Post on 05-Jul-2020
Propulsion and Energy Systems; Dec 21st (2015)
Micro-satellite propulsion KOIZUMI Hiroyuki
(小泉 宏之)
Graduate School of Frontier Sciences, Department of Advanced Energy
& Department of Aeronautics and Astronautics
(基盤科学研究系 先端エネルギー工学専攻,工学系航空宇宙工学専攻兼担)
Huge cost
Failure is never excused
Conservative and long-time design
No growth of technology and human
Compensation by money ant time
Small satellite
・Welcome, new service
・Quick technology cycle
Innovation
・Quick human-resource development
Small satellite
Small satellites
Microsatellites
Nanosatellites
100 – 500 kg
10 – 100 kg
1 – 10 kg
Cubesat Unit: 10 x 10 x 10 cm3
Mass
Power
Typically 10 – 20% of the satellite mass
Typically If parallel to the mission: < 20% If dependent from the mission: < 80%
Typical power generation: 1–3 W/kg (e.g 10 kg satellite → 10–30 W)
Small propulsion; Resource
Typical budget for propulsion would be 10-20%
Budget
Law Strict limitation for High-pressure gas, explosives, toxic materials.
Small propulsion; Resource
Don’t lose the merit of small sat.
LEO; 100km altitude change 60 m/s
LEO 300km, 1-year drag compensation (50kg, 50cm x 50cm, CD1.4)
50 m/s
GEO; NSSK (1year) 50 m/s
LEO; 1 degree orbit inclination 130 m/s
Lunar orbit from GTO 2000 m/s
ΔV
Small Chemical Propulsion
・Cold-gas thruster ・Gas-liquid equilibrium thruster ・mono-propellant propulsion using hydrogen peroxide ・Micro-solid array ・Solid microthruster
Cold-gas thruster
Propulsion and Energy Systems; Dec 21st (2015)
Cold-gas thruster;Principle
gcCI Fsp /*
Blow-down from a high pressure tank
Specific impulse by gas and temperature
M/kg mol-1
Density (24 MPa)
Isp/s
He 4 0.04 180
N2 28 0.28 80
Xe 131 2.74 31
Resisto-jet thruster
Heater
Propulsion and Energy Systems; Dec 21st (2015)
Cold-gas thruster
The simplest
Already used in micro-/nano- satellites
Low specific impulse
Large high-pressure system
Not for high ΔV
Merit
Demerit
Heritage
Propulsion and Energy Systems; Dec 21st (2015)
1) SSTL; Gas Propulsion System
Dry mass: 6.7 kg Dimensions: 400 x 254 x 215 mm3
Propellant: 500g Xe or 176g N2 Thrust: 20 – 50 mN Isp : 42 s Xe or 100 s N2 Total impulse: 380 Ns
50 kg S/C
ΔV = 6.4 m/s
Propulsion and Energy Systems; Dec 21st (2015)
Cold-gas thruster
Dry mass: 7.3 kg
Propellant: 12 kg Xe Thrust: 18 mN Isp : 48 s Total impulse: 5644 Ns
SSTL; Microsatellite Gas Propulsion System
50 kg S/C
ΔV = 110 m/s
For ΔV of ~100 m/s?
Gas-liquid equilibrium thruster
Propulsion and Energy Systems; Dec 21st (2015)
Gas-liquid equilibrium thruster
One of the gold-gas thrusters
Propellant storage in liquid phase
No high pressure system
→Reducing system volume
Needing a heater for vaporization
Needing a gas/liquid separation device
Specific impulse is the same as cold-gas thruster
Merit
Demerit
Propulsion and Energy Systems; Dec 21st (2015)
1) Thruster for IKAROS
Propellant: 20 kg HFC-134a Dry mass: 約20 kg Thrust:400 mN Isp:40 s Total impulse: 7000 Ns
Molecular mass:102 g/mol Vapor pressure: 0.57 MPa Liquid density: 1225 kg/m3
No high-pressure system
Metal foam for the separation
using surface tension and temperature gradient
Mono-propellant thruster
Propulsion and Energy Systems; Dec 21st (2015)
Hydrogen peroxide thruster
Hydrogen peroxide + catalyst
→Isp: 80 s
Propellant feeding →Bladder + High-pressure gas
Propellant tank×2+Pressure tank ×1
Propulsion and Energy Systems; Dec 21st (2015)
Thruster for Hodoyoshi-1/3
Power 3.4W
Mass 5.8kg, including 2 kg propellant
Size 265×270×85 mm3
Thrust 350 mN
Isp >80 s
ΔV 30m/s
Thruster for Hodoyosh-3
Propulsion and Energy Systems; Dec 21st (2015)
Hydrogen peroxide thruster
High Isp as CP
Hodoyoshi-1/3
Toxity of H2O2
Rejected for H2A secondary payload (UNIFORM1)
Merit
Demerit
Heritage
Needing on-site charge
Solid-propellant thruster
Propulsion and Energy Systems; Dec 21st (2015)
Micro-solid array
Digital control of micro-solid propellant
MEMS fabrication Micro Electro Mechanical Systems using semiconductor device fabrication technologies
Propulsion and Energy Systems; Dec 21st (2015)
マイクロソリッドアレイ
Small ΔV
Ultra miniaturization without gas system
e.g. 30 μNs by 1shot
300 mNs by 100x100 array
ΔV = 0.3 m/s @ 1kg S/C
長所
短所
Easy fabrication of arrayed structure
Propulsion and Energy Systems; Dec 21st (2015)
Laser ignition, solid microthruster
Boron & potassium nitrate
Laser ignition of multiple pellets
Propulsion and Energy Systems; Dec 21st (2015)
Laser ignition, solid microthruster
Isp:150s, 60 shots, 300-cc
Cubesat compatible 10 m/s class ΔV
ΔV : 30 m/s for a 3kg Cube-sat
Merit
Demerit ΔV less than 100 m/s
Needing rotating mechanism
Small Electric Propulsion
・Pulsed plasma thruster ・Vacuum arc thruster ・Arc-jet thruster ・Ion thruster ・Electrospray ・Microwave engine ・Hollow cathode thruster
Pulsed Plasma Thruster
Propulsion and Energy Systems; Dec 21st (2015)
Pulsed plasma thruster
Solid propellant (not explosive), passive feed
Pulsed discharge of capacitor energy
Electromagnetic acceleration
Propulsion and Energy Systems; Dec 21st (2015)
パルス型プラズマスラスタ;特徴
Simple feeding mechanism
EMI (electro magnetic interference)
Geometric limitation of propellant and ΔV
Several verifications
Component life time of 1 billion shots
Merit
Demerit
High specific impulse(500-1000 s)
Heritage
Propulsion and Energy Systems; Dec 21st (2015)
Thruster on EO-1
EO-1 by NASA Launch: 2000 Mass: 570 kg
Impulse bit: 0.86 mNs Isp:1370 s Power:70 W (1Hz) Total mass: 4.95 kg Propellant: 0.14 kg Total impulse: 460 Ns →ΔV = 0.81 m/s
←!!
Spacecraft
Propulsion
Propulsion and Energy Systems; Dec 21st (2015)
Concept by Univ. Surrey
for 3U-cubesat
Propulsion module: ¼U Pulsed power module: ¼U
Mass 0.34 kg
Power 1.5
Volume 480 cm3
Isp 320 s
Propellant 1.1 g
ΔV for 4.5 kg 2.7 m/s
Propulsion and Energy Systems; Dec 21st (2015)
PROITERES by OIT (大阪工大)
PROITERES
Launch by PSLV (Indian rocket) in 2012
10 kg, 30x30x30 cm3, 10 W
Coaxial pulse plasma thruster
Electrothermal acceleration, no feeding system Wet mass: 2.0 kg (Head:0.3kg, Cap.:0.2kg PPU:1.0kg, Cables:0.5 kg) Total impulse: 5 Ns(ΔV 0.5 m/s)
Propulsion and Energy Systems; Dec 21st (2015)
• Compatible from cubesat to 100 kg S/C
• High technical maturity
• Few actual usages, so far
• ΔV limitation • Electromagnetic interference
Pulsed plasma thruster; Summary
Ion thruster
Propulsion and Energy Systems; Dec 21st (2015)
Ion thruster
Plasma source Ion acceleration
electron emission
Propellant
Power
Ion
Electron
Neutral Inevitable electron emission
Electrostatic acceleration of ions
Propulsion and Energy Systems; Dec 21st (2015)
