Transcript Lesson 11: Hybrid Propulsion System Basics

Lesson 12: Hybrid Propulsion
System Design
Dr. Andrew Ketsdever
Hybrid Ballistics
Hybrid Ballistics
• Fuel is vaporized as a result of heat transferred from the
flame zone to the fuel grain
– Convection
– Radiation
• Vaporized fuel and oxidizer mix in the port
• The flame is established at a location within the
boundary layer determined by stoichiometric conditions
Hybrid Ballistics
Hybrid Propulsion Design Process
• Start by establishing
mission requirements
• Preliminary Design
– Make Preliminary Decisions
• Propellants
• Number of ports
• Port configuration
– Estimate Performance
• Simulations – Codes
• Design meets requirements?
– Size/Configure Components
Preliminary Design Decisions
• Choose Propellants
– Usual combination
• Solid Fuel / Liquid Oxidizer
– Choose a design O/F
• O/F varies
• Decreases down port
• Increases with time
– Evaluate Thermochemistry
• Code / Appendix B (SPAD)
• g, mw, To, c*
Example: O/F Variation with Time
•
•
•
•
HTPB / LOx
Rp, i = 7 cm
Gox = 350 kg/m2 sec
Po = 3.45 MPa
Time (s)
0
10
30
50
O/F
1.72
2.01
2.33
2.53
Isp (s)
249.4
254.7
254.3
252.1
Example: Continued
• O/F = 2.13 for
maximum Isp (255.1
sec)
• In example, O/F
ranges from 1.72 to
2.53 over the 50 sec
burn
– 20% variation from
ideal O/F
• Average Isp = 253.9
sec (0.5% less than
max)
Preliminary Design
• Determine Pressure Levels
– Combustion chamber pressure determined by
performance characteristics
• Thrust, Isp
– Two pressure systems
• Pressurant-fed
• Pump-fed
• Design of these systems similar to liquid propulsion system
designs
– DPlosses must be considered
• Feedlines, dynamic pressure, injectors
Preliminary Design
• Determine the Initial Propellant Flow
– Thrust requirement
– O/F ratio must be selected
– Isp estimated (thermochemistry code)
– Mass flow rates can be calculated
• Oxidizer
• Fuel
Preliminary Design
• Configure the
Combustion Ports
– Number
– Configuration
– Depends on thrust (mass
flow, burn area) required
– Optimize volumetric
loading
– Reduce left over (unburnt)
propellant
• Volumetric Loading
SolidFuelV olume
V 
TotalGrain Volume
Motor Parameters
• MS Word File…
GIRD-09
• Manufacturer: Korolev. Apogee: 5 km. Liftoff Thrust: 30
kgf. Total Mass: 18 kg. Core Diameter: 0.17 m. Total
Length: 2.46 m. Span: 0.63 m.
• The first rocket successfully launched by the Soviet
GIRD organization was a hybrid (1933).
• Used a liquid oxygen to burn gelled petroleum in large
casing.
• 1933 Aug 17 - Russian hybrid propellant rocket,
designed by M. K. Tikhonravov, successfully flown.
Reached 400 m; design altitude of 5000 m not reached
due to loss of pressure integrity of the motor flank.
Dolphin
• Manufacturer: AMROC. Launches: 1.
Failures: 1. Success Rate: 0.000 pct. First
Launch Date: 3 August 1984. Last Launch
Date: 3 August 1984. Launch data is:
complete. Apogee: 2 km. Liftoff Thrust:
155.00 kN. Total Mass: 7,500 kg. Core
Diameter: 1.07 m. Total Length: 15.50 m.
• Started with Private Funds – After the
failed first launch due to TVC the venture
folded.
• A sea launch arrangement was used for
lift-off - the booster floated in the ocean
separately from the launch support ship.
HYSR
• Manufacturer: Lockheed Martin. Launches: 1. First Launch
Date: 18 December 2002. Last Launch Date: 18 December
2002. Apogee: 70 km. Liftoff Thrust: 27,000 kgf. Core
Diameter: 0.20 m. Total Length: 6.00 m.
• In 1999 Lockheed Martin signed a Space Act Agreement
with NASA Marshall Space Flight Center to develop, test
and launch the hybrid sounding rocket.
• The program goal was to develop a single-stage hybrid
propulsion system capable of replacing existing two- and
three-stage sounding rockets.
• Hybrid propulsion offered significant advantages over solid
fuel propellants in that hybrids were non-explosive, could
be throttled, and were low cost and environmentally benign.
SpaceShipOne
•
Binnie Date: 4 October 2004 14:49 GMT. . Landing Date: 4 October
2004. Flight Time: 0.017 days. Flight Up: SpaceShipOne Flight 17P.
Flight Back: SpaceShipOne Flight 17P. Program: X-Prize. Firsts:
Suborbital altitude record for a manned spaceplane.
• Sixth powered flight of Burt Rutan's SpaceShipOne and winner of
the $10 million X-Prize by becoming the second flight over 100 km
within a week.
• Objectives of the flight were to win the Ansari X-Prize and break the
rocketplane altitude record set by the X-15 in 1963. The Tier One
(White Knight/SpaceShipOne) composite aircraft took off at 06:49
PST. Drop of the rockeplane was made exactly one hour later at
14.4 km altitude. Pilot Brian Binnie fired the hybrid rocket motor,
which burned for 83 seconds. The engine cut off with
SpaceShipOne at Mach 3.09 (3524 kph) at 65 km altitude. From
there it coasted to 112 km altitude. The spacecraft reached Mach
3.25 G's during re-entry and a peak deceleration of 5.4 G's at 32 km
altitude.
• 2004 Oct 4 - SpaceShipOne Flight 17P - X-Prize Flight 2 Flight
Crew: Binnie, Spacecraft: SpaceShipOne. Nation: USA. Launch
Site: Mojave . Launch Vehicle: Tier One. Duration: 0.017 days.
Apogee: 112 km.
SpaceDev Hybrid
• Designer: SpaceDev. Developed in: 20012004. Application: Rocketplane boost.
Gross Mass: 2,700 kg. Empty Mass: 300
kg. Propellants: N2O/Solid Thrust(vac):
7,500 kgf. Isp: 250 sec. Burn time: 80 sec.
Chambers: 1. Chamber Pressure: 24.00
bar. Country: USA. Status: Hardware.
Falcon: Recent Test
•
2/4/2005 - EDWARDS AIR FORCE BASE, Calif. (AFPN) -- A large hybrid rocket
motor was successfully fired on its test stand.
•
The test took place on a Air Force Research Laboratory test stand overlooking
Edwards’ dry lake bed and surrounding Mojave Desert. The test was part of the Air
Force small launch vehicle office’s Falcon program.
•
The program is a 36-month long effort to develop and demonstrate an affordable and
responsive space lift launcher capable of placing a small, 1,000-pound satellite into a
circular orbit of 100 nautical miles.
•
The research site encompasses 65 square miles of Edwards AFB. Its unique
research and development facilities provide state-of-the-art capabilities for
researchers who provide the nation with the latest rocket propulsion technology
possible.