@prefix skos: <http://www.w3.org/2004/02/skos/core#> .
@prefix ns0: <https://gcmd.earthdata.nasa.gov/kms#> .

<https://gcmd.earthdata.nasa.gov/kms/concept/db2063ed-c27a-41e2-9e40-9f2f7e63f94b>
  skos:prefLabel "Sounding Rockets"@en ;
  a skos:Concept ;
  skos:narrower <https://gcmd.earthdata.nasa.gov/kms/concept/9e9e86b0-d613-4069-abe2-8291a6fac3ef> .

<https://gcmd.earthdata.nasa.gov/kms/concept/9e9e86b0-d613-4069-abe2-8291a6fac3ef>
  ns0:reference [ ] ;
  skos:changeNote """2022-02-18 14:03:47.0 [tstevens]  
insert Definition (id: null
text: Still quite similar to the Titan III-C on which it was based, the Titan 34D was introduced in 1982 and could incorporate either the Transtage third stage or a new upper stage called an Inertial Upper Stage (IUS). The IUS was a two-stage booster which effectively provided a third and fourth stage that allowed the Titan 34D to carry large military payloads into orbit. Performance of the Titan 34D was also improved by adding a one-half segment to the previous generation of Titan III solid rocket boosters, making a total of five and one-half segments per booster. The two resulting United Technologies solid rocket boosters burned Powered Aluminum/Ammonium Perchlorate solid fuel and could produce a combined thrust of 2,498,000 pounds. The first stage Aerojet engine could produce a thrust of 532,000 pounds. An Aerojet second stage engine could produce a 101,000-pound thrust. Both the first and second stage engines burned Aerozine 50/Nitrogen Tetroxide liquid fuel. The IUS first stage could produce a thrust of 62,000 pounds, while its second stage was capable of producing a 26,000-pound thrust. Both IUS stages were solid-fueled. The Titan 34D was able to carry a 27,500-pound payload to low-Earth orbit or a 4,200-pound payload to geostationary transfer orbit.
language code: en); 
""", """2021-11-16 15:02:13.0 [tstevens] Move Concepts 
delete broader relation (null); 
add broader relation (Titan 34D [9e9e86b0-d613-4069-abe2-8291a6fac3ef,826560] - Sounding Rockets [db2063ed-c27a-41e2-9e40-9f2f7e63f94b,835879]); 
""", """2015-12-01 15:41:40.0 [gee-cee] Insert Concept 
add broader relation (Titan 34D [9e9e86b0-d613-4069-abe2-8291a6fac3ef,158531] - Balloons/Rockets [2196cc92-a5da-4233-9509-5523385da1d7,143329]); 
""" ;
  skos:broader <https://gcmd.earthdata.nasa.gov/kms/concept/db2063ed-c27a-41e2-9e40-9f2f7e63f94b> ;
  skos:prefLabel "Titan 34D"@en ;
  skos:inScheme <https://gcmd.earthdata.nasa.gov/kms/concepts/concept_scheme/platforms> ;
  skos:definition "Still quite similar to the Titan III-C on which it was based, the Titan 34D was introduced in 1982 and could incorporate either the Transtage third stage or a new upper stage called an Inertial Upper Stage (IUS). The IUS was a two-stage booster which effectively provided a third and fourth stage that allowed the Titan 34D to carry large military payloads into orbit. Performance of the Titan 34D was also improved by adding a one-half segment to the previous generation of Titan III solid rocket boosters, making a total of five and one-half segments per booster. The two resulting United Technologies solid rocket boosters burned Powered Aluminum/Ammonium Perchlorate solid fuel and could produce a combined thrust of 2,498,000 pounds. The first stage Aerojet engine could produce a thrust of 532,000 pounds. An Aerojet second stage engine could produce a 101,000-pound thrust. Both the first and second stage engines burned Aerozine 50/Nitrogen Tetroxide liquid fuel. The IUS first stage could produce a thrust of 62,000 pounds, while its second stage was capable of producing a 26,000-pound thrust. Both IUS stages were solid-fueled. The Titan 34D was able to carry a 27,500-pound payload to low-Earth orbit or a 4,200-pound payload to geostationary transfer orbit."@en ;
  a skos:Concept .