrust pinch. Aero Sci Technol 2019;84:214–22. https://doi.org/10.1016/j.ast.2018.10.026.Search in Google Scholar
15. Darby, CL, Hager, WW, Rao, AV. An Hp-adaptive pseudospectral method for solving optimal control problems. Optim Control Appl Methods 2011;32:476–502. https://doi.org/10.1002/oca.957.Search in Google Scholar
16. Guo, F, Luo, W, Gui, F, Zhu, J, You, Y, Xing, F. Efficiency analysis and integrated design of rocket-augmented turbine-based combined cycle engines with trajectory optimization. Energies 2020;13:2911. https://doi.org/10.3390/en13112911.Search in Google Scholar
17. Li, Y, Jiang, G, Chu, X, Wang, J. Research on TBCC engine size selection and ascent strategy of combined-cycle aircraft. J Astronaut 2018;39:17. https://doi.org/10.3873/j.issn.1000-1328.2018.01.003.Search in Google Scholar
© 2024 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side
Articles in the same Issue
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side
