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The Star is a family of US solid-propellant rocket motors originally developed by Thiokol and used by many space propulsion and launch vehicle stages. They are used almost exclusively as an upper stage, often as an apogee kick motor. 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 the Milky Way galaxy and survive potentially intact for millions of years.

Star 13

The Star 13 (TE-M-458) is a solid fuel apogee kick motor. It was used on NASA's Anchored Interplanetary Monitoring Platform satellites. Several other versions were developed. Star 13D (TE-M-375) was used on the Syncom 1, Star 13A (TE-M-516) on LES 1/2, Aurora (P67-1), Orbiscal (P68-1), Lincoln Calibration Sphere 4, S3-2, Solrad 11A/B, SPX plume generator package, Freja, Meteor and Equator-S, Star C (TE-M-345-11/12) on AMSAT P3A and Star B (TE-M-763) on AMPTE-CCE payloads.

Star 17

The Star 17 (TE-M-479) is a solid fuel apogee kick motor, first launched in 1963. It was used for payloads such as Radio Astronomy Explorer, SOLRAD and S3 satellites. The Star 17A (TE-M-521-5) version was used for orbit circularization on Skynet 1, NATO 1, IMP-H and IMP-J satellites.

Star 20 (Altair-3A)

The Star 20 (TE-M-640) is a solid fuel apogee kick motor, also known as Altair-3A. It was used as a second stage on a Atlas-E/F vehicle launching Stacksat. The TE-M-640 motor is similar to Altair 3 (FW-4S), and both are designated by NASA as Altair IIIA.

Star 24

The Star 24 (TE-M-604) is a solid fuel apogee kick motor, first qualified in 1973. It burns an 86% solids carboxyl-terminated polybutadiene (CTPB)-based composite propellant. The "24" designation refers to the approximate diameter of the Titanium fuel casing in inches.

Star 26

The Star 26 (Burner 2A or TE-M-442) is a upper stage motor used in Burner II stage of the Sandia Strypi IV vehicle introduced in 1965. The Star 26B (TE-M-442-1) variant was used on the Thor-LV2F Burner-2A launcher. Star 26C (TE-M-442-2) was used on the DOT sounding rocket.

Star 27

Star 27

A Star-27 kick motor with nozzle for IBEX
Country of origin	United States
Solid-fuel motor

The Star 27 is a solid apogee kick motor, with the 27 representing the approximate diameter of the stage in inches. It burns HTPB-based composite propellant with an average erosion rate of 0.0011 inches per second (0.028 mm/s).

It as used as a second stage on a version of the Atlas E/F rocket, launching the Solwind and Geosat satellites. When used on the Pegasus air-launch rocket payloads are capable of leaving Earth orbit.

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

Star 30

The Star 30 (TE-M-700-2) is a solid fuel motor, with the 30 representing the approximate diameter of the stage in inches. Different versions (A, B, C, E and PB) were used as an apogee motor for satellites such as G-STAR, Skynet 4, Koreasat or the HS-376 satellite bus. Star 30E was used by the ORBEX small orbital launcher. A Star 30 booster was also used on the CONTOUR comet probe.

Star 31 (Antares 1A)

The Star 31 (also known as Antares 1A or X-254) is a solid fuel motor, with the 31 representing the approximate diameter of the stage in inches. It had a thrust of 60.50 kN and a mass of 1225 kg. It was used as a stages of WASP, Scout X, Scout X-1, Blue Scout Junior, Blue Scout I, Blue Scout II, Scout X-1A and RAM B.

Star 37

Star-37

TE-M-364
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
Thor (rocket family), Delta (rocket family), upper stage

The Star 37 was first used as the engine for the Thor-Burner upper stage in 1965. The Burner I used the Thiokol FW-4 (TE 364-1) engine and the Burner II used the Thiokol (TE-M-364-2).

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 and Star 48. Internally, Thiokol's designation was TE-M-364 for early versions, TE-M-714 for later ones, and TE-M-783 for a special HTPB model used for FLTSATCOM 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 3D carbon-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).

A spin-stabilized or thrust-vectoring version of Star 37 is used as the final stage of the Minotaur V launch vehicle.

The Pioneer 10 & 11, and Voyager 1 & 2 Propulsion Modules used Star 37E motors; each is now on a similar 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).

Star 48

Star 48

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

The Star 48 is a type of solid rocket motor developed primarily by Thiokol Propulsion, which was purchased by Orbital ATK in 2001. In 2018, Orbital ATK in turn was acquired by Northrop Grumman.

The "48" designation refers to the approximate diameter of the fuel casing in inches; Thiokol had also manufactured other motors such as the Star 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 the Delta II launch vehicles. Other launchers such as ULA's Atlas 551 have also incorporated the motor, but with lower frequency. Onboard the Space Shuttle, the complete stage (motor plus accessories) was referred to as the Payload Assist Module (PAM), as the Shuttle could only take satellites to low Earth orbit. Because geostationary orbit is much more lucrative, the additional stage was needed for the final leg of the journey. On such missions, the stage was spin-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 a yo-yo de-spin technique.

A non-spinning, thrust-vectoring version of the Star 48 is available ("Star 48BV"), but much less common. A thrust-vectoring Star 48 is the final stage of the Minotaur IV+ launch vehicle.

A Star 48B motor used in the 3rd stage of the New Horizons probe was the first part of the New Horizons mission to reach Jupiter, crossing Pluto's orbit in 2015 at a distance of 200 million kilometers. It is now set to leave the Solar System, traveling on a similar interstellar trajectory to its companion probe for the indefinite future.

In 2013 a Star 48GXV was tested for the Parker Solar Probe mission as the upper stage on an Atlas V 551 vehicle, but the development was canceled, in favor of a Delta 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 to gimbal the nozzle, along with digital flight controls.

Star 63

The Star 63 is a solid fuel motor, with the 63 representing the approximate diameter of the stage in inches. Different versions exist: Star-63D (used on PAM-D2), Star-63DV and Star-63F. It was used to launch payloads from the Space Shuttle, and as stage on the Titan 34D and Delta 7925 rockets.

References

1. ^ "Star 13". www.astronautix.com. Retrieved 2024-10-02.
2. ^ "Star-13". space.skyrocket.de. Retrieved 2024-10-02.
3. ^ "Star 13". www.planet4589.org. Retrieved 2024-10-02.
4. ^ "Star 13A". www.astronautix.com. Retrieved 2024-10-02.
5. ^ "Star 13B". www.astronautix.com. Retrieved 2024-10-02.
6. ^ "Star 13C". www.astronautix.com. Retrieved 2024-10-02.
7. ^ "Star 13D". www.astronautix.com. Retrieved 2024-10-02.
8. ^ "Star 13E". www.astronautix.com. Retrieved 2024-10-02.
9. ^ "Star 13F". www.astronautix.com. Retrieved 2024-10-02.
10. ^ "Star 17". www.astronautix.com. Retrieved 2024-10-01.
11. ^ "Star 17A". www.astronautix.com. Retrieved 2024-10-01.
12. ^ "Star-20 (Altair-3A)". space.skyrocket.de. Retrieved 2024-10-06.
13. "Atlas with solid-fuel upper stage". Gunter's Space Page. Retrieved 2024-10-06.
14. "Atlas-E/-F Altair-3A". Gunter's Space Page. Retrieved 2024-10-06.
15. Merryman; Smith (December 1974). PERFORMANCE OF A UTC FW-4S SOLID-PROPELLANT ROCKET MOTOR UNDER THE COMBINED EFFECTS OF SIMULATED ALTITUDE AND ROTATIONAL SPIN (PDF). NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (LRC). p. 5.
16. ^ "Orbital ATK Propulsion Products Catalog (October 2016) - Page 84-85" (PDF). Archived from the original (PDF) on 2016-08-26. Retrieved 2017-05-06.
17. "Star 24". www.astronautix.com. Retrieved 2024-09-30.
18. C.E.Carr II and D.W.Walstrum - Solid Rocket Propulsion for Small-Satellite Applications, Presented at Third Annual AIAA/Utah State University Conference on Small Satellites, Utah State University, Logan, Utah (26-28 September 1989) - Page 9
19. "Star 24A". www.astronautix.com. Retrieved 2024-10-01.
20. "Star 24B". www.astronautix.com. Retrieved 2024-10-01.
21. "Star 24C". www.astronautix.com. Retrieved 2024-10-01.
22. ^ "Star 26". www.astronautix.com. Retrieved 2024-09-30.
23. ^ "Star 26B". www.astronautix.com. Retrieved 2024-09-30.
24. ^ "Star 26C". www.astronautix.com. Retrieved 2024-09-30.
25. "DOT". www.astronautix.com. Retrieved 2024-09-30.
26. ^ David Darling (2003). The Complete Book of Spaceflight: From Apollo 1 to Zero Gravity. Wiley. pp. 317–318. ISBN 978-0-471-46771-7.
27. "Star 27". www.astronautix.com. Retrieved 2024-09-30.
28. George P. Sutton; Oscar Biblarz (2011). Rocket Propulsion Elements. Wiley. p. 592. ISBN 978-1-118-17461-6.
29. "Atlas-E/-F OIS". Gunter's Space Page. Retrieved 2024-10-06.
30. "Les lanceurs Pegasus". www.capcomespace.net. Retrieved 2017-02-12.
31. ^ IBEX
32. "Star 27A". www.astronautix.com. Retrieved 2024-09-30.
33. "Star 27B". www.astronautix.com. Retrieved 2024-09-30.
34. "Star 27C". www.astronautix.com. Retrieved 2024-09-30.
35. "Star 27D". www.astronautix.com. Retrieved 2024-09-30.
36. "Star 27E". www.astronautix.com. Retrieved 2024-09-30.
37. ^ "Star 30". www.astronautix.com. Retrieved 2024-10-01.
38. Williams, David R. (2002). "CONTOUR - NSSDCA Master Catalog".
39. "Star 30A". www.astronautix.com. Retrieved 2024-10-01.
40. "Star 30B". www.astronautix.com. Retrieved 2024-10-01.
41. "Star 30C". www.astronautix.com. Retrieved 2024-10-01.
42. "Star 30E". www.astronautix.com. Retrieved 2024-10-01.
43. "Star 30BP". www.astronautix.com. Retrieved 2024-10-01.
44. ^ "Antares 1A". www.astronautix.com. Retrieved 2024-09-28.
45. http://www.globalsecurity.org/space/systems/thor.htm Global Security
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50. Derelict Booster to Beat Pluto Probe to Jupiter
51. ATK and NASA Successfully Demonstrate New Rocket Motor for Solar Probe Plus Mission
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• Star 37 motors

External links

• Astronautix - Star 27
• Solid Propellant Rocket Fundamentals Archived 2012-06-19 at the Wayback Machine (Pages 417-418)

v t e Rocket engines and solid motors for orbital launch vehicles
Comparison of orbital rocket engines
Liquid fuel	Cryogenic Hydrolox (LH2 / LOX) China YF-73 YF-75 YF-75D YF-77 YF-79 YF-90 Europe HM7B Vinci Vulcain India CE-7.5 CE-20 Japan LE-5 LE-7 LE-9 Russia KVD-1 (RD-56) RD-0120 RD-0146 United States BE-3U BE-7 J-2 RL10 RS-25 RS-68 Methalox (CH4 / LOX) China BF-20 Lingyun Longyun TQ-11 TQ-12 TQ-15A YF-209 YF-215 United States BE-4 Raptor Archimedes Aeon 1 Aeon R Russia RD-0169 Europe Prometheus M-10 Semi- cryogenic Kerolox (RP-1 / LOX) China TH-11 TH-12 YF-100 YF-102 YF-115 YF-130 Welkin India SCE-200 Russia NK-15 NK-33, 44 RD-58 RD-0105, 0109 RD-0107, 0108, 0110 RD-0110R RD-0124 RD-107, 108, 117, 118 RD-120 RD-170, 171 RD-180 RD-191, 151, 181 RD-193 S1.5400 Spain TEPREL Ukraine RD-8 RD-801 RD-810 United States F-1 H-1 Kestrel LR-79 LR89 LR105 LR70-NA , S-3D Merlin RS-27 RS-27A RS-56 S-3D Rutherford XLR50 Storable Hypergolic (Aerozine, UH 25, MMH, or UDMH / N2O4, MON, or HNO3) China YF-1, 2, 3 YF-20, 21, 22, 24, 25 YF-23 YF-40 YF-50D Europe Aestus Astris Vexin Viking India PS4 Vikas Israel LK-4 North Korea Paektusan LRE along other LREs Russia 17D61 RD-0202 to 0206, 0208 to 0213 RD-0207, 0214 RD-0216, 0217, 0235 RD-0233, 0234 RD-0236 RD-0237 RD-0243 to 0245 RD-0255 to 0257 RD-215 to 219 RD-250 to 252, 261, 262 RD-253, 275 RD-263, 268, 273 RD-270 S5.92 S5.98M Ukraine RD-843 RD-854, 861 RD-855 RD-856 RD-864, 869 United States AJ10 LR-87 LR-91 RS-88* TR-201 XLR81* Other Russia RD-109, 119 RD-211 to 214 UK Gamma United States Curie RS-88* XLR81*
Solid fuel	China FG-02 FG-36 FG-46 FG-47 SpaB-65 SpaB-140C Europe Mage 1 P-4 P-6 PAP P80 P120C P230 Topaze Waxwing Zefiro 9 Zefiro 23 Zefiro 40 India S7 S9 S12 S139 S200 Iran Salman Rafe Israel LK-1 RSA-3 Japan KM-V1 KM-V2b M-14 M-24 M-34 M-34c SRB-A United States AJ-60A Algol Castor 30 GEM Orbus-6 Orbus-21 Orion Space Shuttle SRB Star 37 Star 48 UA120 SRMU X-248 X-254
* Different versions of the engine use different propellant combinations Engines in italics are under development

v t e Spacecraft engines and motors
Liquid fuel engines	17D61 AJ10 BT-4 Curie Draco KDU-414 S5.19 S5.114 KTDU-35 S5-35 S5.53 S5-60 S5-66 KTDU-80 11D426 11D428 S5.79 S5.80 S5.142 KTDU-425 LEROS LMAE LMDE R-4D RD-58 11D58 RS-25 S400 S5.4 S5.92 SuperDraco TR-201 XLR81
Solid propellant motors	Star 37 Star 48 FG-15 FG-36 SpaB-65 SpaB-140C
Related articles	Spacecraft propulsion Spacecraft Satellite Apogee kick motor Liquid apogee engine

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