 Painting ofUlysses deploying from the Space Shuttle | |
| Manufacturer | Boeing United Technologies |
|---|---|
| Country of origin | United States |
| Used on | Space Shuttle Titan 34D Titan IV |
| General characteristics | |
| Height | 5.2 m (17 ft)[1] |
| Diameter | 2.8 m (9 ft 2 in) |
| Gross mass | 14,700 kg (32,400 lb) |
| Associated stages | |
| Derivatives | TOS |
| Launch history | |
| Status | Retired |
| Total launches | 24 |
| Successes (stage only) | 21 |
| Failed | 2 |
| Lower stage failed | 1 |
| First flight | 30 October 1982 |
| Last flight | 14 February 2004[2] |
| First stage | |
| Height | 3.15 m (10.3 ft)[3] |
| Diameter | 2.34 m (7 ft 8 in)[3] |
| Gross mass | 10,400 kg (22,900 lb)[3] |
| Propellant mass | 9,700 kg (21,400 lb)[1] |
| Powered by | Orbus-21 |
| Maximum thrust | 190 kN (43,000 lbf)[1] |
| Specific impulse | 295.5 s (2.898 km/s)[3] |
| Burn time | up to 150 seconds[1] |
| Propellant | Solid |
| Second stage | |
| Height | 1.98 m (6 ft 6 in)[3] |
| Diameter | 1.60 m (5 ft 3 in)[3] |
| Gross mass | 3,000 kg (6,600 lb) |
| Propellant mass | 2,700 kg (6,000 lb)[1] |
| Powered by | Orbus-6 |
| Maximum thrust | 80 kN (18,000 lbf)[1] |
| Specific impulse | 289.1 s (2.835 km/s)[3] |
| Propellant | Solid |
TheInertial Upper Stage (IUS), originally designated theInterim Upper Stage, was atwo-stage,solid-fueled space launch system developed byBoeing for theUnited States Air Force beginning in 1976[4] for raising payloads fromlow Earth orbit to higher orbits or interplanetary trajectories following launch aboard aTitan 34D orTitan IV rocket as itsupper stage, or from the payload bay of theSpace Shuttle as aspace tug.
During the development of the Space Shuttle, NASA, with support from the Air Force, wanted an upper stage that could be used on the Shuttle to deliver payloads from low earth orbit to higher energy orbits such asGTO orGEO or to escape velocity for planetary probes. The candidates were theCentaur, propelled by liquid hydrogen and liquid oxygen, theTranstage, propelled byhypergolic storable propellantsAerozine-50 anddinitrogen tetroxide (N2O4), and the Interim Upper Stage, using solid propellant. TheDOD reported that Transtage could support all defense needs but could not meet NASA's scientific requirements, the IUS could support most defense needs and some science missions, while the Centaur could meet all needs of both the Air Force and NASA. Development began on both the Centaur and the IUS, and a second stage was added to the IUS design which could be used either as anapogee kick motor for inserting payloads directly into geostationary orbit or to increase the payload mass brought to escape velocity.[5]
Boeing was the primary contractor for the IUS[6] while Chemical Systems Division ofUnited Technologies built the IUS solid rocket motors.[7]
When launched from the Space Shuttle, IUS could deliver up to 2,270 kilograms (5,000 lb) directly to GEO or up to 4,940 kilograms (10,890 lb) toGTO.[3]
The first launch of the IUS was in 1982 on a Titan 34D rocket from theCape Canaveral Air Force Station shortly before theSTS-6 Space Shuttle mission.[8]
Development of the Shuttle-Centaur was halted after theChallenger disaster, and the Interim Upper Stage became the Inertial Upper Stage.
The solid rocket motor on both stages had a steerable nozzle for thrust vectoring. The second stage hadhydrazine reaction control jets for attitude control whilst coasting, and for separation from payload.[9] Depending on mission, one, two or three 54 kg (120 lb) tanks of hydrazine could be fitted.[9]
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On Titan launches, the Titan booster would launch the IUS, carrying the payload into low Earth orbit where it was separated from the Titan and ignited its first stage, which carried it into an elliptical "transfer" orbit to a higher altitude.
On Shuttle launches, the orbiter's payload bay was opened, the IUS and its payload raised (by theIUS Airborne Support Equipment (ASE)) to a 50-52° angle, and released.[9] After the Shuttle separated from the payload to a safe distance, the IUS first stage ignited and, as on a Titan booster mission, entered a "transfer orbit".
Upon reaching apogee in the transfer orbit, the first stage and interstage structure were jettisoned. The second stage then fired to circularize the orbit, after which it released the satellite and, using its attitude control jets, began a retrograde maneuver to enter a lower orbit to avoid any possibility of collision with its payload.
