Kaiser Marquardt
KAISER MARQUARDT
16555 Saticony Street,
Van Nuys, California
91406-1739
Telephone: (818) 989-6400
Fax: (818) 994-2947
A 110 N hypergolic thruster was developed as the Space Shuttle Orbiter's
vernier attitude control and orbit adjust thruster. There are six employed
in conjunction with the 38 3870 N R-40 thrusters.
| Applications | Shuttle Orbiter Vernier,
satellite orbit adjust |
| First Flown | April 1981 on Columbia |
| Dry Mass | 3.7 kg |
| Length | 279 mm, 312 mm satellite version |
| Maximum Diameter | 15.2 cm satellite version, 14 cm Shuttle
version |
| Mounting | fixed |
| Engine Cycle | pressure-fed at 15 atm (range 6.8-27.2
atm) |
| Oxidizer | nitrogen tetroxide at 0.0256 kg/sec |
| Fuel | monomethyl hydrazine at 0.0354 kg/sec |
| Mixture Ratio(O/F) | 1.65 (range 1-2.7) |
| Thrust | 110 N (range 67-155.7 N) |
| Isp | 280 sec vacuum |
| Combustion Chamber | single chamber |
| Expansion Ratio | min ratio of 26 with orthogonal and
scarfed nozzles. |
| Combustion Chamber Construction | made of silicide-coated
columbium (niobium) and insulated for buried installation. |
| Ignition | started by electrical signal to on/off solenoid
valve. Single doublet injector with hypergolic ignition. |
| Burn Time | min 82,000 secs demonstrated. 0.89 Ns min
impulse bit |
Developed as an attitude control thruster for the Apollo's Service and
Lunar Module. Each unit for the modules employed four quadruple clusters.
Approximately 800 were built. The thruster is currently employed in the
R-4D-10 version of the U.S. Navy's Leasat, R-4D-11 by Insat 1 and Arabasat
1, R-4D-12 by HS-393, Milstar, Intelsat 6, Italsat, and Olympus and
Eurostar.
| Application | apogee/perigee maneuvers,
orbit adjust, and attitude control |
| First Flown | February 1966 (Apollo 201) |
| Number Produced | about 800 |
| Dry Mass | 3.63 kg |
| Length | 55.41 cm |
| Maximum Diameter | 27.94 cm |
| Mounting | fixed |
| Engine Cycle | pressure-fed |
| Propellants | hypergolic nitrogen tetroxide and MMH or
hyrdazine which was pressure-fed at 0.05 kg/sec fuel and 0.091 kg/sec
oxidizer at atm |
| Mixture Ratio | 1.65 (1.0 - 2.4 range) |
| Thrust | 490 N vacuum standard |
| Isp | 312 sec vacuum standard |
| Expansion Ratio | 164:1 |
| Chamber Pressure | 6.84 atm |
| Combustion Chamber | a single chamber/nozzle of welded
coated columbium (niobium), radiatively and film-cooled, controlled by an
on/off solenoid, and a multiple doublet injector with hypergolic
ignition. |
| Burn Time | up to 1 hour continuous with a 2.67 Ns min
impulse bit |
A derivative of an Advent Communications satellite thruster in the
1960s, the 6C was qualified in 1981 for the Insat 1, Arbasat 1, and Olympus
and HS-393-type satellites.
| Applications | satellite AOCS |
| Dry Mass | 0.66 kg |
| Length | 251.6 mm |
| Mounting | fixed |
| Engine Cycle | pressure-fed |
| Oxidizer | nitrogen tetroxide at 0.005 kg/sec at 15-17
atm |
| Fuel | MMH at 0.003 kg/sec at 15-17 atm |
| Mixture Ratio(O/F) | 16(0.1 |
| Thrust | 22 N (range 6.2-32.9 N). R-6C-2.2 version operates
at 100 N nominal |
| Isp | 290 sec vacuum at 22 N thrust |
| Exit Diameter | 55.9 mm |
| Expansion Ratio | 100:1 |
| Combustion Chamber | a single chamber of silicide-coated
columbium (niobium). Pressure 6.84 atm. Started by electrical signal to
on/off solenoid valve. Also has a multiple doublet injector with
hypergolic ignition. |
This thruster was developed for Shuttle Orbiter orbit control. The
vehicle carries 38 in long scarf, short scarf, or no scarf configurations.
Depending on the location of it.
| Applications | spacecraft orbital
maneuvering, perigee kick engine |
| First Flown | April 1981 on the Columbia |
| Dry Mass | 10.25 kg |
| Length | 55.4 cm short scarf version, 103.9 cm for the long
scarf, and 88.9 cm for the satellite version with 100:1 expansion
ratio |
| Maximum Diameter | 30.9 cm long scarf version, and 51.8 cm
for the satellite version with 100:1 expansion ratio |
| Mounting | fixed |
| Engine Cycle | pressure-fed |
| Oxidizer | nitrogen tetroxide at 0.838 kg/sec at 16.4
atm |
| Fuel | MMH at 0.52 kg/sec at 16.4 atm |
| Mixture Ratio(O/F) | 1.6 |
| Thrust | 3870 N (range 3114 - 5338 N) |
| Isp | 281 sec (306 sec for 120 expansion ratio) |
| Expansion Ratio | 20 (40 - 150 available for satellite
version) |
| Exit Diameter | 267 mm (328 - 635 mm for satellite
version) |
| Chamber Pressure | 10.5 atm |
| Combustion Chamber | single chamber of silicide-coated
columbium (niobium) with welded-on orthogonal and scarfed nozzle extension
in same material with internal film cooling. Exterior insulated for buried
installation. Started by electrical signal to on/off solenoid valve.
Multiple doublet injector with hypergolic ignition. |
| Burn Time | max 500 sec for single burn, qualified to 15,319
sec life; 289 Ns min impulse bit. |
United Technologies (UTC) Hamilton Standard Division's hyrazine thruster
line was acquired by Kaiser Marquardt in 1993. The world's largest supplier
of catalytic hydrazine thrusters and propulsion systems, the company
delivered more than 80 monopropellant systems to various companies and
organizations. The higher power motors, of the low thrust versions, are
used for precession, despin, and (V maneuvers, while the 0.89 N versions
are used for wheel desaturation, North-South/East-West stationkeeping and
precise attitude control. The mid-range thrusters, on the other hand, are
used for major (V maneuvers and atmosphereic drag make-up.
| REA 10 | 0.89 N |
| REA 17-6 | 2.22 N |
| REA 17-12 | 4.45 N |
| REA 16 | 22.2 N |
| REA 39-2 | 22.2 N |
| REA 22-5 | 53.4 N |
| REA 22-2 | 91.6 N |
| REA 22-16 | 133.4 N |
| REA 22-17 | 177.9 N |
| REA 20-4 | 556 N |
ASI W9800153r1.2.
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