Crew Exposure to Vibration in the F-4C Aircraft during Low-Altitude, High-Speed Flight.
Abstract
Measurements were made of the total vibration environment that the crew member is exposed to in the aft compartment of a F-4C aircraft during low-altitude, high-speed flight. Data were obtained of the longitudinal, lateral and vertical linear accelerations and the roll, pitch and yaw angular accelerations in the aft compartment and of the lateral and vertical linear accelerations at the aircraft center of gravity. The flights were performed in the contour following mode at various speeds at an altitude of 100-1000 feet over several different types of terrain. Data analysis included peak counting, probability density and distribution, auto-power spectral density and tests for stationarity, randomness and normality. The individual degree-of-freedom results are presented in graphical and tabular form and in general indicate that the crew station vibration environment produced by the combination of gust response and maneuvering: (1) is stationary for up to 400 seconds; (2) does not satisfy the chi-square goodness-of-fit test for Gaussian distribution; (3) exhibits a spectral content that is determined by certain aircraft design characteristics; (4) has for various flight conditions a power spectral density that can vary in overall level by a factor of 30; (5) cannot be adequately simulated for human tolerance type studies by considering the vertical axis accelerations only. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1971
- Accession Number
- AD0720271
Entities
People
- Harold K. Hille
- Hubert F. Bonfili
- Jerry D. Speakman
- John N. Cole
Organizations
- Air Force Research Laboratory