3. はじめに
化学スラスタなど宇宙機用化学推進の紹介
一液式が中心
ヒドラジン,推進機の構造,略史
なぜ,「電気推進夏の学校」で?
電気推進機の論文では,Introductionで化学推進と比較する
ことが多い.
電気推進機は,教科書があるが・・・
電気推進ロケット入門(栗木先生,荒川先生編集)
イオンエンジンによる動力飛行(國中先生他)
一方,化学スラスタには洋書を含めて書籍が僅か.
Charles D. Brown, Space propulsion
G. P. Sutton, History of Liquid Propellant Engines
Peter J. Turchi, Propulsion Techniques: Action and Reaction
Wilfried Ley, Handbook of Space Technology
36. AIM-4Gの派生?
Falcon missile (AIM-4G, GAR-3A, Hughes & Thiokol)
Thiokol SP-188 (Isp: 204 s)One the other apex was a 13.3-kN-thrust solid fueled
TX-8-6 motor derived from the Falcon air-to-air
missile, to brake the probe into lunar orbit
―Pauro Ulivi, Lunar Exploration: Human Pioneers and Robotic Surveyors
正確なところは1958 NASA/USAF SPACE PROBES (ABLE-l) FINAL REPORT
のAppendix D (confidential)が公開されないとわからない?
37. 1958 NASA/USAF SPACE PROBES (ABLE-1) FINAL REPORT VOL.2, 1959
計画では
月探査
月軌道への投入は失敗
流星塵密度
惑星間磁場
計測には成功
41. Thrusterという新概念の誕生?
The development of small thrusters for spaceflight vehicles is
really a different business than those discussed before in this
chapter. (G. P. Sutton, History of liquid propellant rocket)
古い単語に新しい意味をもたせることがある. 例) missile
古めかしいthrusterという言葉に最新鋭のthrusterの意味を付与した?
43. Thruster & Thrustor
0
10
20
30
40
50 NTRS, thruster
ELSEVIER, thruster
Springer, thruster
DTIC, thruster
NTRS, thrustor
ELSEVIER, thrustor
Springer, thrustor
DTIC, thrustor
or
er
er
oror
or
44. 正書法的にThrusterが正しい
In forming the agent-noun from the base thrust,
established rules of English orthography require that
the suffix should be spelled –er.
―Robert G. Jahn, Physics of Electric Propulsion, 1968
45. Thruster before 1959
Underseat Rocket
Motor MK 124
Figure: M.P. Audley, LOGISTICS MANAGEMENT REPORT FOR U.S. NAVY PROPELLANT-ACTUATED DEVICES
(PAD), 2004
46. Thruster before 1959
Underseat Rocket
Motor MK 124
Figure: M.P. Audley, LOGISTICS MANAGEMENT REPORT FOR U.S. NAVY PROPELLANT-ACTUATED DEVICES
(PAD), 2004
The canopy jettison system for the B-57B aircraft has been
evaluated by ballistic tests. The system consists of an M5
thruster for release of the canopy latches, an M3 remover for
jettison of the canopy, and initiators with pressure
transmission systems for actuation of these devices.
― J.E. Prozek, EVALUATION OF CANOPY JETTISON SYSTEM PROPOSED
FOR USE IN B-57B AIRPLANE, Frankford Arsenal Report, 1956
47. Thruster before 1959
Underseat Rocket
Motor MK 124
Figure: M.P. Audley, LOGISTICS MANAGEMENT REPORT FOR U.S. NAVY PROPELLANT-ACTUATED DEVICES
(PAD), 2004
Lately, integrated escape systems for large aircraft, such as the
B-52, have been developed. These involve initiators,
removers, catapults and work devices called thrusters, which
are merely propellant actuated devices that move a piston,
the thrust of which does some desired work.
― The Bureau of Naval Weapons, CHLORATES AND PERCHLORATES THEIR
CHARACTERISTICS AND USES, May 1960
48. Thruster before 1959
Underseat Rocket
Motor MK 124
Figure: M.P. Audley, LOGISTICS MANAGEMENT REPORT FOR U.S. NAVY PROPELLANT-ACTUATED DEVICES
(PAD), 2004
work devices called thrusters, which are merely
propellant actuated devices that move a piston, the thrust of
which does some desired work.
― The Bureau of Naval Weapons, CHLORATES AND PERCHLORATES THEIR
CHARACTERISTICS AND USES, May 1960
56. Starfinder apogee motor
Syncom III
SYNCOM ENGINEERING REPORT, VOLUME II, NASA TR R-252, 1967
H2O2 thruster
JET direction
JET direction
JET
direction
57. Syncom III
Starfinder apogee motor
SYNCOM ENGINEERING REPORT, VOLUME II, NASA TR R-252, 1967
JET
LATERAL H2O2 (No.1)
AXIAL H2O2
(No.1)
70. Mariner 2
(Mariner R-2)
Launch on Aug. 3, 1962
Mission: Venus exploration
Attitude control: Nitrogen gas jet system
4-jet vane vector control 225-N motor (burn time: 0.2-57 s)
(Slug start w/ NTO and Al2O3 pellets)
NASA, MARINER-VENUS 1962, SP-59, 1965
NASA, NSSDCA
71. Mariner 4
Launch on Nov. 28, 1964
Mission: mars exploration
4-jet vane vector control 222-N motor (Slug start)
12 cold gas jet
NASA, NSSDCA
NASA, NSSDCA
72. Mariner
Retro
Rocket
T. W. Price and D.D. Evans, The Status of Monopropellant Hydrazine Technology, 1968
R. V. Buren, MARINER MARS 1964 HANDBOOK, 1965
Burn time:
103 s at launch
81 s after midcourse maneuver
Max. thrust vector deflection
±5 deg
Nozzle area ratio: 44
73. Thruster
arrangement for
Mariner 4
Mariner Mars 1971 Attitude Control Subsystem, 1974
Mariner Mars 1964 Handbook, 1965
Nitrogen cold gas jet
(RCS, PITCH)
Nitrogen cold gas jet
(RCS, ROLL and YAW)
225-N H2N4 engine
w/ four jet vanes for
thrust vector ctrl
X
Y
X
Y
Cold gas jet arrangement
(TOP VIEW)
VIEW DIRECTION
(z-axis)
+Z
74. T. W. Price and D.D. Evans, The Status of Monopropellant Hydrazine Technology, 1968
H-7 catalyst
Nitrogen
(pressurant)
N2H4
点火装置
(N2O4)
75. Shell 405 (Aerojet 405)
• Iridiumベースの触媒
• Caltech JPLとShell Chemicals Companyが開発(1957–1960年頃)
• 1963 (1964?)から利用可能になる.
• この触媒により点火用のNTOが不要になり,Pulse modeが可能になる
Eckart W. Schmidt, History of Hydrazine Monopropellants, 2009
Wilfried Ley, Handbook of Space Technology
78. Applications Technology Satellite 3
技術試験
静止衛星
スピン安定
通信(VHF, C-band)
カメラ
レジストジェット
ヒドラジン一液式(4 lbs)
1967年11月5日打ち上げ
ATS-3でヒドラジン推進系へ変
更になる
ATS-1でH2O2スラスタが失
敗
NASA SP-4217
Flight success of hydrazine/Shell 405 thrusters in the late
1960s prompted the phasing out of hydrogen peroxide in favor
of hydrazine for practically all satellite applications. The
transition began with the NASA/Hughes ATS-3 satellite.
―Peter J. Turchi, Propulsion Techniques: Action and Reaction
79. Ammonia resistojet on ATS-III
Thruster #1 Thruster #2
Hot Cold Hot Cold
Thrust, mN 169 146 1850 1060
Isp, s 132 105 158 86
Power, W 2.5 0 3.6 0
T. K. PUGMIRE AND W. S. DAVIS, ATS-III Resistojet Thruster System Performance, J. Spacecraft, 1966.
83. Instrumentation/Propulsion
The propellants are nitrogen tetroxide and unsymmetrical-dimethyl
hydrazine.
The main propulsion system and the smaller reaction control system, used for
https://www.nasa.gov/mission_pages/station/structure/elements/soyuz/spacecraft_detail.html
84. Descent Module on Soyuz TMA
“The eight hydrogen peroxide thrusters located on the module are used to control
the spacecraft's orientation, or attitude, during the descent until parachute
deployment.”
