研究者データベース

KAMPS LANDON THOMAS(ケンプス ランドン トマス)
工学研究院 機械・宇宙航空工学部門 宇宙航空システム
特任助教

基本情報

所属

  • 工学研究院 機械・宇宙航空工学部門 宇宙航空システム

職名

  • 特任助教

学位

  • 博士(北海道大学)

ホームページURL

J-Global ID

研究キーワード

  • Nozzle Erosion   Space Exploration   Hybrid Rockets   

研究分野

  • ものづくり技術(機械・電気電子・化学工学) / 機械要素、トライボロジー / ハイブリッドロケットシステム設計および性能予測
  • ものづくり技術(機械・電気電子・化学工学) / 設計工学 / ハイブリッドロケットシステム設計および性能予測
  • ものづくり技術(機械・電気電子・化学工学) / 熱工学 / 熱化学的黒鉛浸食
  • ものづくり技術(機械・電気電子・化学工学) / 流体工学 / ロケット推進剤流量システム

職歴

  • 2017年10月 - 2019年09月 北海道大学 宇宙環境システム工学研究室 特別研究員(DC1)
  • 2013年06月 - 2014年10月 米陸軍 第502情報大隊・本部中隊 服中隊長
  • 2010年11月 - 2013年05月 米陸軍 第502情報中隊・第A中隊 中隊長

学歴

  • 2015年10月 - 2017年09月   北海道大学   機械宇宙工学講座   修士課程
  •         -   ニューヨーク州立大学バッファロー交   航空宇宙工学講座   学部
  •         -   北海道大学   機械宇宙工学講座   博士課程

研究活動情報

論文

  • Stabilized Combustion of Circular Fuel Duct with Liquid Oxygen
    Ayumu Tsuji, Yuji Saito, Masashi Wakita, Harunori Nagata
    Proceedings of the Combustion Institute 2020年07月 [査読有り][通常論文]
  • Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using O2/HDPE
    ケンプス トマス ランドン, 平井翔大, 和人櫻井, ビスコアトール, 齋藤勇士, グワンレーモンド, 五十地光, 安達直人, 伊藤光紀, 永田晴紀
    2020年 [査読有り][通常論文]
  • Landon Kamps, Kazuhito Sakurai, Yuji Saito, Harunori Nagata
    Aerospace 6 4 1 - 22 2019年04月 [査読有り][通常論文]
     
    Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle throat erosion, characteristic exhaust velocity (c) efficiency, and nozzle throat wall temperature to be determined experimentally. This is done by firing a motor under the same conditions six times, varying only the burn time. Results show that fuel mass consumption was nearly perfectly repeatable, whereas the magnitude and timing of nozzle throat erosion was not. Correlations of the fuel regression rate result in oxidizer port mass flux exponents of 0.62 and 0.76. There is a transient time in the c efficiency histories of around 2.5 s, after which c efficiency remains relatively constant, even in the case of excessive nozzle throat erosion. Although nozzle erosion was not repeatable, the erosion onset factors were similar between tests, and greater than values in previous research in which oxygen was used as the oxidizer. Lastly, nozzle erosion rates exceed 0.15 mm/s for chamber pressures of 4 to 5 MPa.
  • KAMPS Landon, NAGATA Harunori
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 17 4 544 - 551 一般社団法人 日本航空宇宙学会 2019年 [査読有り][通常論文]
     

    A new performance parameter titled “tubular equivalent regression rate” is introduced to evaluate burning rates in hybrid rockets with geometrically complex solid propellant grains. Tubular equivalent regression rates are calculated for eight previously reported CAMUI-type hybrid rocket firing tests and compared with extrapolations of previously reported empirical correlations for classic, swirl and vortex hybrid rockets. A non-dimensional number titled “CAMUI Number” is introduced to evaluate how CAMUI-like a solid propellant grain is. The CAMUI Number ranges from 0-1: 0 means no CAMUI-type blocks are used, 1 means only CAMUI-type blocks are used. The results show that the tubular equivalent regression rate increases logarithmically with CAMUI Number, and approaches a value of around 3 [mm/s] for a CAMUI Number of 1. This increase in tubular equivalent regression rate is shown to correspond to an increase in performance range from a classic (tubular) hybrid rocket at low CAMUI Numbers (0.1) to surpassing a vortex hybrid rocket for high CAMUI Numbers (>0.7). Furthermore, through the block-by-block analysis of tubular equivalent regression rate in a fuel grain with a CAMUI Number of 0.71, it is shown that maximum burning rates were achieved in blocks under slightly oxidizer rich conditions.