Ion acceleration
Ion beam
Outside
Inside
Example of the ion beam
Appropriately-designed grids system converges the ion beam
Beam trajectory
Electrostatic potential
Propulsion and Energy Systems; Dec 21st (2015)
Types of the plasma generators
• Direct current (DC) electron discharge
• Radio frequency (RF) discharge
• Microwave discharge
Propulsion and Energy Systems; Dec 21st (2015)
DC-discharge ion thruster
Electron emission
magnetic field
Anode 30 V
Gas injection
Propulsion and Energy Systems; Dec 21st (2015)
RF-discharge ion thruster
Induced magnetic field Insulating body
RF coil
Gas injection
Induced current
ICP
Propulsion and Energy Systems; Dec 21st (2015)
Microwave discharge ion thruster
Microwave emission
magnetic field
Gas injection
Antenna Coaxial cable or waveguide
Electron cyclotron resonance
𝑓microwave = 𝑓cyclotoron
Propulsion and Energy Systems; Dec 21st (2015)
Ion thruster
High Isp (1000-3000 s)
High-pressure tank and feeding system
Complicated = a number of parts
Merit
Demerit
Heritage
The most heritage in standard-size S/C Small ion thruster: Hodoyoshi-4, PROCYON
High ΔV mission Storage in a tank
Propulsion and Energy Systems; Dec 21st (2015)
μRIT by Univ. Giessen
The smallest thruster in RIT series
RF plasma
Developed for LISA
RIT for (four thruster heads)
Dry mass: 14 kg Propellant: 0.4 kg Xe Thrust: 7 – 100 μN Power: 60-86 W (PCU: 26 W)
Max. thrust 600 μN
Propulsion and Energy Systems; Dec 21st (2015)
Research by JPL & UCLA
DC-discharge, 30 mm of beam diameter Thrust:3.0 mN Specific impulse:1700 – 3200 s Ion production cost: 400 – 600 V/ion *not included the neutralizer DC-discharge = two cathodes Inside for plasma Outside for neutralizer
Propulsion and Energy Systems; Dec 21st (2015)
Research by KU (九州大学)
Microwave discharge (μ10’s neutralizer based plsma source)
Thrust 790 μN Isp 4100 s Microwave power 8 W Beam power 20 W
システムには45W必要 (8/0.4 + 20/0.8)
*not included the neutralizer
Propulsion and Energy Systems; Dec 21st (2015)
Mass: 8.1 kg (incl. 0.9 kg Xe)
Volume: 39 x 26 x 15 cm3
Power: 27 W
Thrust: 210 μN
Isp: 740 s
Delta V: 140 m/s (50 kg S/C)
MIPS Flight Model
Performance summary
MIPS, flight model
Earth gravity assist
A small secondary payload of HAYABUSA-2
Flyby observation of a small asteroid
1. Wheel unloading by RCS
2. High ΔV for orbit transfer
3. Trajectory correction maneuver
Multiple thrusters
Electric propulsion
Chemical propulsion
PROCYON needs
Xenon-gas system
Ion thruster
Controller
Control
Gas
Power supplies Microwave
High voltages
MIPS Miniature Ion
Propulsion System
Xenon-gas system
Ion thruster
Controller
Control
Gas
Power supplies Microwave
High voltages
I-COUPS Ion thruster and COld-gas thruster
Unified Propulsion System
Cold-gas thrusters
Cold-gas thruster
Thrust (single) 22 mN
Specific impulse 24 s
Number of thrusters 8
Power consumption 7 W
(2 thrusters)
Cold-gas thruster Thruster valve
Cold-gas thrusters 0.41 kg
Controller 0.95 kg
Power supplies 1.31 kg
Ion thruster 0.38 kg
Gas system
4.5 kg !!
Xenon 2.57 kg
Sharing gas system is superior to increasing Isp
Gas system1 (Tank) 2.01 kg
Gas system2 (others) 2.25 kg
0
50
100
150
200
250
Accu
mu
late
d o
pera
tion
tim
e/h
ou
rs
I-COUPS; ITU全運転(5分平均プロット ) 論文用 from Dec 28 (2014) to Mar 12 (2015); 運転判定条件:SPS-I (mA)>1.00
Tota
l opera
ting t
ime/h
ours
223 h
©Hodoyoshi-3&4, The University of Tokyo
COTS-based micro-EP subsystems, including the high-pressure gas system, have been in good health.
The cold-gas-thruster RCS are successfully working over 103 operations
The ion thruster operated in 223 hours.
The miniature propulsion system of PROCYON has operated for more than 6 months, as the first interplanetary micropropulsion.
Propulsion and Energy Systems; Dec 21st (2015)
Iodine ion thruster by Busek
54
Thrust 600 μN Specific impulse 2000 s Power 30 W System Dry Mass 1.7 kg Propellant Mass 1.5 kg
Lunar Ice Cube; launch in 2018
Propulsion and Energy Systems; Dec 21st (2015)
• Studies are increasing, but fewer than PPT
• Few thrusters completed as a system
• UT launched/operated the first one, and may be followed by Busek.