https://www.nasa.gov/mission_pages/station/structure/elements/soyuz/spacecraft_detail.html
89. Viking orbiter and lander
https://nssdc.gsfc.nasa.gov/
2-axis gimballed main engine
Thrust vector control
(pitch and yaw)
Cold gas thrusters
Roll control
92. Aeroshell
thrusters
Yaw & Pitch engine
Used for attitude control
Produce deorbit impulse
Thrust: 36N, Prop.: hydrazine
Roll engine
Roll control
Thrust: 36N, Prop.: hydrazine
x
y
z
Four RCS modules
RCS module
93. Lander with
Terminal
Descent System
(TDS)
ROLL ENGINES (4)
TERLMINAL DESCENT ENGINE (3)
Descending
Pitch & Yaw ctrl
Thrust: 44.5 N
Neil A. et. Al., Viking '75 Spacecraft Design and Test Summary Volume I - Lander Design, 1980
94. Neil A. et. Al., Viking '75 Spacecraft Design and Test Summary Volume I - Lander Design, 1980
Eckart W. Schmidt, History of Hydrazine Monopropellants, 2009
Catalyst
container
Motor driven
throttle valve
Propellant
inlet
Exhaust
nozzles
(18)
Terminal Descent
Engine (MR-80)
Thrust: 62-638 lbf, ISP:205s
Expansion ratio: 20, Prop.: Hydrazine
96. 18 nozzles
Viking 75 project: Viking lander system primary mission performance report, 1971
Eckart W. Schmidt, Viking Mars Lander History - Hydrazine Monopropellant History, 2015
Original design
Final design
To reduce surface
pressure, minimizing
landing site alteration
by dispersing plume
97. FIRST CLASS
PASSENGER
Eckart W. Schmidt, Viking Mars Lander
History - Hydrazine Monopropellant
History, 2015
Assembly at Rocket
Research Company
99. Voyager, the most distant artifact
21.0 billion km (140.6 AU), Velocity:17 km/s
17.3 billion km (115.8 AU)
Velocity: 15 km/s
Orbit of Pluto: 39.4 AU
Data:October 23, 2017
Launched in 1977 https://voyager.jpl.nasa.gov/
101. Rocket Research Company, VOYAGER URANUS ENCOUNTER 0.2-lbf T/VA SHORT PULSE TEST REPORT, 1986
MR-103, a thruster designed for Voyager
10-ms pulse firing yielded
an Isp of 110 s.
C.D Brown, Spacecraft Propulsion, 1995
104. 0.89 N (ATT CTRL & TRAJ CORR, Prop.: Viking grade N2H4)
441 N (Pitch and Yaw)
Solid motor
22 N (Roll)
441 N (Pitch and Yaw)
Charles D. Brown, Elements of Spacecraft Design
Thrust: 6.8 MN
Heaters (1.4-W) maintain
min. temp of 116 ºC
105. Rockets and thrusters on Voyager
On-board
MR-103 (16 thrusters)
Thrust: 0.89 N
Isp: 227? s
10-ms pulse
Attitude/Trajectory
control
Trajectory correction (4
thrusters)
Attitude control (2
redundant systems w/ 6
thrusters)
Jettisoned
5-lbf (4 thrusters)
Model: RRC MR-50 ?
Thrust: 22 N, Isp: 228? s
Thrust vector control (Roll)
MR-104 (4 thrusters)
Thrust: 441 N, Isp: 239? s
TVC (pitch & yaw)
Star 37E Solid propellant
motor
Accelerating spacecraft to final
Jupiter trajectory velocity
Thrust: 6,805,440 N
Weight: 1,123 kg
Prop.: 1039 kg
Burn time: 43 s
Charles D. Brown, Elements of Spacecraft Design
109. Terminal Descent Engine for Viking
一液式の燃焼ガスはきれいなはずだった
比推力は二液式の方が有利だが一液が用いられた
実際は,アニリンのためにシアン化水素(猛毒)が発生する
可能性があった.
Viking grade hydrazineの誕生
Aniline 0.5%から0.003%へ
H
H
N
HH
H
+
Eckart W. Schmidt, Viking Mars Lander History - Hydrazine Monopropellant History, 2015
110. MR-103 monopropellant thrusters on
Voyager
着陸しない→HCNが発生し
てもよいはず
当初はmonopropellant
grade (aniline 0.5%)を使用
した.
pulse shape distortion
燃焼室圧力の緩慢な上
昇.
