Plasma and Nuclear Propulsion
• Thrust is defined as the force generated by an engine or rocket
• For rockets Fthrust = ce*dm; dm = fuel mass flow rate • Specific Impulse measures the efficiency of a rocket engine (not a physical quan ty). • It is effec vely equal to the thrust divided by the amount of fuel used per unit me.
• It is measured by a quan ty called Isp = ce/g
2 Types of Electric Propulsion 1. Electrothermal – uses electricity to heat a neutral gas examples: arcjet
2. Electrosta c – uses a sta c electric field to accelerate a plasma. Sta c magne c field are some mes used to help confine the plasma, but they are not used for accelera on. examples: gridded ion thruster
3. Electromagne c – uses electric and magne c fields to accelerate a plasma. examples: hall thruster, pulsed plasma thruster
3 Electrothermal: Arcjet
How they work: 1. Neutral gas flows through the propellant flow. 2. An electrical arc forms between the anode and cathode. 3. A small amount of the neutral gas is ionized to form the arc. 4. The remaining gas is heated as it passes through the arc. Propellant: Hydrazine Ammonia Exhaust speed: 4-10 km/s Thrust range: 200-1000 mN* Power required: 400 W – 3 kW Efficiency: 30-50%
* 1 mN is about the weight of a sheet of paper. 4 Electrosta c: Gridded Ion Thruster Electrosta c: Gridded Ion Thruster Vital Stats: Propellant: Argon, Krypton, Xenon Exhaust speed: 15-50 km/s Thrust range: 0.01-200 mN* Power 1-10 kW required: Efficiency: 60-80%
* 1 mN is about the weight of a sheet of paper. Advantages: Disadvantages: Uses: 1. High exhaust speed 1. Complex power processing 1. Sta on keeping 2. High efficiency 2. Low thrust 2. Orbital change 3. Inert propellant 3. Grid and cathode life me LEO to GEO issues 3. Primary propulsion 4. High voltages 5. Thrust density is limited 6 Electrosta c: Gridded Ion Thruster
Gridded Ion Thrusters have been flown as the primary propulsion of several satellites: Deep Space 1 (NASA; Braille, Borrelly) Dawn (NASA; Ceres & Vesta) Hayabusa (JAXA; sample from Itokawa)
Deep Space 1’s NSTAR Thruster: 1. Exhaust speed 35 km/s 2. Used 74 kg of Xenon fuel 3. Low thrust (92 mN) over a long me (678 days) 4. Δv due to thruster (4.3 km/s)
DAWN’s Ion Engine: 1. Exhaust speed 31 km/s 2. Low thrust (90 mN) over a long me (longer than DS1) 3. Larger Δv than DS1
7 Electromagne c: Pulsed Plasma Thruster (PPT) How they work: 1. Arc ablates material off the Teflon surface. a. Material is ionzied b. Current flows through the arc. 2. Current generates a magne c field. 3. Magne c field and current interact to accelerate the plasma. Propellant: Solid Teflon Exhaust speed: 6 - 20 km/s Thrust range: 0.05 - 10 mN* Power required: 5 -500 W Efficiency: 10%
* 1 mN is about the weight of a sheet of paper. 8 Electromagne c: Pulsed Plasma Thruster (PPT) Advantages: 1. Simple design 2. Low power 3. Solid fuel a. No propellant tanks/plumbing b. No zero-g effects on propellant
Disadvantages: 1. Low thrust 2. Low efficiency 3. Toxic products
Uses (flown in space): Sta on keeping Precision poin ng 9 Electromagne c: Hall Thruster How they work: 1. Cathode releases electrons which ionize propellant. 2. Electrons from ioniza on move in a circular pa ern (create current). 3. Current interacts with radial magne c field to produce ion accelera on. 4. Cathode electrons neutralize the beam. Propellant: Xenon or Argon Exhaust speed: 15 - 20 km/s Thrust range: 0.01 - 2000 mN* Power required: 1 W - 200 kW Efficiency: 30-50%
* 1 mN is about the weight of a sheet of paper. 10 Electromagne c: Hall Thruster
Advantages: 1. High exhaust velocity 2. Simple power supply 3. Inert propellant 4. High efficiency 5. Desirable exhaust velocity
Disadvantages: 1. High beam divergence 2. Life me issues (erosion)
Uses (flown in space): Sta on keeping Orbital transfer (LEO to GEO) Primary Propulsion (SMART-1) 11 Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
How it works (VX-200): 1. Helicon ionizes neutral gas (30 kW). 2. Plasma flows along field lines and is compressed. 3. Ion Cyclotron Resonance Hea ng (ICRH) is used to heat the ions (170 kW). 4. Magne c nozzle converts temperature into directed flow. 5. Plasma detaches from the magne c field. VASIMR
Advantages: 1. Variable exhaust speed 2. High exhaust speed 3. Variable thrust 4. High thruster 5. No grids or anode/cathode 6. Variety of fuels (H, Ar, Ne) Disadvantages: 1. Superconduc ng magnets required 2. Poten al detachment issues 3. Poten al energy conversion issues 4. Requires nuclear reactor EP Summary Types of EP: Electrothermal: resistojet, arcjet Electrosta c: gridded ion thruster Electromagne c: Hall thruster, PPT, MPD thruster, VASIMR
Advantages: High exhaust velocity High propellant efficiency High spacecra speeds
Disadvantages: Power intensive Very low thrust (in space only) Accelera on takes me Poten al life me issues
15 Radioisotope Thermal Generator (RTG):
How they work: Addi onal informa on: • Radioac ve decay (o en 238Pu) • 10s-100s of Wa s • Heat generated in decay • 3-7% efficient • Thermocouples convert heat to • Well suited to deep space robo c electricity missions • US has Flown 45 RTGs in 25 missions • Voyager 1& 2 • Cassini (870 W - shown le ) • Galileo (570 W) • Viking 1 & 2 • Pioneer • Ulysses
Radioac ve Heater Units: • 1 Wa of heat power • Used to keep spacecra warm • US has flown more than 240
RTGs have a good service history, but are still controversial. 16 Nuclear Propulsion
Now we’re really ge ng into the border of science fic on. However, real research is being done or has been done to seriously inves gate several nuclear propulsion concepts.
Types of nuclear propulsion: 1. Nuclear pulse propulsion – uses nuclear explosions to propel a spacecra
2. Nuclear thermal propulsion – uses the heat of a nuclear reactor to heat a gas which is expelled for thrust
3. Nuclear electric propulsion – uses electrical power from a nuclear reactor to power an electric thruster 17 Nuclear Pulse Propulsion Also called external pulsed plasma propulsion. Uses nuclear explosions to generate thrust.
Programs: 1. Project Orion (1958 – 1963) 2. Project Daedalus (1973 – 1978) 3. Project Longshot (1987-1988)
18 Project Orion
Study by General Atomics led by Ted Taylor and Freeman Dyson Goal: High thrust with high exhaust speeds
How it works: 1. Drop nuclear bomb out the back of the spacecra 2. Nuclear bomb detonates about 60 m behind the spacecra 3. Explosion hits a steel plate, which propels the spacecra forward.
Note: shock absorber is required for human payload due to the high g involved.
19 Project Orion Performance: Es mated thrust > 1 mega-newton Es mated exhaust velocity: 20 – 30,000 km/s Es mated spacecra speed: 0.03c – 0.1c (c = speed of light) Poten al Missions: Fast travel through solar system with massive payloads Single stage to Mars Saturn’s moons Jupiter’s moons Poten al Problems: Asteroid deflec on Plate abla on/damage Interstellar travel Nuclear fallout on Earth High accelera on rate Project Orion was terminated by the Crew shielding Par al Test Ban Treaty of 1963. 20 Orion
21 Commercializing Human Space Flight New Commercial Space
• NASA COTS/CRS • Space Tourism – Orbital Sciences – Bigelow Aerospace – SpaceX – Space Adventures • NASA CCDev Partners – Virgin Galac c – Blue Origin – XCor – Boeing – Paragon – Sierra Nevada – United Launch Alliance Falcon 1/1e: • 2 stages: LOX-Kerosene • 670 kg (1010 kg) to LEO • Achieved orbit: Sept., 28, 2008 • 2/5 successes • $10.9 M Falcon 9: • 2 stages: LOX-Kerosene • 10,450 kg to LEO • 4,540 kg to GTO • Dragon Capability • Maiden Flight: June 4, 2010 Placed test payload in orbit • Cost: $45.8 – $55.1 M • Flight 2: Tuesday, Dec 7, 2010 – First Dragon test flight – First private company to return a capsule from orbit. • Next launch with docking to ISS soon (5/19?)