Multifunction rocket system development based on advanced hybrid propulsion

Yen Sen Chen, Robert Cheng, Hao Chi Chang, Luke Yang, Bill Wu, Alfred Lai, Jhe Wei Lin, Shih Sin Wei, Tzu Hao Chou, Tsung Lin Chen, Jong Shinn Wu, Ming-Tzu Ho

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Mainly due to its propellant non-mixing feature, hybrid rocket propulsion has been demonstrated to be more advantageous in operation safety as compared to its solid and liquid counterparts. The traditionally moderate Isp output of hybrid rockets has been enhanced to be close to the liquid rocket performance in recent years, particularly with the innovative designs employed in this research by using dual-vortical-flow (DVF) chambers. Based on this new approach and cost saving strategy, a multifunction rocket system is designed with the features of high performance hybrid combustion, trajectory following flight controls, enhanced science experiments, and an advanced payload recovery method. High fidelity numerical modeling design approach and hot-fire experiments are employed to assess the overall performance of the DVF hybrid rocket engines that has roll control capability embedded in the engine design. The present hybrid rocket engine designs consider propellant systems of N 2 O/HTPB, N 2 O/HDPE and H 2 O 2 /HDPE. Pressure-fed system is the baseline for delivering the oxidizer to the combustion chamber while pump-fed system is also considered as a design option, especially for the hydrogen peroxide system. Carbon fiber filament winding pressure tank is incorporated to contain the oxidizer. Pressurant is also employed for better thrust control. To enhance the overall performance and benefits of conducting flight experiments using hybrid rocket, three basic flight trajectory designs are proposed in this study, namely the traditional standard parabolic trajectory, a TASE (Trajectory Augmented Science Experiments) maneuver and a HOOK (Homing Oriented Operation Kernel) maneuver. The TASE maneuver is designed for maximizing the measurement capabilities of the instruments for atmospheric and ionosphere data profiles. The HOOK maneuver is aiming at improving the success in science payload recovery and in reducing the search and recovery efforts. To achieve these goals, a high performance and reliable flight control system is critical, that incorporates the throttling capability of the DVF hybrid rocket engine, which is one of the key development aspects of this study. For the numerical modeling of the internal ballistics of hybrid rocket combustion for flow analysis and design optimization, a multiphysics Navier-Stokes flow solver with finite-rate chemistry, real-fluid properties, turbulence model and radiative transfer model is employed for high resolution computations. This numerical model is also incorporated in analyzing the aerothermodynamics for high-speed ascend and reentry flights. A 6-DOF flight dynamics, navigation and control simulator is employed in assessing the overall performance of the vehicle based on the aerodynamics and propulsion data generated by the flow solver. Results of the numerical analyses are validated by measured data of ground and flight tests.

Original languageEnglish
Title of host publicationSpaceOps 2016 Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104268
DOIs
Publication statusPublished - 2016 Jan 1
Event14th International Conference on Space Operations, SpaceOps 2016 - Daejeon, Korea, Republic of
Duration: 2016 May 162016 May 20

Publication series

NameSpaceOps 2016 Conference

Other

Other14th International Conference on Space Operations, SpaceOps 2016
CountryKorea, Republic of
CityDaejeon
Period16-05-1616-05-20

Fingerprint

hybrid propulsion
Rockets
rockets
Propulsion
hybrid rocket engines
maneuvers
flight
Trajectories
trajectories
Rocket engines
homing
trajectory
feed systems
flight control
engine
oxidizers
recovery
propellants
High density polyethylenes
Propellants

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering
  • Acoustics and Ultrasonics

Cite this

Chen, Y. S., Cheng, R., Chang, H. C., Yang, L., Wu, B., Lai, A., ... Ho, M-T. (2016). Multifunction rocket system development based on advanced hybrid propulsion. In SpaceOps 2016 Conference [AIAA 2016-2586] (SpaceOps 2016 Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2016-2586
Chen, Yen Sen ; Cheng, Robert ; Chang, Hao Chi ; Yang, Luke ; Wu, Bill ; Lai, Alfred ; Lin, Jhe Wei ; Wei, Shih Sin ; Chou, Tzu Hao ; Chen, Tsung Lin ; Wu, Jong Shinn ; Ho, Ming-Tzu. / Multifunction rocket system development based on advanced hybrid propulsion. SpaceOps 2016 Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (SpaceOps 2016 Conference).
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title = "Multifunction rocket system development based on advanced hybrid propulsion",
abstract = "Mainly due to its propellant non-mixing feature, hybrid rocket propulsion has been demonstrated to be more advantageous in operation safety as compared to its solid and liquid counterparts. The traditionally moderate Isp output of hybrid rockets has been enhanced to be close to the liquid rocket performance in recent years, particularly with the innovative designs employed in this research by using dual-vortical-flow (DVF) chambers. Based on this new approach and cost saving strategy, a multifunction rocket system is designed with the features of high performance hybrid combustion, trajectory following flight controls, enhanced science experiments, and an advanced payload recovery method. High fidelity numerical modeling design approach and hot-fire experiments are employed to assess the overall performance of the DVF hybrid rocket engines that has roll control capability embedded in the engine design. The present hybrid rocket engine designs consider propellant systems of N 2 O/HTPB, N 2 O/HDPE and H 2 O 2 /HDPE. Pressure-fed system is the baseline for delivering the oxidizer to the combustion chamber while pump-fed system is also considered as a design option, especially for the hydrogen peroxide system. Carbon fiber filament winding pressure tank is incorporated to contain the oxidizer. Pressurant is also employed for better thrust control. To enhance the overall performance and benefits of conducting flight experiments using hybrid rocket, three basic flight trajectory designs are proposed in this study, namely the traditional standard parabolic trajectory, a TASE (Trajectory Augmented Science Experiments) maneuver and a HOOK (Homing Oriented Operation Kernel) maneuver. The TASE maneuver is designed for maximizing the measurement capabilities of the instruments for atmospheric and ionosphere data profiles. The HOOK maneuver is aiming at improving the success in science payload recovery and in reducing the search and recovery efforts. To achieve these goals, a high performance and reliable flight control system is critical, that incorporates the throttling capability of the DVF hybrid rocket engine, which is one of the key development aspects of this study. For the numerical modeling of the internal ballistics of hybrid rocket combustion for flow analysis and design optimization, a multiphysics Navier-Stokes flow solver with finite-rate chemistry, real-fluid properties, turbulence model and radiative transfer model is employed for high resolution computations. This numerical model is also incorporated in analyzing the aerothermodynamics for high-speed ascend and reentry flights. A 6-DOF flight dynamics, navigation and control simulator is employed in assessing the overall performance of the vehicle based on the aerodynamics and propulsion data generated by the flow solver. Results of the numerical analyses are validated by measured data of ground and flight tests.",
author = "Chen, {Yen Sen} and Robert Cheng and Chang, {Hao Chi} and Luke Yang and Bill Wu and Alfred Lai and Lin, {Jhe Wei} and Wei, {Shih Sin} and Chou, {Tzu Hao} and Chen, {Tsung Lin} and Wu, {Jong Shinn} and Ming-Tzu Ho",
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doi = "10.2514/6.2016-2586",
language = "English",
isbn = "9781624104268",
series = "SpaceOps 2016 Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
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}

Chen, YS, Cheng, R, Chang, HC, Yang, L, Wu, B, Lai, A, Lin, JW, Wei, SS, Chou, TH, Chen, TL, Wu, JS & Ho, M-T 2016, Multifunction rocket system development based on advanced hybrid propulsion. in SpaceOps 2016 Conference., AIAA 2016-2586, SpaceOps 2016 Conference, American Institute of Aeronautics and Astronautics Inc, AIAA, 14th International Conference on Space Operations, SpaceOps 2016, Daejeon, Korea, Republic of, 16-05-16. https://doi.org/10.2514/6.2016-2586

Multifunction rocket system development based on advanced hybrid propulsion. / Chen, Yen Sen; Cheng, Robert; Chang, Hao Chi; Yang, Luke; Wu, Bill; Lai, Alfred; Lin, Jhe Wei; Wei, Shih Sin; Chou, Tzu Hao; Chen, Tsung Lin; Wu, Jong Shinn; Ho, Ming-Tzu.

SpaceOps 2016 Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. AIAA 2016-2586 (SpaceOps 2016 Conference).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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AU - Lin, Jhe Wei

AU - Wei, Shih Sin

AU - Chou, Tzu Hao

AU - Chen, Tsung Lin

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N2 - Mainly due to its propellant non-mixing feature, hybrid rocket propulsion has been demonstrated to be more advantageous in operation safety as compared to its solid and liquid counterparts. The traditionally moderate Isp output of hybrid rockets has been enhanced to be close to the liquid rocket performance in recent years, particularly with the innovative designs employed in this research by using dual-vortical-flow (DVF) chambers. Based on this new approach and cost saving strategy, a multifunction rocket system is designed with the features of high performance hybrid combustion, trajectory following flight controls, enhanced science experiments, and an advanced payload recovery method. High fidelity numerical modeling design approach and hot-fire experiments are employed to assess the overall performance of the DVF hybrid rocket engines that has roll control capability embedded in the engine design. The present hybrid rocket engine designs consider propellant systems of N 2 O/HTPB, N 2 O/HDPE and H 2 O 2 /HDPE. Pressure-fed system is the baseline for delivering the oxidizer to the combustion chamber while pump-fed system is also considered as a design option, especially for the hydrogen peroxide system. Carbon fiber filament winding pressure tank is incorporated to contain the oxidizer. Pressurant is also employed for better thrust control. To enhance the overall performance and benefits of conducting flight experiments using hybrid rocket, three basic flight trajectory designs are proposed in this study, namely the traditional standard parabolic trajectory, a TASE (Trajectory Augmented Science Experiments) maneuver and a HOOK (Homing Oriented Operation Kernel) maneuver. The TASE maneuver is designed for maximizing the measurement capabilities of the instruments for atmospheric and ionosphere data profiles. The HOOK maneuver is aiming at improving the success in science payload recovery and in reducing the search and recovery efforts. To achieve these goals, a high performance and reliable flight control system is critical, that incorporates the throttling capability of the DVF hybrid rocket engine, which is one of the key development aspects of this study. For the numerical modeling of the internal ballistics of hybrid rocket combustion for flow analysis and design optimization, a multiphysics Navier-Stokes flow solver with finite-rate chemistry, real-fluid properties, turbulence model and radiative transfer model is employed for high resolution computations. This numerical model is also incorporated in analyzing the aerothermodynamics for high-speed ascend and reentry flights. A 6-DOF flight dynamics, navigation and control simulator is employed in assessing the overall performance of the vehicle based on the aerodynamics and propulsion data generated by the flow solver. Results of the numerical analyses are validated by measured data of ground and flight tests.

AB - Mainly due to its propellant non-mixing feature, hybrid rocket propulsion has been demonstrated to be more advantageous in operation safety as compared to its solid and liquid counterparts. The traditionally moderate Isp output of hybrid rockets has been enhanced to be close to the liquid rocket performance in recent years, particularly with the innovative designs employed in this research by using dual-vortical-flow (DVF) chambers. Based on this new approach and cost saving strategy, a multifunction rocket system is designed with the features of high performance hybrid combustion, trajectory following flight controls, enhanced science experiments, and an advanced payload recovery method. High fidelity numerical modeling design approach and hot-fire experiments are employed to assess the overall performance of the DVF hybrid rocket engines that has roll control capability embedded in the engine design. The present hybrid rocket engine designs consider propellant systems of N 2 O/HTPB, N 2 O/HDPE and H 2 O 2 /HDPE. Pressure-fed system is the baseline for delivering the oxidizer to the combustion chamber while pump-fed system is also considered as a design option, especially for the hydrogen peroxide system. Carbon fiber filament winding pressure tank is incorporated to contain the oxidizer. Pressurant is also employed for better thrust control. To enhance the overall performance and benefits of conducting flight experiments using hybrid rocket, three basic flight trajectory designs are proposed in this study, namely the traditional standard parabolic trajectory, a TASE (Trajectory Augmented Science Experiments) maneuver and a HOOK (Homing Oriented Operation Kernel) maneuver. The TASE maneuver is designed for maximizing the measurement capabilities of the instruments for atmospheric and ionosphere data profiles. The HOOK maneuver is aiming at improving the success in science payload recovery and in reducing the search and recovery efforts. To achieve these goals, a high performance and reliable flight control system is critical, that incorporates the throttling capability of the DVF hybrid rocket engine, which is one of the key development aspects of this study. For the numerical modeling of the internal ballistics of hybrid rocket combustion for flow analysis and design optimization, a multiphysics Navier-Stokes flow solver with finite-rate chemistry, real-fluid properties, turbulence model and radiative transfer model is employed for high resolution computations. This numerical model is also incorporated in analyzing the aerothermodynamics for high-speed ascend and reentry flights. A 6-DOF flight dynamics, navigation and control simulator is employed in assessing the overall performance of the vehicle based on the aerodynamics and propulsion data generated by the flow solver. Results of the numerical analyses are validated by measured data of ground and flight tests.

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Chen YS, Cheng R, Chang HC, Yang L, Wu B, Lai A et al. Multifunction rocket system development based on advanced hybrid propulsion. In SpaceOps 2016 Conference. American Institute of Aeronautics and Astronautics Inc, AIAA. 2016. AIAA 2016-2586. (SpaceOps 2016 Conference). https://doi.org/10.2514/6.2016-2586