CarterCopter Aviation Technologies
 
4-Place PAV CH-150 Heliplane CarterCopter Technology Demonstrator CarterGyro Demonstrator Trainer Heliplane Hydrablaster CH-45 Heliplane Mu-1 Crew Photo
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Carter Aviation Technologies is a research and development company, pioneering new aviation concepts. Our primary focus is the slowed-rotor compound aircraft, a vertical takeoff and landing aircraft that uses the rotor for takeoff and landing, and a small, efficient wing for high speed flight, up to 500 mph, all with much less complexity than a tilt-rotor or other vectored thrust vehicle. We successfully demonstrated the slowed rotor concept with the CarterCopter Technology Demonstrator (CCTD), the first and only aircraft to reach mu-1 (more info).

License Agreement with AAI

Carter Aviation Technologies LLC (Carter) of Wichita Falls, TX is announcing that they have completed negotiations with AAI Corporation, an operating unit of Textron Systems, a Textron Inc. company, of Hunt Valley, MD on an exclusive licensing agreement for Unmanned Aircraft Systems (UAS) using Carter's revolutionary Slowed Rotor/Compound (SR/C) Aircraft Technology - a combination of rotorcraft and fixed-wing aerodynamics. The 40-year exclusive agreement covers all UAS programs worldwide.

For more information, read the full press release:
2009-11-17 Carter Signs UAS License Agreement with AAI

 

This Month at Carter
2010-07-12

  • Company president, Jay Carter, will be giving a forum at this year's EAA Airventure in Oshkosh. The presentation will be on Saturday, July 31st from 11:30 AM - 12:45 PM in the Remos Aircraft Pavilion #11. (more info)
  • Continued work on the 4-Place PAV Prototype.
    • Continued with the wiring & avionics.
    • Completed side load test on the 5 point pilot's harness.
    • Fabricated gas tank.
    • Completed test of the automatic mechanical pitch mechanism. We tested the full operating limits of pitch change and coning , and proof loads on the mechanism to 1.5 times the maximum load possible during prerotation.
    • Completed testing of the 15' blade. We cycled the rotor from 0 rpm to 900 rpm 256 times, which created a centrifugal force from the tip weights 1.5x higher than what will occur in the full size blade at 375 rpm. We then performed one cycle to 1175 rpm, which created a centrifugal force 2.56x higher that what will occur in the full size blade at 375 rpm.
    • Built the test stand that will be used to test the full size rotor. We will perform a proof test to 412 rpm before installing the rotor on the aircraft. We plan to perform the test this week.


    Rotor Head Installed in Rotor
    Rotor Head
    Installed
    in Rotor

    Completed Full Size Rotor in Test Pit
    Completed Full
    Size Rotor
    in Test Pit

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This web site was last updated on 2010-01-05.