  • EXPERIMENTAL INVESTIGATION OF C* EFFICIENCY IN NITROUS OXIDE HYBRID ROCKETS
    Erika Uchiyama, Yurika Kiyotani, Landon Kamps, Harunori Nagata
    PROMOTE THE PROGRESS OF THE PACIFIC-BASIN REGION THROUGH SPACE INNOVATION 166 109 - 115 2019年 [査読有り][通常論文]
     
    Hybrid Rockets have advantages of low cost and high safety but there are few practical uses at the current state of the art. The combustion characteristics of N2O, which is very useful oxidizer, have not been researched in particular. This study is the investigation to clarify the dependency of the c* (characteristic exhaust velocity) efficiency eta(c)* in nitrous oxide (N2O) hybrid rockets on operating conditions through experimentation. Several firing tests were conducted using a 200N thrust class conventional hybrid rocket motor employing high density polyethylene (HDPE) as the fuel and liquid nitrous oxidizer as the oxidizer. The results reveal that there is no clear dependency of eta(c)* on mixture ratio, pressure or characteristic length, suggesting that efficiency must be improved through other design parameters.
  • Landon Kamps, Yuji Saito, Ryosuke Kawabata, Masashi Wakita, Tsuyoshi Totani, Yusuke Takahashi, Harunori Nagata
    Journal of Propulsion and Power 33 6 1369 - 1377 2017年11月 [査読有り][通常論文]
     
    The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flow rates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.

講演・口頭発表等

  • Flame Spreading Opposed to Liquid Oxygen Flow in a Circular Fuel Duct
    Ayumu Tsuji, Yuji Saito, Landon Kamps, Masashi Wakita, Harunori Nagata
    38th International Symposium on Combustion 2020年07月 口頭発表(一般)
  • Development of N2O/HDPE Hybrid Rocket for Microsatellite Propulsion  [通常講演]
    Landon Kamps, Pau Molas Roca, Erica Uchiyama, Tomohiro Takanashi, Harunori Nagata
    70th International Astronautical Congress 2019年10月 口頭発表(一般)
  • Fuel Regression Characteristics in Hybrid Rockets Using N2O/HDPE
    Itoh Seiji, Landon Kamps, Kazuhito Sakurai, Terutaka Okuda, Harunori Nagata
    AIAA Propulsion and Energy 2019 Forum 2019年08月
  • Effect of Aft Chamber Volume on Hybrid Rocket Combustion Efficiency
    Lisa Kageyama, Landon Kamps, Harunori Nagata
    AIAA Propulsion and Energy 2019 Forum 2019年08月
  • Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using N2O/HDPE  [通常講演]
    Landon Kamps, Kazuhito Sakurai, Harunori Nagata
    AIAA Propulsion and Energy 2019 Forum 2019年08月 口頭発表(一般)
  • Feasibility Study on the Application of Hybrid Rockets as Onboard CubeSat Thrusters  [通常講演]
    Landon Kamps, Yuji Saito, Tor Viscor, Tsuyoshi Totani, Harunori Nagata
    32st International Symposium on Space Technology and Science 2019年06月 口頭発表(一般)
  • Development of N2O/HDPE Hybrid Rocket for SmallSat Propulsion  [通常講演]
    Landon Kamps, Harunori Nagata
    超小型衛星利用シンポジウム 2019年03月 口頭発表(招待・特別)
  • N2O/HDPE および O2/HDPE ハイブリッドロケットにおけ る黒鉛ノズル浸食の比較  [通常講演]
    Landon Kamps, Kazuhito Sakurai, Harunori Nagata
    第62回宇宙科学技術連合講演会 2018年10月 口頭発表(一般)
  • The Accuracy of Reconstruction Techniques for Determining Hybrid Rocket Fuel Regression Rate
    Yuji Saito, Landon Kamps, Kodai Komizu, Kentaro Soeda, Daniele Bianchi, Fransesco Nasuti, Harunori Nagata
    AIAA Propulsion and Energy 2018 Forum 2018年07月
  • Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using O2/C2H4  [通常講演]
    Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata
    AIAA Propulsion and Energy 2018 Forum 2018年07月 口頭発表(一般)
  • ハイブリッドロケットにおけるノズルスロート部の壁面温度履歴に関する研究  [通常講演]
    Landon Kamps, Harunori Nagata
    第1回ハイブリッドロケットシンポジウム 2018年06月 口頭発表(一般)
  • ハイブリッドロケット燃料における 軸方向 O/F プロファイル推算に関する研究  [通常講演]
    Landon Kamps, Yuji Saito, Harunori Nagata
    日本航空宇宙学会北部支部2018年大会 2018年03月 口頭発表(一般)
  • Numerical and Experimental Investigation of Nozzle Thermochemical Erosion in Hybrid Rockets
    Daniele Bianchi, Landon Kamps, Fransesco Nasuti, Harunori Nagata
    AIAA Propulsion and Energy 2018 Forum 2017年07月
  • Investigation of Graphite Nozzle-Throat-Erosion in a Laboratory-scale Hybrid Rocket Using GOX and HDPE  [通常講演]
    Landon Kamps, Shota Hirai, Yassine Ahmimache, Raymond Guan, Harunori Nagata
    53rd Joint Propulsion Conference 2017年07月 口頭発表(一般)
  • Tubular Equivalent Regression Rate in Hybrid Rockets with Complex Geometries  [通常講演]
    Landon Kamps
    31st International Symposium on Space Technology and Science 2017年06月 口頭発表(一般)
  • ハイブリッドロケットにおけるノズルスロート浸食取得方法の 精度と適用性に関する研究  [通常講演]
    Landon Kamps, Yuji Saito, Shota Hirai, Harunori Nagata
    第60回宇宙科学技術連合講演会 2016年09月 口頭発表(一般)
  • Method for Determining Nozzle Throat Erosion History in Hybrid Rockets  [通常講演]
    Landon Kamps, Yuji Saito, Ryosuke Kawabata, Yusuke Takahashi, Harunori Nagata
    52nd Joint Propulsion Conference 2016年09月 口頭発表(一般)
  • ハイブリッドロケットにおけるノズルスロート浸食履歴の取得方法  [通常講演]
    Landon Kamps, Yuji Saito, Harunori Nagata
    日本航空宇宙学会北部支部2016年大会 2016年03月 口頭発表(一般)
  • ハイブリッドロケットにおけるノズルスロート浸食履歴取得方法の確立  [通常講演]
    Landon Kamps, Ryosuke Kawabata, Yuji Saito, Harunori Nagata
    6th UNISEC Space Takumi Conference 2016年03月 口頭発表(一般)

その他活動・業績

  • 伊藤 聖司, 内山 絵里香, 櫻井 和人, ケンプス ランドン, 影山 理沙, 永田 晴紀 年次大会 2019 (0) J19105P 2019年 [査読無し][通常論文]
     

    There are few opportunities to launch a satellite for deep space exploration, because of the low budget in Japan. A piggy-back microsatellite takes lower cost than a satellite launched alone. A microsatellite can go GTO with the main satellite, and then the microsatellite goes to deep space using a kick motor. To achieve the thrust and specific impulse that the kick motor requires, we need chemical rockets. Hybrid rockets are the best choice from the viewpoint of safety. Nitrous oxide is selected as the oxidizer because the kick motor also requires storable oxidizer. The relationship between L* and c* efficiency, the fuel regression rate formula and the characteristic of nozzle erosion are obtained from static firing tests. Furthermore, the change in velocity is calculated for each size of the kick motor.

