The objective is to outline the results of the preliminary design of the Scorpion, a proposed close air support aircraft. The results obtained include complete preliminary analysis of the aircraft in the areas of aerodynamics, structures, avionics and electronics, stability and control, weight and balance, propulsion systems, and costs. A conventional wing, twin jet, twin-tail aircraft was chosen to maximize the desirable characteristics. The Scorpion will feature low speed maneuverability, high survivability, low cost, and low maintenance. The life cycle cost per aircraft will be 17.5 million dollars. The maximum takeoff weight will be 52,760 pounds. Wing loading will be 90 psf. The thrust to weight will be 0.6 lbs/lb. This aircraft meets the specified mission requirements. Some modifications have been suggested to further optimize the design.
Scorpion: Close Air Support (CAS) Aircraft
1991
107 pages
Report
Keine Angabe
Englisch
Aircraft , Avionics , Logistics Military Facilities & Supplies , Attack aircraft , Life cycle costs , Propulsion system configurations , Jet aircraft , Propulsion system performance , Wings , Aircraft maintenance , Balance , Low cost , Low speed , Maneuverability , Mission planning , Stability , Takeoff , Weight (Mass) , Wing loading
Scorpion: Close Air Support (CAS) aircraft
NTRS | 1991
|Design of a close-support aircraft
AIAA | 1990
|Technology Integration for Close Air Support Aircraft
NTIS | 1973
|Manx: Close air support aircraft preliminary design
NTRS | 1991
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