Integrated propulsion/lift/control system for aircraft and ship applications
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorMaximilian F. Platzer
Life of this patent
Estimating the term…
Abstract
A new method for boundary layer energization and boundary layer propulsion or use on vehicles moving through fluids, which comprises mounting small airfoils parallel or perpendicular to the vehicle's surface, said airfoils being embedded within the said vehicle's boundary layer and juxtaposed the surface of said vehicle, said airfoils being approximately the height of the boundary layer thickness and exciting said airfoils into flapping oscillation parallel to the chord plane of said airfoils, said oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoil, whereby flow separation is delayed or suppressed which enables the redesign of said vehicle.
Claims16
A new method for boundary layer energization and boundary layer propulsion for use on vehicles moving through fluids, which comprises:
- mounting at least one small airfoil parallel to said vehicle's surface, said airfoil being embedded within said vehicle's boundary layer;
- and
- exciting said airfoil into flapping oscillation parallel to the chord plane of said airfoil at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoil for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-energizing and accelerating the boundary layer and thereby preventing flow separation and wake formation, whereby flow separation is delayed or suppressed on said vehicle which enables the re-design of the shape of said vehicle.
A new method for energization and suppression of wakes shed from vehicles moving through fluids, which comprises:
- mounting at least one airfoil in said vehicle's wake;
- and
- exciting said airfoils into a flapping oscillation parallel to the chord plane of said airfoil, with a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoil for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-energizing and accelerating the boundary layer and thereby preventing flow separation and wake formation.
A new method for energization and suppression of wakes shed from vehicles moving through fluids, which comprises:
- mounting a pair of airfoils in said vehicle's wake;
- and
- exciting said airfoils into a flapping oscillation whereby said airfoils are flapping in counterphase, said oscillation occurring parallel to the chord plane of said airfoils at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoils for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-eneroizing and accelerating the boundary layer and thereby preventing flow separation and wake formation.
A new method for boundary layer energization of fluids moving through a structure, which comprises:
- mounting at least one small airfoil proximate the fluid boundary and juxtaposed the surface of said structure;
- and
- exciting said airfoils into a flapping oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoils for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-energizing and accelerating the boundary layer and thereby preventing flow separation and wake formation, whereby flow separation is delayed or suppressed which enables the reconfiguration of the surface of said structure.
A new method for boundary layer energization and boundary layer propulsion for use on vehicles moving through fluids, which comprises:
- mounting small airfoils perpendicular to the vehicle's surface, said airfoils being embedded within the said vehicle's boundary layer and juxtaposed the surface of said vehicle, said airfoils being approximately the height of the boundary layer thickness;
- and
- exciting said airfoils into flapping oscillation parallel to the chord plane of said airfoils, said oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoil for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-energizing and accelerating the boundary layer and thereby preventing flow separation and wake formation, whereby flow separation is delayed or suppressed which enables the reconfiguration of said vehicle.
A new method of generating thrust for use on vertical/short take-off and landing (V/STOL) aircraft, which comprises:
- mounting at least one airfoil proximate to and parallel to said aircraft's fuselage;
- and
- exciting said airfoil into a flapping oscillation parallel to the chord plane of said airfoil, said oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of said chord length of said airfoil for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-energizing and accelerating the boundary layer and thereby preventing flow separation and wake formation.
A new method of generating thrust for use on vertical/short take-off and landing (V/STOL) aircraft, which comprises:
- mounting at least one pair of airfoils proximate to and parallel to said aircraft's fuselage;
- and
- exciting said pair of airfoils into a counter-phase type of flapping oscillation parallel to the chord plane of said airfoils, said oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoils for generating a jet flow downstream of the airfoil as a direct result of its oscillation for the purpose of re-energizing and accelerating the boundary layer and thereby preventing flow separation and wake formation, whereby ajet flow is generated by said flapping airfoils which is directed into a thrust augmenting ejector.
Dependencies are inferred from the claim text.