INVESTIGATION OF A-4 SIGHT IN F-86E AIRPLANE
Abstract
A previous report concluded that the major cause of reticle vibration was excessive free play, mirror unbalance and lack of inherent system stiffness. The rework accomplished by the sight manufacturers was effective in reducing high frequency reticle vibration. The predominant range of vibration was 3 - 5 mils in azimuth and in elevation, with a peak of approximately 6 - 8 mils in both azimuth and elevation. Low frequency reticle oscillation occurred during air and ground firing tests. An A-4 adapter assembly, incorporating a removable combining glass, was devised to eliminate removal of the sight head for the purpose of cleaning the aft face of the windshield and the forward face of the combining glass. This configuration was mounted in the F-86E airplane, in conjunction with an N-9 sight, and subjected to gun fire vibrations. In azimuth, the predominant range of reticle vibration was 1 - 2 mils with a peak of 2 - 3 mils. In elevation, the predominant range was 1 - 2 mils with a peak of 3 - 4 mils. The removable combining glass was also checked for retention of boresight position. The thumb screws which retain the combining glass in the adapter were tightened in various sequences to determine the best procedure to follow. It has been found that if the thumb screws are tightened simultaneously, or reasonably so, the maximum variation from the original boresighted position is approximately 1/2 mil.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 18, 1952
- Accession Number
- AD0473192
Entities
People
- E. C. Holton
- J. A. D'amico