低デューティー比
低触媒温度
Eckart W. Schmidt, Viking Mars Lander History - Hydrazine Monopropellant History, 2015
111. Pulse shape distortion
L. Holcomb, et. Al., Effects of Aniline Impurities on Monopropellant Hydrazine Thruster Performance, 1977
0.9 N thruster
Catalyst bed temp.: 394
Duty ratio: 0.04/100
Propellant: Monopropellant grade
112. Pulse shape distortion
L. Holcomb, et. Al., Effects of Aniline Impurities on Monopropellant Hydrazine Thruster Performance, 1977
PURIFIED: aniline < 0.002%
Military grade: 0.54% aniline
PURIFIED/Aniline: 0.74% aniline
触媒温度:394 K
Duty ratio: 0.04/100
触媒温度:394 K
Duty ratio: 0.04/100
触媒温度:477 K
Duty ratio: 0.04/36
113. Ignition delay
L. Holcomb, et. Al., Effects
of Aniline Impurities on
Monopropellant Hydrazine
Thruster Performance, 1977
Aniline 0.012%
Aniline 0.41%
Aniline 1.09%
LOWERISBETTER
114. 原因はaniline poisoning
High purityで偶然実験したところ,aniline poisoningが原因
と判明.
Voyagerの推進剤をHigh purity gradeに変更
ヒータ電力の削減
長寿命化
Eckart W. Schmidt, Viking Mars Lander History - Hydrazine Monopropellant History, 2015
Production of Viking-Grade hydrazine would most
likely have been discontinued if it had not been for
this accidental discovery.
―E. W. Schmidt, History of Hydrazine Monopropellants
116. Cassini
spacecraft
Two R-4D bipropellant engines
Orbital maneuvers
Trajectory corrections
Four RCS modules
Have four MR-103H thrusters
Produce thrust (y and z axes)
Allow 3-axis control
xy
z
Y1
Z1
Y2
Z2
Z4
Y4
117. Thruster arrangements
RCS module (4 modules)
Has two redundant thruster
blanches
Contains Y and Z direction thrusters
3-axis attitude control
R-4Ds are arranged along Y axis.
Thrust vector (MR-103H)
Thrust vector (R-4D)
Magnetometer
arm
x
y
z
z
x
y
Z1
Y1
Y2
Z2 Z3
Y3
Y4
Z4
RCS module
S. Sarani, A Flight-Calibrated Methodology for Determination of Cassini Thruster On-Times for Reaction Wheel Biases, 2010
123. SHP-163
ISAS/JAXA
HAN-based propellant
Specific weight: 1.4
Freezing point 243 K
Low toxicity
Isp: 276 s
O
N
H
H
H
H O
O
O N
HAN
H
H H
H
O
C
Methanol
HH
O
Water
N
H H
H
H
N
Ammonium nitrate
O
O O
N
124. Hydroxyl Ammonium Nitrate (HAN)
固体推進薬の酸化剤として
研究される
水溶性
イオン性液体
LP-1845などHANをベースと
した発射薬がある.
8 atmあたりで燃焼速度が
急激に上昇
Ion liquid
O
O
O
O
N
N
H
H
H
H
126. AF-M315E
HAN based monopropellant
Isp: 257 s
12% higher than Hydrazine
Specific weight: 1.47
Hydrazine: 1.00
Low toxicity, Can not freeze
Aerojet, MPS-130 Innovative Propulsion Solutions for Smallsats
Ronald A. Spores, et. al., AIAA 2015-3753
Busek, BXT-X5 Green Monopropellant Thruster
MODEL: GR-1
Thrust: 1N
MODEL: MPS-130
Thrust: 1N, Isp: 240 s Manufacturer: Busec
Model: BST-X5
Thrust: 0.5 N
127. LMP-103S
Monopropellant
Higher performance
Specific weight: 1.24, Isp: 230 s
Freezing point : -90ºC
Increased safety, Low toxicity, Non-carbogenic
ECAPS, HIGH PERFORMANCE GREEN PROPULSION (HPGP) ON-ORBIT
VALIDATION & ONGOING DEVELOPMENT, 2013
(3-6%)ADN
(60-65%)
(15-20%)
+ + ++
Water
(solvent)
Syncom IIは,JFKとナイジェリア首相(Abubaker Balewa)とのトップ会談に使われた.
http://www.boeing.com/news/frontiers/archive/2003/november/i_ids3.html
Satellite used in a live two-way call between heads of state (Syncom 2, President John F. Kennedy and Nigerian Prime Minister Abubaker Balewa, 1963).
東京オリンピックの中継を行っている.
http://www.boeing.com/news/frontiers/archive/2003/november/i_ids3.html
Satellite used to provide the first continuous trans-Pacific broadcast (Syncom 3, Tokyo Olympic Games, 1964).