Accession Number:

AD0829727

Title:

FLEXIBLE EXIT CONE NOZZLE DEVELOPMENT PROGRAM.

Descriptive Note:

Rept. on phase 1, 1 Aug 67-15 Mar 68,

Corporate Author:

MORTON THIOKOL INC BRIGHAM CITY UT WASATCH OPERATIONS

Personal Author(s):

• Wilson, Jonathan W.
• Wright, Charles W.

Report Date:

1968-04-01

Pagination or Media Count:

248.0

Abstract:

A program was established by the Air Force Rocket Propulsion Laboratory to demonstrate by rocket motor testing the flexible exit cone omniaxis movable nozzle concept. Engineering studies and analysis, laboratory materials, subscale and full scale nozzle materials testing with flexible joint, and cold flow tests are performed to support the demonstration nozzle design. Engineering studies and analysis indicate that a flexible exit cone nozzle joint exposed to rocket motor exhaust gases can survive. Bond testing between elastomers to shims has verified the joint with the materials tested. Materials tests have selected a number of acceptable elastomers and shim reinforcement materials. A joint bench test fixture was designed and fabricated. The exposed joint will be the prime design with the recessed design carried in parallel for the fixed materials test nozzles and the joint bench tests. Cold flow model testing for the first nine tests determined the optimum pivot point and joint location. Adequate supporting design data was completed to design the three char motor materials nozzles and the first joints for bench testing. Author

Descriptors:

• *ROCKET NOZZLES
• MOVABLE NOZZLES
• FEASIBILITY STUDIES
• FLEXIBLE STRUCTURES
• BONDED JOINTS
• CONICAL NOZZLES
• ELASTOMERS
• MODEL TESTS
• OPTIMIZATION
• COLD FLOW
• MATERIALS
• CAPTIVE TESTS
• COMPUTER PROGRAMMING
• SUBROUTINES
• AERODYNAMIC CHARACTERISTICS
• TABLES(DATA)
• TEST METHODS
• EXHAUST NOZZLES

Subject Categories:

• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE