TheStar is a family ofUSsolid-propellant rocket motors originally developed byThiokol and used by many space propulsion and launch vehiclestages. They are used almost exclusively as upper stages, often asapogee kick motors. The number designations refer to the approximate diameter of the fuel casing in inches.

Three Star 37 stages, and one Star 48 stage,were launched on solar escape trajectories; fast enough to leave the Sun's orbit and out into interstellar space, where barring the low chance of colliding with debris, they will travel past other stars in theMilky Way galaxy and survive potentially intact for millions of years.

TheStar 13 (TE-M-458) is a solid fuelapogee kick motor.^[1][2] It was used on NASA'sAnchored Interplanetary Monitoring Platform satellites.^[3] Several other versions were developed.^{[1][4][5][6][7][8][9][2]}Star 13D (TE-M-375) was used on theSyncom 1,Star 13A (TE-M-516) onLES 1/2, Aurora (P67-1), Orbiscal (P68-1),Lincoln Calibration Sphere 4, S3-2,Solrad 11A/B, SPX plume generator package,Freja, Meteor andEquator-S,Star 13C (TE-M-345-11/12) onAMSAT P3A andStar 13B (TE-M-763) onAMPTE-CCE payloads.^[3]

TheStar 17 (TE-M-479) is a solid fuelapogee kick motor, first launched in 1963.^[10] It was used for payloads such asRadio Astronomy Explorer,SOLRAD and S3 satellites. TheStar 17A (TE-M-521-5) version was used for orbit circularization onSkynet 1, NATO 1,IMP-H andIMP-J satellites.^[10][11]

TheStar 20 (TE-M-640) is a solid fuelapogee kick motor, also known as Altair-3A.^[12] It was used as a second stage on anAtlas-E/F vehicle launching Stacksat.^[13][14] The TE-M-640 motor is similar toAltair 3 (FW-4S), and both are designated by NASA as Altair IIIA.^[15]

TheStar 24 (TE-M-604) is a solid fuelapogee kick motor, first qualified in 1973.^[16][17] It burns an 86% solidscarboxyl-terminated polybutadiene (CTPB)-based composite propellant.^[16][18] The "24" designation refers to the approximate diameter of the Titanium fuel casing in inches.^[16]

TheStar 26 (Burner 2A or TE-M-442) is an upper stage motor used in Burner II stage of theSandiaStrypi IV vehicle introduced in 1965.^[22] TheStar 26B (TE-M-442-1) variant was used on theThor-LV2F Burner-2A launcher.^[23]Star 26C (TE-M-442-2) was used on the DOT sounding rocket.^[24][25]

Star 27

A Star 27H kick motor forIBEX
Country of origin	United States
Solid-fuel motor

TheStar 27 is a solid apogee kick motor, with the 27 representing the approximate diameter of the stage in inches.^[26][27] It burnsHTPB-based composite propellant with an average erosion rate of 0.0011 inches per second (0.028 mm/s).^[28][26]

It as used as a second stage on a version of theAtlas E/F rocket, launching theSolwind andGeosat satellites.^[29] When used on thePegasus air-launch rocket payloads are capable of leaving Earth orbit.^[26]

A version of the Star 27, designated theStar 27H,^[30] was used in the launch of theIBEX spacecraft.^[31] The spacecraft had a mass of 105 kg by itself and together with its Star 27H motor, 462 kg.^[31] The Star 27H helped it get to a higher orbit, beyond Earth's magnetosphere.^[31]

TheStar 30 (TE-M-700-2) is a solid fuel motor, with the 30 representing the approximate diameter of the stage in inches.^[37] Different versions (A, B, C, E and BP) were used as an apogee motor for satellites such as G-STAR,Skynet 4,Koreasat or theHS-376 satellite bus.^[37] Star 30E was used by the smallORBEX orbital launcher.^[37] A Star 30 booster was also used on theCONTOUR comet probe.^[38]

TheStar 31 (also known asAntares 1A orX-254) is a solid fuel motor, with the 31 representing the approximate diameter of the stage in inches.^[44] It had a thrust of 60.50 kN and a mass of 1225 kg.^[44] It was used as a stage on theWASP missile,Scout X,Scout X-1,Blue Scout Junior,Blue Scout I,Blue Scout II,Scout X-1A and RAM B.^[44]

Star 37

Star 37E (TE-M-364-4)
Country of origin	United States
Date	1963-present
Manufacturer	Thiokol
Application	Upper stage/Spacecraft propulsion
Predecessor	Star 27
Successor	Star 48
Status	Active
Solid-fuel motor
Configuration
Chamber	1
Performance
Thrust, vacuum	33.600 kN (7,554 lbf)
Specific impulse, vacuum	(161,512 N•s/kg)
Dimensions
Length	2.27 m (7.44 ft)
Diameter	0.66 m (2.16 ft)
Empty mass	113 kg (249 lb)
Used in
Upper stage onThor andDelta

TheStar 37 was first used as the engine for theThor-Burner upper stage in 1965. TheBurner I used the Thiokol FW-4 engine and theBurner II used the Thiokol TE-M-364-2.^[45]

The "-37" designation refers to the approximate diameter of the titanium fuel casing in inches; Thiokol had also manufactured other motors such as the Star 40 andStar 48. Internally, Thiokol's designation was TE-M-364 for early versions, TE-M-714 for later ones, and TE-M-783 for a specialHTPB model used forFLTSATCOM launches.