In addition to the communication and reconnaissance missions described above, which placed the payload into stationary (24-hour) orbit, the IUS was also used to boost spacecraft towards planetary trajectories. For these missions, the second IUS stage was separated and ignited immediately after first stage burnout. Igniting the second stage at low altitude (and thus, high orbital speed) provided the extra velocity the spacecraft needed to escape from Earth orbit (seeOberth effect). IUS could not impart as much velocity to its payload as Centaur would have been able to: while Centaur could have launched Galileo directly on a two-year trip to Jupiter, the IUS required a six-year voyage with multiple gravity assists.[10]
The final flight of the IUS occurred in February 2004.[2]
| Serial number[11] | Launch date | Launch vehicle | Payload | Remarks | Image |
|---|---|---|---|---|---|
| 2 | 1982-10-30 | Titan 34D | DSCS II F-16/III A-1 | Mission successful despite telemetry loss for most of the flight. | |
| 1 | 1983-04-04 | Space Shuttle Challenger (STS-6) | TDRS-A (TDRS-1) | The second stage tumbled due to a thruster motor problem, resulting in an incorrect orbit. The Boeing staff that was monitoring the flight was able to separate the tumbling IUS from the satellite so it could be maneuvered into its final orbit. |  |
| 11 | 1985-01-24 | Space Shuttle Discovery (STS-51-C) | USA-8 (Magnum) | Classified DoD payload[12] | |
| 12 | 1985-10-03 | Space Shuttle Atlantis (STS-51-J) | USA-11/12 (DSCS) | DoD payload. Declassified in 1998.[13] |  |
| 3 | 1986-01-28 | Space Shuttle Challenger (STS-51-L) | TDRS-B | Destroyed during launch[14] | |
| 7 | 1988-09-29 | Space Shuttle Discovery (STS-26) | TDRS-C (TDRS-3) |  | |
| 9 | 1989-03-13 | Space Shuttle Discovery (STS-29) | TDRS-D (TDRS-4) | ||
| 18 | 1989-05-04 | Space Shuttle Atlantis (STS-30) | Magellan | Probe toVenus. Only one tank of hydrazine.[9] |  |
| 8 | 1989-06-14 | Titan IV (402) A | USA-39 (DSP) | ||
| 19 | 1989-10-18 | Space Shuttle Atlantis (STS-34) | Galileo | Probe toJupiter |  |
| 5 | 1989-11-23 | Space Shuttle Discovery (STS-33) | USA-48 (Magnum) | Classified DoD payload[12] | |
| 17 | 1990-10-06 | Space Shuttle Discovery (STS-41) | Ulysses onPAM-S | Probe to the polar regions of theSun |  |
| 6 | 1990-11-13 | Titan IV (402) A | USA-65 (DSP) | ||
| 15 | 1991-08-02 | Space Shuttle Atlantis (STS-43) | TDRS-E (TDRS-5) |  | |
| 14 | 1991-11-24 | Space Shuttle Atlantis (STS-44) | USA-75 (DSP) | ||
| 13 | 1993-01-13 | Space Shuttle Endeavour (STS-54) | TDRS-F (TDRS-6) |  | |
| 20 | 1994-12-22 | Titan IV (402) A | USA-107 (DSP) | ||
| 26 | 1995-07-13 | Space Shuttle Discovery (STS-70) | TDRS-G (TDRS-7) | ||
| 4 | 1997-02-23 | Titan IV (402) B | USA-130 (DSP) | ||
| 21 | 1999-04-09 | Titan IV (402) B | USA-142 (DSP) | IUS first and second stages failed to separate, payload placed into useless orbit | |
| 27 | 1999-07-23 | Space Shuttle Columbia (STS-93) | Chandra X-ray Observatory | Last launch of a payload using IUS on a Space Shuttle. |  |
| 22 | 2000-05-08 | Titan IV (402) B | USA-149 (DSP) | ||
| 16 | 2001-08-06 | Titan IV (402) B | USA-159 (DSP) | ||
| 10 | 2004-02-14 | Titan IV (402) B | USA-176 (DSP) |
Boeing won the contract to develop the IUS in 1976...
They argued that the IUS, which was designed by the Air Force, was a potentially better rocket. The first stage of the two-stage rocket was capable of launching medium-sized payloads at most. This limitation would be overcome by means of the addition of a second stage for larger payloads with destinations into deeper space. Specifically, the Air Force asked NASA to develop an additional stage that could be used for planetary missions such as a proposed probe to Jupiter called Galileo.
The IUS is 17 feet long and 9.25 ft. in diameter. It consists of an aft skirt; an aft stage solid rocket motor (SRM) containing approximately 21,400 lb. of propellant and generating approximately 42,000 lb. of thrust; an interstage; a forward stage SRM with 6,000 lb. of propellant generating approximately 18,000 lb. of thrust; and an equipment support section. - The equipment support section contains the avionics, which provide guidance, navigation, control, telemetry, command and data management, reaction control and electrical power. All mission-critical components of the avionics system, along with thrust vector actuators, reaction control thrusters, motor igniter and pyrotechnic stage separation equipment are redundant to assure better than 98 percent reliability. - The IUS two-stage vehicle uses both a large and small SRM. These motors employ movable nozzles for thrust vector control. The nozzles provide up to 4 degrees of steering on the large motor and 7 degrees on the small motor. The large motor is the longest thrusting duration SRM ever developed for space, with the capability to thrust as long as 150 seconds. Mission requirements and constraints (such as weight) can be met by tailoring the amount of propellant carried.