Drop and Static Tests on a Tenth-Scale Model of an Air Cushion Landing System (ACLS)

Item

Title
Drop and Static Tests on a Tenth-Scale Model of an Air Cushion Landing System (ACLS)
Date
1973
Index Abstract
Not Available
Photo Quality
Complete
Report Number
AFFDL TR 73-46
Corporate Author
Air Force Institute of Technology
Laboratory
Air Force Flight Dynamics Laboratory
Extent
160
Identifier
AD0770026
Access Rights
Approved for public release; distribution unlimited
Distribution Classification
1
Contract
Laboratory Research - No Contract
DoD Project
1369
DoD Task
None Given
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
None
Distribution Conflict
No
Abstract
An experimental investigation of the performance of an Air Cushion Landing System (ACLS) on a one-tenth scale model of a CC-115 Canadian aircraft is discussed. Several different types of tests were conducted on an extended version of the ACLS trunk at simulated fullscale trunk pressures of 315 psfg, out of ground effect, and 342 psfg, in ground effect. Cushion pressure was 160 psfg, in ground effect, during hover. The experiments involved: vertical drop tests to measure the effects of sink rate and initial attitude between full- scale sink rates of 3.0 and 12.5 fps, and attitudes of pitch and roll from 0.0 to 12.0 and 0.0 to 7.5 degrees, respectively; static equilibrium tests to measure vertical stiffness, roll stiffness, pitch stiffness, and floor pressure exerted by the ACLS with loads up to 4.1 times the aircraft landing weight; and braking tests to obtain the effects of changing brake pillow thickness between simulated full-scale heights of 0.0 inches and 26.0 inches. The results of the vertical drop tests revealed that the air cushion will absorb most of the landing impact load except at initial attitudes of 12.0 degrees pitch, where the aircraft fuselage could touch the ground. Vertical stiffness test results showed the extended version of the ACLS trunk to be 39% stiffer than a previous shorter version between vertical load ranges of 0.5 and 1.9 times the aircraft landing weight. Floor pressure tests verified that the ACLS aircraft could land on low strength runways and never exert pressures higher than 3.8 psi above the atmospheric, full scale. Braking tests concluded that maximum deceleration of the aircraft was about 0.34 g, and that increasing pillow thickness above 10.8 inches, full scale, would not increase that deceleration rate.
Report Availability
Full text available
Date Issued
1973-09
Provenance
Bombardier/Aero
Type
report
Format
1 online resource
Creator
Rodrigues, Anthony
Media
AFFDLTR73-046.pdf

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