Accession Number:

AD0832821

Title:

ENGINEERING FLIGHT TEST OF THE CH-47 (CHINOOK) HELICOPTER INTEGRAL WEIGHT AND BALANCE SYSTEMS (ENSURE)

Descriptive Note:

Final rept. 1 Aug 1967-12 Jan 1968

Corporate Author:

ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA

Personal Author(s):

• Higgins, Allyn E.
• Schwartz, Samuel R.
• Catey, Harold C.
• Forsyth, Robert F.

Report Date:

1968-03-01

Pagination or Media Count:

45.0

Abstract:

An engineering research evaluation of two proposed integral weight and balance systems for the CH-47 Chinook Helicopter was conducted to determine the feasibility of such systems. The primary function of the systems is to accurately predict the aircraft gross weight and center of gravity location along with cargo hook load. The evaluation of these systems was conducted at Edwards Air Force Base, California, by the US Army Aviation Test Activity. The systems were tested throughout the entire envelope of allowable gross weight and center of gravity for the CH-47A aircraft. The testing consisted of determining the effects of rotor rpm, terrain, wind and control position, for various loading configurations, upon the indicated values of gross weight and center of gravity for the STAN and STOW weight and balance systems. Also, evaluated were the problems of installation and calibration of the systems, repeatability, reliability, and compatibility with other systems. Both systems performed reasonably well with the helicopter in a static mode rotors not turning.

Descriptors:

• *HELICOPTERS
• FLIGHT TESTING
• CENTER OF GRAVITY
• PERFORMANCE(ENGINEERING)
• WIND
• WEIGHT
• ROTATION
• BALANCES
• CALIBRATION
• AERODYNAMIC LOADING
• TERRAIN
• HELICOPTER ROTORS
• RELIABILITY

Subject Categories:

• Helicopters

Distribution Statement:

APPROVED FOR PUBLIC RELEASE