Shown here is the larger chamber of a two-chamber liquid-fuel rocket engine for the Navy's Lark surface-to-air missile. It produced 400 pounds of thrust, firing only when the Lark fell below a certain pre-determined velocity. The smaller chamber produced 220 pounds of thrust. The Lark, which also relied on two 1,000-pound solid propellant boosters during shipboard launch, burned fuming nitric acid and aniline to reach a maximum range of 38 miles. Initially developed late in World War II as an anti-Kamikaze missile, the Lark never entered service, but the Navy used it as a test vehicle until the early 1950s for ongoing studies of radar guidance and missile stability and control.
This engine is among the first to incorporate regenerative cooling technology, pioneered by the manufacturer--Reaction Motors. In this cutaway, the regeneratively cooled propellant walls are visible around the combustion chamber.
Display Status
This object is not on display at the National Air and Space Museum. It is either on loan or in storage.
Object Details
Country of Origin
United States of America
Type
PROPULSION-Rocket Engines
Manufacturer
Reaction Motors, Inc.
Dimensions
Overall: 27.9 x 10.8 x 5.7cm (11in. x 4 1/4in. x 2 1/4in.)
Length, overall 11 inches; length, chamber, 10.5 inches; outside diameter, maximum, 3.5 inches; outside diameter, at nozzle end, 2 inches 10/16 inches; inside diameter, main section of chamber, 3 inches
Materials
Stainless Steel
Inventory Number
A19990027000
Credit Line
Found in collection. Donor unknown at this time. Found on NASM premises.
Data Source
National Air and Space Museum
Restrictions & Rights
Usage conditions apply
For more information, visit the Smithsonians Terms of Use.