Airplane having non-stalling wings and wing-mounted propellers

Claim 1

A MONOPLANE FOR TAKE-OFF AND LANDING AT VERY STEEP ANGLES WHICH INCLUDES: A FUSELAGE, RIGHT AND LEFT WINGS EXTENDING SYMMETRICALLY FROM THE RIGHT AND LEFT SIDES OF SAID FUSELAGE, AND ADAPTED TO ROTATE FREELY AND INDEPENDENTLY OF EACH OTHER ABOUT THE SAME WING ROTATION AXIS TRANSVERSE TO SAID FUSELAGE, SAID WING ROTATION AXIS BEING LOCATED FORWARD OF THE CENTER OF LIFT OF SAID WINGS; AT LEAST ONE PROPELLER MOUNTED AT THE FORWARD EDGE OF EACH OF SAID RIGHT AND LEFT WINGS, SYMMETRICALLY WITH RESPECT TO SAID FUSELAGE, AND ADAPTED TO DIRECT A SLIPSTREAM REARWARD OVER SAID WING SURFACES; A PILOT-CONTROLLED CONTROL SURFACE AT THE TRAILING EDGE OF SAID WINGS, ROTATABLE ABOUT AN AXIS TRANSVERSE TO SAID FUSELAGE, AND DISPOSED IN THE SLIPSTREAM OF THE PROPELLER ON SAID WING; SAID FUSELAGE HAVING A TAIL ASSEMBLY SPACED TO THE REAR OF SAID WINGS; SAID TAIL ASSEMBLY HAVING STABILIZER CONTROL EXTENDING TO THE RIGHT AND LEFT OF SAID FUSELAGE AND FREELY ROTATABLE ABOUT A COMMON AXIS TRANSVERSE TO SAID FUSELAGE; PILOT-CONTROLLED SURFACES AT THE TRAILING EDGE OF EACH OF SAID RIGHT AND LEFT STABILIZERS, AND SAID STABILIZER CONTROL SURFACES HAVING AN AXIS OF ROTATION AT THE TRAILING EDGE OF SAID STABILIZERS; WING SUPPORT MEANS EXTENDING FROM EACH SIDE OF SAID FUSELAGE TO SAID WING, AND SUPPORTING SAID WING AT SAID AXIS OF ROTATION AT A POINT SUBSTANTIALLY OUTBOARD OF SAID FUSELAGE, SAID WING SUPPORT MEANS LIMITING THE ROTATION OF SAID WINGS ABOUT SAID WING ROTATION AXIS TO AN ANGLE AT WHICH THE VERTICAL COMPONENT OF THE WING''S LIFT IS AT LEAST AS GREAT AS THE VERTICAL COMPONENT OF THE PROPELLER''S THRUST.