Subtypes are given one or more letter suffixes after the diameter number, or a trailing number (i.e., "-2") after the internal designation. Not surprisingly, the "T" prefix stands for Thiokol, and the following letter refers to the company division that developed the rocket motor. In this case, "M" refers to the Magna, UT Division. "E" refers to the Elkton, MD division.

The Star 37FM rocket motor was developed and qualified for use as an apogee kick motor on FLTSATCOM. The motor is a replacement for the Star 37E Delta, which has been discontinued. The Nozzle assembly uses a 3Dcarbon-carbon throat and a carbon-phenolic exit cone. Maximum propellant weight is 2,350 pounds (1,070 kg), while the motor has been qualified for propellant off-loading to 2,257 pounds (1,024 kg).

Aspin-stabilized (Star 37FM) orthrust-vectoring (Star 37FMV) version of Star 37 is used as the final stage of theMinotaur V launch vehicle.^[46][47]

ThePioneer 10 &11, andVoyager 1 &2 Propulsion Modules used Star 37E motors; each is now on asimilar interstellar trajectory to its companion probe, and is set to leave the Solar System (except the Pioneer 11 stage, which is thought to have remained in solar orbit^[48]).

Star 48

Star-48B rocket motor
Country of origin	United States
Date	1982 - present
Manufacturer	Thiokol
Predecessor	Star 37
Solid-fuel motor

TheStar 48 is a type ofsolid rocket motor developed primarily byThiokol Propulsion, which was purchased byOrbital ATK in 2001. In 2018, Orbital ATK in turn was acquired byNorthrop Grumman.

The "48" designation refers to the approximate diameter of the fuel casing in inches; Thiokol had also manufactured other motors such as theStar 37 and Star 30. Internally, Thiokol's designation was TE-M-711 for early versions, and TE-M-799 for later ones. Subtypes are given one or more letter suffixes after the diameter number, or a trailing number (i.e., "-2") after the internal designation. The "T" prefix stands for Thiokol, and the following letter refers to the company division that developed the rocket motor. In this case, "E" refers to the Elkton, MD division and the "M" stands for motor.

The most common use of the Star 48 was as the final stage of theDelta II launch vehicles. Other launchers such asULA'sAtlas 551 have also incorporated the motor, but with lower frequency. On board theSpace Shuttle, the complete stage (motor plus accessories) was referred to as thePayload Assist Module (PAM), as the Shuttle could only take satellites tolow Earth orbit. Becausegeostationary orbit is much more lucrative, the additional stage was needed for the final leg of the journey. On such missions, the stage wasspin-stabilized. A turntable, mounted in the shuttle payload bay or atop the previous Delta stage, spun the PAM and payload to approximately 60 rpm prior to release.

Usually after motor burnout and just prior to satellite release the spin is canceled out using ayo-yo de-spin technique.

A non-spinning,thrust-vectoring version is known as theStar 48BV, which had its design based off of the Star 48B.^[49] It is available, but much less common. A Star 48BV is the final stage of theMinotaur IV+ launch vehicle.

A Star 48B motor used in the 3rd stage of theNew Horizons probe was the first part of the New Horizons mission to reachJupiter, crossingPluto's orbit in 2015 at a distance of 200 million kilometers.^[50] It is now set to leave the Solar System, traveling on asimilar interstellar trajectory to its companion probe for the indefinite future.

In 2013 aStar 48GXV was tested for theParker Solar Probe mission as the upper stage on anAtlas V 551 vehicle,^[51] but the development was canceled, in favor of aDelta IV Heavy / Star 48BV combination. The Star 48GXV boasted a carbon composite casing and nozzle, enabling it to operate at triple the chamber pressure of an ordinary Star 48. It also featured electro-mechanical actuators togimbal the nozzle, along with digital flight controls.^[52]

TheStar 63 is a solid fuel motor, with the 63 representing the approximate diameter of the stage in inches. Different versions exist:Star 63D (used onPAM-D2), Star 63DV andStar 63F.^[53][54] It was used to launch payloads from theSpace Shuttle, and as stage on theTitan 34D andDelta 7925 rockets.^[53][54]

• Star 37 motors

• Astronautix - Star 27
• Solid Propellant Rocket FundamentalsArchived 2012-06-19 at theWayback Machine (Pages 417–418)

• Rocket stages
• Solid-fuel rockets
• Alliant Techsystems

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