Accession Number:

AD0832677

Title:

EFFECTS OF ENGINE THRUST TRANSIENTS ON XSM-65C MISSILE,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s):

• Eisenberg, B. L.

Report Date:

1959-05-26

Pagination or Media Count:

141.0

Abstract:

The purpose of the tests was to obtain an empirical solution to substantiate the analytical approach to the problem of excessive load-factors resulting from engine dry start thrust build-up transients. Dry start signifies the absence of fluid in the thrust chamber walls prior to ignition. Data derived from the captive testing of Missile 2C were evaluated with respect to the following objectives. 1 Obtain thrust build-up rates from strain gauge data for correlation with chamber pressure information. 2 Obtain tank pressures and hoop and longitudinal stresses in the tank skins produced by the thrust build-up transient in order to determine the contribution of the propellant acceleration to the missile structure stress pattern. Author

Descriptors:

• *LIQUID PROPELLANT ROCKET ENGINES
• PROPELLANT TANKS
• STRUCTURAL PROPERTIES
• THRUST
• TRANSIENTS
• PRESSURIZATION
• PRESSURE VESSELS
• LOADS(FORCES)
• IGNITION
• LIQUID ROCKET OXIDIZERS
• LIQUID ROCKET FUELS
• LAUNCHING
• STAGING
• CAPTIVE TESTS
• TRANSDUCERS
• MATHEMATICAL ANALYSIS
• STRESSES

Subject Categories:

• Surface-Launched Guided Missiles
• Mechanics
• Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE