SBIR-STTR Award

An innovative, rotorless VTOL aircraft concept is proposed for Phase I mission scenario analysis, conceptual design, wind tunnel testing and performance analysis. The aircraft is a high speed vertical takeoff and landing (HSVTOL) aircraft concept. The HSVTOL concept has been patented. In vertical takeoff, the HSVTOL aircraft is capable of lifting heavy payloads and large fuel quantities similar to CTOL aircraft. In horizontal flight, preliminary data indicates a capability of cruise speeds in the high subsonic speed regime. The objective of this Phase I effort is to confirm that commercial applications of the HSVTOL concept can be made to closely approximate the high performance of generic disk shapes. The wind tunnel data will also be used to determine the performance capability of the HSVTOL concept with higher confidence. Using the wind tunnel data, analytical tools will be recalibrated and performance analyses performed. A performance map of the HSVTOL capability is expected to confirm that the HSVTOL will significantly out-perform current VTOL concepts in speeds and altitude and have comparable capability to CTOL short to medium range jet aircraft. Recalibrated analytical tools will enable higher confidence conceptual design of future HSVTOL designs/applications.

In view of the establishment of the preliminary feasibility of the unique HSVTOL aircraft concept and its potential to perhaps double the capability of current VTOLs in speed and range, the overall goal of Phase II is to perform work that reduces technical risks and leads to a Proof-of-Concept (PoC) flight test demonstration. A major milestone is to demonstrate that the fan of the PoC HSVTOL can produce adequate thrust to enable takeoff out-of-ground effect. This is in view of the previous 1960's test of the Avro car that failed to develop design vertical thrust. The conceptual design of Phase I of a 45' diameter aircraft is modified with circular planform aerosurfaces and new proprietary features. Detailed design of the pilotless 15' diameter PoC demonstrator is conducted especially at the interface of the fan assembly and the fuselage (bearings, seal and ducting). Further, design is conducted on the demonstrator flight controls and radio control links to reduce the long lead development time of the flight control software and hardware. The fan assembly thrust capability is tested first with roller wheels and then with air bearings using an electric motor to drive the fan assembly.