  • 井上卓, KAMPS Landon, 櫻井和人, 内山絵里香, 脇田督司, 永田晴紀 宇宙科学技術連合講演会講演集(CD-ROM) 62nd ROMBUNNO.1N05 2018年 [査読無し][通常論文]
  • Yuji Saito, Landon Kamps, Kodai Komizu, Kentaro Soeda, Daniele Bianchi, Francesco Nasuti, Harunori Nagata 2018 Joint Propulsion Conference 2018年01月01日 [査読無し][通常論文]
     
    © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study is an investigation of the accuracy of reconstruction techniques for determining instantaneous fuel regression rate. Results of reconstruction techniques are compared with results obtained through the measurement of the pressure drop across the fuel in an Axial-Injection End-Burning hybrid rocket (EBHR). The results of numerous firing tests show that this method allows for the evaluation of the accuracy of the instantaneous fuel regression rates obtained by reconstruction techniques. The error bias of O/F values calculated by the reconstruction techniques were around ±10%, and were mainly caused by uncertainties in the measured values of oxidizer mass flowrate and the definition of firing duration. The instantaneous length of an EBHR-type fuel can be calculated from the measurement of the pressure drop across the fuel. However, the calculated fuel length history obtained by the pressure drop in a port does not coincide with that obtained by the reconstruction technique because of an underestimation in pressure drop.
  • Erika Uchiyama, Yurika Kiyotani, Landon Kamps, Harunori Nagata Advances in the Astronautical Sciences 166 109 -115 2018年01月01日 [査読無し][通常論文]
     
    © 2018 Univelt Inc. All rights reserved. Hybrid Rockets have advantages of low cost and high safety but there are few practical uses at the current state of the art. The combustion characteristics of N2O, which is very useful oxidizer, have not been researched in particular. This study is the investigation to clarify the dependency of the c* (characteristic exhaust velocity) efficiency ηc* in nitrous oxide (N2O) hybrid rockets on operating conditions through experimentation. Several firing tests were conducted using a 200N thrust class conventional hybrid rocket motor employing high density polyethylene (HDPE) as the fuel and liquid nitrous oxidizer as the oxidizer. The results reveal that there is no clear dependency of ηc* on mixture ratio, pressure or characteristic length, suggesting that efficiency must be improved through other design parameters.
  • 清谷 優理香, 平井 翔大, ケンプス ランドン, 山口 亮, 櫻井 和人, 脇田 督司, 戸谷 剛, 永田 晴紀 年次大会 2017 (0) S1920105 2017年 [査読無し][通常論文]
     

    To realize deep space missions on a limited budget, a hybrid rocket kick motor for a laboratory-scale space probe being kicked from GTO to a deep space trajectory is being developed. Nitrous Oxide (N2O) is selected as an oxidizer to allow for long-term non-cryogenic storage in space, and High Density Polyethylene (HDPE) is selected as a fuel for safety and affordability.Two fuel configurations are being considered for this mission: a conventional tubular fuel grain, and a Cascaded Multistage Impinging-jet (CAMUI) type fuel grain. This study presents results and analysis from the first set of CAMUI-type static firing tests employing N2O as an oxidizer, with the aim of clarifying performance related issues such as achieving an optimum oxidizer to fuel mass ratio O/F of around 6~7, quantifying fuel regression rate etc. for design purposes. The results of two gaseous N2O firing tests and two liquid N2O firing test lead to the following two conclusions. The use of liquid N2O will be necessary to realize an appropriate flowrate for space applications, and CAMUI-type motors may not be suitable for achieving optimum O/F because they tend to burn extremely fuel rich. Additional firing tests are necessary to quantify the fuel regression rate in CAMUI-type fuel and conventional tubular fuel grains using N2O.

  • 清谷優理香, 山口亮, 櫻井和人, KAMPS Landon, 井上卓, 脇田督司, 戸谷剛, 永田晴紀 宇宙科学技術連合講演会講演集(CD-ROM) 61st ROMBUNNO.3H02 2017年 [査読無し][通常論文]
  • Daniele Bianchi, Landon Kamps, Francesco Nasuti, Harunori Nagata 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 2017年01月01日 [査読無し][通常論文]
     
    Despite some inherent disadvantages, hybrid rockets are today considered as having a great potential to become one of the future generation of propulsion systems, partly due to recent emphasis on propulsion safety, reliability, low development cost, reduced environmental pollution, and greater operability. Nevertheless, the hybrid rocket development has not achieved the same level of maturity as solid and liquid traditional systems. An aspect that has not been much dealt with in the open literature is that of nozzle erosion, whose minimization or reduction is one of the challenges in hybrid rocket propulsion. To this goal, a joint numerical and experimental investigation of nozzle throat erosion has been performed using a computational fluid dynamics approach compared to static firing tests carried out on a 2kN-class lab-scale hybrid rocket burning liquid oxygen and highdensity polyethylene. The numerical approach is able to capture the main features of the nozzle throat erosion behavior, fairly reproducing the throat erosion rate values and its dependence upon the oxidizer to fuel mixture ratio and motor chamber pressure.
  • 山口 亮, 川端 良輔, 平井 翔大, ケンプス ランドン, 脇田 督司, 戸谷 剛, 永田 晴紀 年次大会 2016 (0) S1920201 2016年 [査読無し][通常論文]
     

    These days, CAMUI type hybrid rocket has been developed. The rocket is faced with the problem of erosion of graphite nozzle. Nozzle erosion, which is mainly caused by oxidation reaction, decreases specific impulse of rockets. The authors selected some materials which can prevent nozzle erosion and evaluated anti-erosion materials for hybrid rocket nozzle by combustion experiments. We used 2.5 kN class CAMUI type hybrid rocket motor for combustion experiment. The authors used two types of fiber reinforced ceramics, silicon carbide ceramics, zirconia, tungsten carbide, silicon nitride ceramics, graphite coated by silicon carbide, alumina and carbon fiber carbon composite for nozzles. As an experimental result, tungsten carbide and graphite coated by silicon carbide showed good anti-erosion characteristics for hybrid rocket nozzles. High melting point and high thermal conductivity seem favorable for anti-erosion materials for hybrid rocket nozzles.

受賞

  • 2019年08月 AIAA ハイブリッドロケットの最優秀論文賞
     O2/C2H4を用いるハイブリッドロケットにおける黒鉛ノズル浸食に関する研究 
    受賞者: ケンプス ランドン トマス
  • 2018年03月 JSASS Good Presentation Award for Student
     ハイブリッドロケット燃料における軸方向O/Fプロフィル推算に関する研究 
    受賞者: ケンプス ランドン トマス
  • 2016年08月 JSASS 優秀発表賞
     ハイブリッドロケットにおけるノズルスロート浸食取得方法の精度と適用性に関する研究 
    受賞者: ケンプス ランドン トマス
  • 2014年05月 米陸軍 Army Commendation Medal
     For Meritorious Service as Executive Officer 
    受賞者: ケンプス ランドン トマス
  • 2013年02月 米陸軍 Army Commendation Medal
     For Meritorious Service in Operation Enduring Freedom 
    受賞者: ケンプス ランドン トマス

共同研究・競争的資金等の研究課題

  • 再生冷却によるハイブリッドロケット黒鉛ノズル浸食抑制の実証
    日本学術振興会:
    研究期間 : 2020年04月 -2023年03月 
    代表者 : ケンプストマスランドン
  • ハイブリッドロケットにおける黒鉛ノズル浸食現象の機構解明
    日本学術振興会:特別研究員(DC1)
    研究期間 : 2018年04月 -2019年09月 
    代表者 : ケンプス ランドン トマス

大学運営

社会貢献活動

  • Space Propulsion and Research at Hokkaido University
    期間 : 2019年03月08日 - 2019年03月09日
    役割 : パネリスト
    主催者・発行元 : スーパーサイエンスハイスクール(SSH)
    イベント・番組・新聞雑誌名 : 2019年北海道大学国際サイエンスフェア
  • 日本ロケット事業と私
    期間 : 2016年08月28日 - 2016年08月28日
    役割 : 司会
    主催者・発行元 : 札幌ユネスコ協会
    イベント・番組・新聞雑誌名 : 2016 UNESCO Sapporo Annual Lecture


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