• Xenon limits the dry mass as >3 kg
• The highest ΔV potential
Ion thruster; summary
Other Electric Propulsions
Propulsion and Energy Systems; Dec 21st (2015)
Microwave engine
Developed in Hokkaid Univ. (北海道大学)
μ10’s neutralizer based plasma source
= Double discharge, cusped field Hall effect thruster
Electrostatic acceleration, no grids
Endurance test
Components development for Hokkaido satellite (no information update)
Propulsion and Energy Systems; Dec 21st (2015)
Microwave engine
Including PPU eff.
18.5W
38.5W
57 W total power
T: 0.6 mN Isp: 1015 s
Propulsion and Energy Systems; Dec 21st (2015)
Small arc-jet thruster
Micro-Multi-Plasma-jet Array
Small arrayed nozzle by laser etching
Needing high pressure feeding system
Thrust 1.1 mN Power < 10 W Isp 70 s (N2)
by 3x3 array
Propulsion and Energy Systems; Dec 21st (2015)
Electrospray thruster
Emission of charged particles from liquid surface by strong electric field
liquid metal Oil Ionic liquid
FEEP
Isp depends on specific charge and mass
Colloid thruster
10,000 s 100 s 1000 s
MEMS, μm-needle → array
No plasma → High efficiency
~100 kV/mm
Propulsion and Energy Systems; Dec 21st (2015)
FEEP: Field Emission Electrostatic Prop.
In-FEEP: using Indium
LMIS (Liquid Metal Ion Source) is not a thruster but has a lot of space utilization heritage
Thrust:0.1 – 100 μN Isp: 5,800 s @ 25 μN Total Impulse: 6100 Ns Propellant: 15 g Indium
9 LMIS Assembly
Ultra-accurate attitude control
Propulsion and Energy Systems; Dec 21st (2015)
Vacuum-arc thruster
Surface discharge in vacuum
Propellant: electrodes + insulator (dielectric material)
One type of the pulsed plasma thrusters
(using a capacitor, but not using an ignitor)
Merit/demerit is similar as PPT
Propulsion and Energy Systems; Dec 21st (2015)
Hollow cathode thruster
Hollow cathode(electron source)as thruster
Acceleration: electrothermal + plasma potential
Merit: already developed for space utilization
Thrust 1.6 mN Power 55 W Isp 85 s
Needing high pressure
PPU: 260 x 86 x 23 mm3
Similar with resisto-jet
Propulsion and Energy Systems; Dec 21st (2015)
Microthruster
Motivation of small sat: Easy, Quick, Cheep
Motivation of small prop.の魅力: same
Abundant researches for microthrusters (more than standard sized propulsion)
Few flight heritage
Point 1: Don’t trust specific impulse
Point 2: Total system mass & power
Point 3: Check the sub-components
Check points for microthrusters
Propulsion and Energy Systems; Dec 21st (2015)
Specific impulse
Quite attaractive
Case 1) EP; Isp 3000s, Max Prop. 10 g, Dry M. 5 kg
Case 2) CP; Isp 30s, Max Prop. 1000 g, Dry M. 4 kg
Which is better? Both have the same wet mass, but Case 2 has shorter firing time
Total impulse is the most important
ITotal = Isp * g * MProp
Case 3) Isp 300 s, Max Prop. 1 kg, Dry M. 4 kg
Propulsion and Energy Systems; Dec 21st (2015)
System mass and power
No thruster operate without sub-components
System (total) mass and power are important
Thruster: 10g, Sub-component: 1 kg ??
Few direct drive by satellite bus voltage
Needing PPU (high vol.,DC→AC, etc)
High voltage supplies: 50-90% efficiency
Mcirowave :20-40% efficiency
Gas-feeding system has dominant mass
Does it have a neutralizer?
Propulsion and Energy Systems; Dec 21st (2015)
Sub-components
e.g. ion thruster of HAYABUSA-1/2
Ion thruster by NEC (research by ISAS) Power and system assembling by NEC High-pressure system by MHI
Who is responsible for the microthruster?
Completeness of the subcomponents
Simple subcomponents are merits
Propulsion and Energy Systems; Dec 21st (2015)
Summary
No standard microthrusters
Important: non high-pressure and non toxic
S/C of >20 kg ΔV < 100 m/s → Cold-gas thruster
Pulsed plasma thruster
ΔV > 100 m/s → Ion thruster
S/C of <20 kg ΔV < 10 m/s → Pulsed plasma thruster
Solid microthruster
ΔV > 10 m/s → No candidate
My perspective:
Thank you