Accession Number:

AD0387671

Title:

FEASIBILITY DEMONSTRATION OF A LARGE IMPULSE SOLID ROCKET ATTITUDE CONTROL MOTOR. VOLUME 1

Descriptive Note:

Final rept. Jan 1965-Jul 1966

Corporate Author:

CURTISS-WRIGHT CORP WOOD-RIDGE NJ WRIGHT AERONAUTICAL DIV

Personal Author(s):

• Rolleri, Norman J.

Report Date:

1966-08-01

Pagination or Media Count:

274.0

Abstract:

A solid propellant propulsion system was designed consisting of individual tape-mounted solid propellant rocket motors, which are fed from a storage container into firing position by means of a stepping motor-driven sprocket wheel. The rocket motors are fired, on command, at any of three positions by a signal from an external electrical source. The operation of a typical system in an attitude control application, is shown schematically. Rocket motor optimization studies show that a rectangular motor configuration with an LD ratio of 21 using a simple flat end-burning grain was optimum to provide minimum weight, volume, and sprocket wheel inertia. The design of the rocket motor was based on a quartz-phenolic base, a pre-molded rubber grain inhibitor, a silicone expandable E dome, CWP-13 propellant, and a pyrofuze wire pyrotechnic overspray ignition system. The weight of the WSR-101 rocket motor is .0246 pounds.

Descriptors:

• *ATTITUDE CONTROL SYSTEMS
• *SOLID PROPELLANT ROCKET ENGINES
• MANUFACTURING
• PULSES
• ALUMINUM
• RECTANGULAR BODIES
• ROCKET PROPELLANT GRAINS
• SPECIFIC IMPULSE
• SATELLITE ATTITUDE
• SOLID ROCKET PROPELLANT BINDERS
• EXPLOSIVE ACTUATORS
• FUEL ADDITIVES
• ROCKET IGNITERS
• INTERIOR BALLISTICS
• SOLID ROCKET PROPELLANTS
• CAPTIVE TESTS
• SERVOMECHANISMS
• ARTIFICIAL SATELLITES
• ENCAPSULATION
• IGNITION
• BURNING RATE
• INHIBITION

Subject Categories:

• Solid Propellant Rocket Engines
• Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE