Thrust measurement and visualization experiment of a multi-cycle single-tube pulse detonation

Ken Matsuoka, Motoki Esumi, Ken Bryan Ikeguchi, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

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

4 Citations (Scopus)

Abstract

We developed a rotary valve for a pulse detonation engine (PDE), and confirmed its basic characteristics and performance by the visualization experiment and the thrust measurement. We visualized a multi-shot of a pulse detonation rocket engine (PDRE) cycle at an operation frequency of 160 Hz by using a high-speed camera (time resolution: 3.33 μsec, space resolution: 0.4 mm), a schlieren method and square cross-section combustor. We confirmed the each process of one cycle of a PDE (propellant filling, detonation wave generation, and burned gas blowdown and purge process) with high time relolution. The DDT distance decreased under the premature ignition condition. With a passage width of 20 mm, the DDT distance decreased by 22% under the premature ignition condition to a minimum value (76 ± 8 mm). The DDT time from spark time reached a minimum value (69 ± 14 μsec) under the condition of a passage width of 10 mm and premature ignition. The detonation initiation time and the DDT distance were represented by the time until the flame expanded toward the tube-axis one-dimensionally from ignition (characteristic time). We also carried out thrust measurement using a single-tube PDRE and double-tube PDRE composed of a circular cross-section combustor and the newly developed valve. In the singletube PDRE system, we obtained a stable time-averaged thrust in a wide range of operation frequency (40 Hz - 160 Hz) and confirmed the increase of specific impulse due to a partialfill effect. At a maximum operation frequency of 159 Hz, we achieved a maximum propellant-based specific impulse of 232 sec and a maximum time-averaged thrust of 71 N. In the double-tube PDRE system, at a operation frequency per one tube of 65 Hz, we achieved a propellant-based specific impulse of 157 sec and a maximum time-averaged thrust of 104 N.

Original languageEnglish
Title of host publication47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011
Publication statusPublished - 2011
Event47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011 - San Diego, CA, United States
Duration: 2011 Jul 312011 Aug 3

Other

Other47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011
CountryUnited States
CitySan Diego, CA
Period11/7/3111/8/3

Fingerprint

Pulse detonation engines
Detonation
Rocket engines
Visualization
Ignition
Propellants
Experiments
Combustors
High speed cameras
Electric sparks

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

Cite this

Matsuoka, K., Esumi, M., Ikeguchi, K. B., Kasahara, J., Matsuo, A., & Funaki, I. (2011). Thrust measurement and visualization experiment of a multi-cycle single-tube pulse detonation. In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011

Thrust measurement and visualization experiment of a multi-cycle single-tube pulse detonation. / Matsuoka, Ken; Esumi, Motoki; Ikeguchi, Ken Bryan; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh.

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011. 2011.

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

Matsuoka, K, Esumi, M, Ikeguchi, KB, Kasahara, J, Matsuo, A & Funaki, I 2011, Thrust measurement and visualization experiment of a multi-cycle single-tube pulse detonation. in 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011, San Diego, CA, United States, 11/7/31.
Matsuoka K, Esumi M, Ikeguchi KB, Kasahara J, Matsuo A, Funaki I. Thrust measurement and visualization experiment of a multi-cycle single-tube pulse detonation. In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011. 2011
Matsuoka, Ken ; Esumi, Motoki ; Ikeguchi, Ken Bryan ; Kasahara, Jiro ; Matsuo, Akiko ; Funaki, Ikkoh. / Thrust measurement and visualization experiment of a multi-cycle single-tube pulse detonation. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011. 2011.
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abstract = "We developed a rotary valve for a pulse detonation engine (PDE), and confirmed its basic characteristics and performance by the visualization experiment and the thrust measurement. We visualized a multi-shot of a pulse detonation rocket engine (PDRE) cycle at an operation frequency of 160 Hz by using a high-speed camera (time resolution: 3.33 μsec, space resolution: 0.4 mm), a schlieren method and square cross-section combustor. We confirmed the each process of one cycle of a PDE (propellant filling, detonation wave generation, and burned gas blowdown and purge process) with high time relolution. The DDT distance decreased under the premature ignition condition. With a passage width of 20 mm, the DDT distance decreased by 22{\%} under the premature ignition condition to a minimum value (76 ± 8 mm). The DDT time from spark time reached a minimum value (69 ± 14 μsec) under the condition of a passage width of 10 mm and premature ignition. The detonation initiation time and the DDT distance were represented by the time until the flame expanded toward the tube-axis one-dimensionally from ignition (characteristic time). We also carried out thrust measurement using a single-tube PDRE and double-tube PDRE composed of a circular cross-section combustor and the newly developed valve. In the singletube PDRE system, we obtained a stable time-averaged thrust in a wide range of operation frequency (40 Hz - 160 Hz) and confirmed the increase of specific impulse due to a partialfill effect. At a maximum operation frequency of 159 Hz, we achieved a maximum propellant-based specific impulse of 232 sec and a maximum time-averaged thrust of 71 N. In the double-tube PDRE system, at a operation frequency per one tube of 65 Hz, we achieved a propellant-based specific impulse of 157 sec and a maximum time-averaged thrust of 104 N.",
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