Triple

T11509520
Position Surface form Disambiguated ID Type / Status
Subject Delta IV upper stage E272871 entity
Predicate hasDesignation P974 FINISHED
Object Delta Cryogenic Second Stage E846509 NE FINISHED

How this triple was built (2 steps)

Every LLM step that produced this triple, in pipeline order — named-entity classification, the disambiguation choices (the exact options shown, with the pick highlighted), and the generated description. The batch + timestamp of each is in the Provenance table below.

NER Named-entity recognition gpt-5-mini
Instruction
Given a phrase, classify it is english named entity (e.g., persons, organizations, works of art) in Latin script, or not (e.g., literals, dates, URLs, verbose phrases). For disambiguation, the statement where the phrase occurs as object is also given. Please return a JSON object with `phrase` (string, the phrase being analyzed) and `is_ne` (boolean, indicating whether the phrase is a Named Entity).
Input
Phrase: Delta Cryogenic Second Stage | Statement: [Delta IV upper stage, hasDesignation, Delta Cryogenic Second Stage]
NED1 Entity disambiguation (via context triple) gpt-5-mini-2025-08-07
Target entity: Delta Cryogenic Second Stage
Context triple: [Delta IV upper stage, hasDesignation, Delta Cryogenic Second Stage]
  • A. Delta Cryogenic Second Stage chosen
    The Delta Cryogenic Second Stage is a liquid hydrogen–liquid oxygen upper stage used on Delta IV rockets to provide high-efficiency propulsion for orbital insertion and mission maneuvers.
  • B. CE-20 cryogenic engine
    The CE-20 cryogenic engine is an Indian-developed, liquid hydrogen–liquid oxygen rocket engine that powers the upper stage of ISRO’s heaviest launch vehicles for placing large payloads into orbit.
  • C. Titan II second stage
    The Titan II second stage was the upper propulsion segment of the Titan II launch vehicle used during the Gemini program, serving as the spent target object for early U.S. crewed orbital rendezvous attempts.
  • D. Interim Cryogenic Propulsion Stage
    The Interim Cryogenic Propulsion Stage is a liquid hydrogen–liquid oxygen upper stage used on early NASA Space Launch System missions to provide orbital insertion and translunar injection capability before the introduction of a more powerful exploration upper stage.
  • E. L110 liquid core stage
    The L110 liquid core stage is a cryogenic rocket stage used in India’s GSLV Mk III launch vehicle, providing the main liquid propulsion for its ascent.
  • F. None of above.
  • G. Unsure - the case is ambiguous/there is not enough information to decide.

Provenance (3 batches)

The batch behind each pipeline step, in order, with when it ran. Timestamps are batch-level — stages were processed in waves, so the object chain (NER → NED1 → NEDg → NED2) reads in order, but predicate / elicitation batches can sit in a different wave.

Step Stage Batch ID Status When
creating Elicitation batch_69d6aae2c3748190bed2ea50dfb160dc completed April 8, 2026, 7:22 p.m.
NER Named-entity recognition batch_69d86db65eb081908613a1002c6a4fb4 completed April 10, 2026, 3:25 a.m.
NED1 Entity disambiguation (via context triple) batch_69e624f5c9608190bde28a59860b3c93 completed April 20, 2026, 1:07 p.m.
Created at: April 8, 2026, 9:36 p.m.