Rocketdyne J-2

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Explore the main themes, entities and connections around Rocketdyne J-2. Start with the topic map, then use the sections below for research and deeper semantic analysis.

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History

Atlas-Centaur Centaur Crewed flight Injector Santa Susana Field Laboratory

9 related topics

Overview

Liquid-fuel Cryogenic rocket engine NASA Saturn IB Saturn V

46 related topics

Components

Stainless steel Regeneratively cooled Manifold Swaged Spark plugs

7 related topics

Engine operation

Ullage

1 related topics

Key facts & relationships

High-confidence facts extracted from structured source data. Use them as anchors for further research.

Application: Upper stage engine
Associated LV: Saturn IB · Saturn V
Burn time: 500 seconds
Chamber pressure: 5,260 kPa (763 psi)
Country of origin: United States
Cycle: Gas generator

Topics to explore

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History

Atlas-Centaur
Centaur Centaur (rocket stage)
Crewed flight Human spaceflight
Injector Fuel injection
Santa Susana Field Laboratory
Turbopumps Turbopump
Saturn rockets Saturn (rocket family)
MSFC Marshall Space Flight Center
Douglas Douglas Aircraft Company

Advanced semantic analysis

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Map overview Semantic statistics

Nodes68

Edges67

Triples31

Avg. degree1.97

Density0.029412

Components1

How this topic connects Entity context

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Rocketdyne J-2

Top relations

Application · 1

Rocketdyne J-2 → Upper stage engine

Associated LV · 1

Rocketdyne J-2 → Saturn IB · Saturn V

Burn time · 1

Rocketdyne J-2 → 500 seconds

Chamber pressure · 1

Rocketdyne J-2 → 5,260 kPa (763 psi)

Country of origin · 1

Rocketdyne J-2 → United States

Cycle · 1

Rocketdyne J-2 → Gas generator

Designer · 1

Rocketdyne J-2 → Marshall Space Flight Center · Rocketdyne

Diameter · 1

Rocketdyne J-2 → 2.1 m (6.8 ft)

Dry mass · 1

Rocketdyne J-2 → 1,788.1 kg (3,942 lb)

First flight · 1

Rocketdyne J-2 → 26 February 1966 (1966-02-26) (AS-201)

Important terminology Word statistics

Use these terms to understand the vocabulary surrounding the topic, not as a checklist for keyword stuffing.

Important terminology

engine oxidizer thrust fuel chamber j-2 gas stage valve turbine system injector control generator first propellant j-2x rocketdyne manifold turbopump

Entity relationships Subject–Predicate–Object triples

Subject	Predicate	Object	Confidence	Src
Rocketdyne J-2	Application	Upper stage engine	1.00	infobox
Rocketdyne J-2	Associated LV	Saturn IB · Saturn V	1.00	infobox
Rocketdyne J-2	Burn time	500 seconds	1.00	infobox
Rocketdyne J-2	Chamber pressure	5,260 kPa (763 psi)	1.00	infobox
Rocketdyne J-2	Country of origin	United States	1.00	infobox
Rocketdyne J-2	Cycle	Gas generator	1.00	infobox
Rocketdyne J-2	Designer	Marshall Space Flight Center · Rocketdyne	1.00	infobox
Rocketdyne J-2	Diameter	2.1 m (6.8 ft)	1.00	infobox
Rocketdyne J-2	Dry mass	1,788.1 kg (3,942 lb)	1.00	infobox
Rocketdyne J-2	First flight	26 February 1966 (1966-02-26) (AS-201)	1.00	infobox
Rocketdyne J-2	Last flight	15 July 1975 (1975-07-15) (ASTP)	1.00	infobox
Rocketdyne J-2	Length	3.4 m (11.1 ft)	1.00	infobox
Rocketdyne J-2	Manufacturer	Rocketdyne	1.00	infobox
Rocketdyne J-2	Mixture ratio	5.5:1	1.00	infobox
Rocketdyne J-2	Notes	Data is for SA-208/SA-504 version.	1.00	infobox
Rocketdyne J-2	Nozzle ratio	27.5:1	1.00	infobox
Rocketdyne J-2	Propellant	Liquid oxygen / Liquid hydrogen	1.00	infobox
Rocketdyne J-2	Specific impulse, sea-level	200 s (2.0 km/s)	1.00	infobox
Rocketdyne J-2	Specific impulse, vacuum	421 s (4.13 km/s)	1.00	infobox
Rocketdyne J-2	Status	Retired	1.00	infobox
Rocketdyne J-2	Successor	HG-3 J-2X	1.00	infobox
Rocketdyne J-2	Thrust, sea-level	486.2 kN (109,302 lbf)	1.00	infobox
Rocketdyne J-2	Thrust, vacuum	1,033.1 kN (232,250 lbf)	1.00	infobox
Rocketdyne J-2	Thrust-to-weight ratio	73.18:1	1.00	infobox

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