Star (rocket stage)#Star 26

The Star 13 (TE-M-458) is a solid fuel apogee kick motor.{{Cite web |title=Star 13 |url=http://www.astronautix.com/s/star13.html |access-date=2024-10-02 |website=www.astronautix.com}}{{Cite web |title=Star-13 |url=https://space.skyrocket.de/doc_eng/star-13.htm |access-date=2024-10-02 |website=space.skyrocket.de}} It was used on NASA's Anchored Interplanetary Monitoring Platform satellites.{{Cite web |title=Star 13 |url=https://www.planet4589.org/space/book/lv/engines/motorlist/star13.html |access-date=2024-10-02 |website=www.planet4589.org}} Several other versions were developed.{{Cite web |title=Star 13A |url=http://www.astronautix.com/s/star13a.html |access-date=2024-10-02 |website=www.astronautix.com}}{{Cite web |title=Star 13B |url=http://www.astronautix.com/s/star13b.html |access-date=2024-10-02 |website=www.astronautix.com}}{{Cite web |title=Star 13C |url=http://www.astronautix.com/s/star13c.html |access-date=2024-10-02 |website=www.astronautix.com}}{{Cite web |title=Star 13D |url=http://www.astronautix.com/s/star13d.html |access-date=2024-10-02 |website=www.astronautix.com}}{{Cite web |title=Star 13E |url=http://www.astronautix.com/s/star13e.html |access-date=2024-10-02 |website=www.astronautix.com}}{{Cite web |title=Star 13F |url=http://www.astronautix.com/s/star13f.html |access-date=2024-10-02 |website=www.astronautix.com}} 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.

The Star 17 (TE-M-479) is a solid fuel apogee kick motor, first launched in 1963.{{Cite web |title=Star 17 |url=http://www.astronautix.com/s/star17.html |access-date=2024-10-01 |website=www.astronautix.com}} 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.{{Cite web |title=Star 17A |url=http://www.astronautix.com/s/star17a.html |access-date=2024-10-01 |website=www.astronautix.com}}

The Star 20 (TE-M-640) is a solid fuel apogee kick motor, also known as Altair-3A.{{Cite web |title=Star-20 (Altair-3A) |url=https://space.skyrocket.de/doc_eng/star-20.htm |access-date=2024-10-06 |website=space.skyrocket.de}} It was used as a second stage on an Atlas-E/F vehicle launching Stacksat.{{Cite web |title=Atlas with solid-fuel upper stage |url=https://space.skyrocket.de/doc_lau/atlas_sd.htm |access-date=2024-10-06 |website=Gunter's Space Page |language=en}}{{Cite web |title=Atlas-E/-F Altair-3A |url=https://space.skyrocket.de/doc_lau_det/atlas-ef_altair-3.htm |access-date=2024-10-06 |website=Gunter's Space Page |language=en}} The TE-M-640 motor is similar to Altair 3 (FW-4S), and both are designated by NASA as Altair IIIA.{{Cite book |last=Merryman |url=https://apps.dtic.mil/sti/tr/pdf/ADA002149.pdf |title=PERFORMANCE OF A UTC FW-4S SOLID-PROPELLANT ROCKET MOTOR UNDER THE COMBINED EFFECTS OF SIMULATED ALTITUDE AND ROTATIONAL SPIN |last2=Smith |date=December 1974 |publisher=NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (LRC) |pages=5}}

The Star 24 (TE-M-604) is a solid fuel apogee kick motor, first qualified in 1973.{{Cite web |url=https://www.orbitalatk.com/flight-systems/propulsion-systems/docs/2016%20OA%20Motor%20Catalog.pdf |title=Orbital ATK Propulsion Products Catalog (October 2016) - Page 84-85 |access-date=2017-05-06 |archive-date=2016-08-26 |archive-url=https://web.archive.org/web/20160826135927/https://www.orbitalatk.com/flight-systems/propulsion-systems/docs/2016%20OA%20Motor%20Catalog.pdf |url-status=dead }}{{Cite web |title=Star 24 |url=http://www.astronautix.com/s/star24.html |access-date=2024-09-30 |website=www.astronautix.com}} It burns an 86% solids carboxyl-terminated polybutadiene (CTPB){{Broken anchor|date=2024-06-24|bot=User:Cewbot/log/20201008/configuration|target_link=Ammonium perchlorate composite propellant#Common species|reason= The anchor (Common species) has been deleted.}}-based composite propellant.[http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2593&context=smallsat 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] The "24" designation refers to the approximate diameter of the Titanium fuel casing in inches.

The Star 26 (Burner 2A or TE-M-442) is an upper stage motor used in Burner II stage of the Sandia Strypi IV vehicle introduced in 1965.{{Cite web |title=Star 26 |url=http://www.astronautix.com/s/star26.html |access-date=2024-09-30 |website=www.astronautix.com}} The Star 26B (TE-M-442-1) variant was used on the Thor-LV2F Burner-2A launcher.{{Cite web |title=Star 26B |url=http://www.astronautix.com/s/star26b.html |access-date=2024-09-30 |website=www.astronautix.com}} Star 26C (TE-M-442-2) was used on the DOT sounding rocket.{{Cite web |title=Star 26C |url=http://www.astronautix.com/s/star26c.html |access-date=2024-09-30 |website=www.astronautix.com}}{{Cite web |title=DOT |url=http://www.astronautix.com/d/dot.html |access-date=2024-09-30 |website=www.astronautix.com}}

{{Infobox rocket engine

|country_of_origin = United States

|image=Star-27.jpg

|image_size=200

|caption=A Star-27 kick motor with nozzle for IBEX

|name=Star 27

|type=solid

}}

The Star 27 is a solid apogee kick motor, with the 27 representing the approximate diameter of the stage in inches.{{cite book|author=David Darling|title=The Complete Book of Spaceflight: From Apollo 1 to Zero Gravity|url=https://archive.org/details/completebookofsp00davi|url-access=registration|year=2003|publisher=Wiley|isbn=978-0-471-46771-7|pages=[https://archive.org/details/completebookofsp00davi/page/317 317]–318}}{{Cite web |title=Star 27 |url=http://www.astronautix.com/s/star27.html |access-date=2024-09-30 |website=www.astronautix.com}} It burns HTPB-based composite propellant with an average erosion rate of {{convert|0.0011|in/s|mm/s}}.{{cite book|author1=George P. Sutton|author2=Oscar Biblarz|title=Rocket Propulsion Elements|url=https://books.google.com/books?id=xZkdm7Efdb8C&pg=PA592|year=2011|publisher=Wiley|isbn=978-1-118-17461-6|page=592}}

It as used as a second stage on a version of the Atlas E/F rocket, launching the Solwind and Geosat satellites.{{Cite web |title=Atlas-E/-F OIS |url=https://space.skyrocket.de/doc_lau_det/atlas-ef_ois.htm |access-date=2024-10-06 |website=Gunter's Space Page |language=en}} When used on the Pegasus air-launch rocket payloads are capable of leaving Earth orbit.

A version of the Star 27, designated Star 27H,{{Cite web|url=http://www.capcomespace.net/dossiers/espace_privee/Orbital_Sciences/pegasus/index.htm|title=Les lanceurs Pegasus|website=www.capcomespace.net|access-date=2017-02-12}} was used in the launch of the IBEX spacecraft.[http://www.orbital.com/SatellitesSpace/ScienceTechnology/IBEX/ IBEX] 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.

The Star 30 (TE-M-700-2) is a solid fuel motor, with the 30 representing the approximate diameter of the stage in inches.{{Cite web |title=Star 30 |url=http://www.astronautix.com/s/star30.html |access-date=2024-10-01 |website=www.astronautix.com}} 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.{{Cite web |last=Williams |first=David R. |date=2002 |title=CONTOUR - NSSDCA Master Catalog |url=https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=2002-034A}}

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.{{Cite web |title=Antares 1A |url=http://www.astronautix.com/a/antares1a.html |access-date=2024-09-28 |website=www.astronautix.com}} 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.

{{Infobox rocket engine

|country_of_origin= United States

|image=TE-M-364 Rocket Engine USAF.jpg

|image_size=

|caption=TE-M-364

|name=Star-37

|date= 1963-present

|manufacturer= Thiokol

|purpose=Upper stage/Spacecraft propulsion

|status=Active

|cycle=

|combustion_chamber=1

|thrust(Vac)= 33.600 kN (7,554 lbf)

|specific_impulse_vacuum= (161,512 N•s/kg)

|chamber_pressure=

|thrust_to_weight=

|diameter= 0.66 m (2.16 ft)

|length= 2.27 m (7.44 ft)

|dry_weight= 113 kg (249 lb)

|predecessor= Star 27

|successor= Star 48

|type= solid

|fuel=

|oxidiser=

|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).http://www.globalsecurity.org/space/systems/thor.htm Global Security

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 {{convert|2350|lb}}, while the motor has been qualified for propellant off-loading to {{convert|2257|lb|kg}}.

A spin-stabilized or thrust-vectoring version of Star 37 is used as the final stage of the Minotaur V launch vehicle.{{Cite web|url=https://www.nasaspaceflight.com/2013/09/orbitals-minotaur-v-launch-ladee-mission-moon/|title=Orbital's Minotaur V launches LADEE mission to the Moon {{!}} NASASpaceFlight.com|website=www.nasaspaceflight.com|date=7 September 2013 |language=en-US|access-date=2017-02-12}}{{Cite web|url=http://www.spacelaunchreport.com/mintaur4.html|title=Space Launch Report ... Minotaur Data Sheet|last=Kyle|first=Ed|website=www.spacelaunchreport.com|access-date=2017-02-12}}

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{{Cite web |title=rockets - Where are the upper stages for the Voyager/Pioneer stages? |url=https://space.stackexchange.com/questions/1940/where-are-the-upper-stages-for-the-voyager-pioneer-stages |access-date=2022-06-08 |website=Space Exploration Stack Exchange |language=en}}).

{{Infobox rocket engine

|country_of_origin = United States

|image=PAM-D rocket stage.jpg

|image_size=200

|caption=Star-48B rocket motor

|name=Star 48

|date = 1982 - present

|manufacturer = Thiokol

|predecessor=Star 37

|type=solid

}}

{{main|Star 48}}

The Star 48 is a type of solid rocket motor developed primarily by Thiokol Propulsion, which was purchased by Orbital ATK in 2001.{{cite book |title= ATK Space Propulsion Products Catalog |publisher= ATK | year= 2012 |pages=99ff |url=http://www.atk.com/wp-content/uploads/2013/02/ATK-Motor-Catalog-2012.pdf |access-date=2013-06-06}} 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. On board 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.[http://www.space.com/missionlaunches/060126_newhorizons_update.html Derelict Booster to Beat Pluto Probe to Jupiter] 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,[http://www.prnewswire.com/news-releases/atk-and-nasa-successfully-demonstrate-new-rocket-motor-for-solar-probe-plus-mission-234652981.html ATK and NASA Successfully Demonstrate New Rocket Motor for Solar Probe Plus Mission] 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.{{Cite news|url=http://blog.executivebiz.com/2015/04/orbital-atk-to-augment-ula-rocket-for-launch-of-nasa-solar-probe/|title=Orbital ATK to Augment ULA Rocket for Launch of NASA Solar Probe|newspaper=ExecutiveBiz|access-date=2017-02-12}}

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.{{Cite web |title=Star 63 |url=http://www.astronautix.com/s/star63.html |access-date=2024-10-06 |website=www.astronautix.com}}{{Cite web |title=Star-63 |url=https://space.skyrocket.de/doc_eng/star-63.htm |access-date=2024-10-06 |website=space.skyrocket.de}} It was used to launch payloads from the Space Shuttle, and as stage on the Titan 34D and Delta 7925 rockets.

{{reflist}}

• [http://space.skyrocket.de/doc_eng/star-37.htm Star 37 motors]

• [https://web.archive.org/web/20161228054002/http://astronautix.com/s/star27.html Astronautix - Star 27]
• [http://euroaviaterrassa.upc.es/pc/apunts/Llibres/Propulsio/Propulsio/Sutton,%20Rocket%20Propulsion%20Elements/26429_11.pdf Solid Propellant Rocket Fundamentals] {{Webarchive|url=https://web.archive.org/web/20120619125300/http://euroaviaterrassa.upc.es/pc/apunts/Llibres/Propulsio/Propulsio/Sutton%2C%20Rocket%20Propulsion%20Elements/26429_11.pdf |date=2012-06-19 }} (Pages 417–418)

{{Rocket engines}}

{{Orbital spacecraft rocket engines}}

{{Upper stages}}

Category:Rocket stages

Category:Solid-fuel rockets

Category:Alliant Techsystems