Artificial Icing Test CH-47C Helicopter with Fiberglass Rotor Blades.
Abstract
The United States Army Aviation Engineering Flight Activity in conjunction with the Boeing Vertol Company conducted an evaluation of the CH-47C helicopter with fiberglass rotor blades and a prototype blade de-ice system. The rotor blades were tested under natural and artificial icing conditions at St. Paul, Minnesota from 24 January to 2 March 1979, and required 30.1 flight hours of which 17.7 hours were in an icing environment. Testing was conducted in two phases: (1) protected, where the blade de-ice system was allowed to operate automatically and (2) unprotected, where the blade de-ice system was held in standby status. The fiberglass rotor blade system was evaluated at conditions varying from 0.1 gm cu m liquid water content (LWC) to 0.8 gm cu m LWC and temperatures varying from -4 C to -16 C. Time in the icing environment varied from a minimum of 28 minutes to a maximum of 2 hours and 25 minutes. The protected rotor blade de-ice system operated satisfactorily. The unprotected rotor blades operated satisfactorily under the limited conditions tested. Minimal ice accretion and minimal asymmetric shed characteristics were observed. Two deficiencies for flight under icing conditions unrelated to the fiberglass rotor blades were noted. The deficiencies are: (1) failure of the droopstops to engage after flight in icing conditions; and (2) ice accretion and subsequent blockage of the fuel vents.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1979
- Accession Number
- ADA081860
Entities
People
- Frame J. Bowers Iii
- John R. Niemann
- Sherwood C. Spring