Accession Number:

ADD015215

Title:

High Lift Aircraft.

Descriptive Note:

Patent, Filed 29 Nov 89, Patented 10 Dec 91,

Corporate Author:

DEPARTMENT OF THE NAVY WASHINGTON DC

Personal Author(s):

Report Date:

1991-12-10

Pagination or Media Count:

16.0

Abstract:

A high lift vertical takeoff and landing aircraft has first and second fuselages connected by a central airfoil. Jet engines at the leading edge of the airfoil expel propulsive stream simultaneously over top and bottom surfaces of the foil. Extendable flaps are utilized at a trailing edge of the airfoil with a horizontal control blade being attached to the leading edge of the foil. The control blade is within the jets propulsive stream to permit proportioning of the stream above and below the airfoil. An extendable augmenter wing is attached between the fuselages aft and above the main airfoil to permit airflow in this region to be directed downwardly, accelerating the flow and providing additional lift. The main airfoil is positioned so that the fuselage walls extend above and below the foil. Lateral flow of the main engine exhaust is restrained by these walls. Above the wing walls and airfoil create a venturi to speed airflow and decrease pressure. Below the wing the walls and extended flaps dam exhaust and ambient flow to create a high pressure region. Outboard wings provide secondary lift and reduce main wing loading. A canard is attached between the fuselages to provide pitch control. Both top and bottom canard surfaces are blown by forward mounted engines or exhaust ducts to add lift to the aircraft and to permit upward tilting of the aircraft during takeoff and landing. Tilting the aircraft permits the resultant of the engine thrust and wing lift vectors to be vertical.

Subject Categories:

  • VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE