Accession Number:

AD0804596

Title:

HIGH RESPONSE, LOW LEVEL PULSE ENGINE THRUST STAND SYSTEM.

Descriptive Note:

Final rept. Feb 65-Oct 66,

Corporate Author:

HUGHES RESEARCH LABS MALIBU CA

Personal Author(s):

• Couvillion, A. J.
• Smith, J. D.
• Kuberek, R.

Report Date:

1966-12-01

Pagination or Media Count:

122.0

Abstract:

A high response, low level pulse engine thrust stand system has been designed, fabricated, and installed at the Air Force Flight Test Center, Rocket Propulsion Laboratory, Edwards Air Force Base. This system is designed to measure rocket engine thurst in the range of 1 to 100 lb and to track the leading and trailing edges of thrust pulses exhibiting rise and decay times of 0.5 msec. As installed, the system has adequate thrust measurement capacity and has usable response from dc to 350 cps, limited only by mechanical resonance in the engine mounting platform and the readout transducer. The thrust stand system consists of the thrust platform, a hydraulic power supply unit, and a control console. Of these subsystems, the thrust platform is unique and, despite its limitations, represents a significant advance in the state of the art. The hydraulic load cell is its key component. This component meets or exceeds all design goals and has a useful response from dc to more than 2000 cps. The response capability of the hydraulic load cell can be more fully utilized and over-all system response can be enhanced by correcting the deficiencies in the engine mounting platform and the readout transducer. Author

Descriptors:

• *ENGINE MOUNTS
• HYDRAULIC EQUIPMENT
• ACCURACY
• VIBRATORS(MECHANICAL)
• SHAFT COUPLINGS
• TRANSDUCERS
• LOADS(FORCES)

Subject Categories:

• Test Facilities, Equipment and Methods
• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE