IP Library › Granted Patent US 9,889,940
Granted Patent B2
US 9,889,940 · App. 15/434,288 · Granted Feb 13, 2018

Deicing apparatuses comprising at least one standoff

Inventor: Peter Lenkey (Culver City, CA)
B64D15/163B64D15/16B64D33/02B64D2033/0233
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Quick Facts
Patent No.
US 9,889,940
App. No.
15/434,288
Granted
Feb 13, 2018
Kind
B2
Abstract

Apparatuses for and methods of deicing aircraft surfaces, engine inlets, windmill blades and other structures. Deicing apparatuses can comprise at least one standoff coupled with an actuator and a first region of an inner surface of a skin. A standoff can act as a moment arm and can create efficient, tailorable skin bending and acceleration, breaking an ice to skin bond. Integral as well as modular leading edges can comprise deicing apparatuses.

Claims (50)

1. An aircraft leading edge electro-expulsive deicing apparatus comprising:

a leading edge comprising a skin;

said skin comprising first and second regions;

a first standoff coupled with said first region;

an actuator comprising:

electrical conductors;

wherein at least one first conductor is coupled with said first standoff;

wherein at least one second conductor is coupled with said skin second region;

a second standoff interposed between and coupling said at least one second conductor and said skin second region;

wherein said at least one first and second conductors are positioned proximate to each other;

wherein said at least one first and second conductors are electrically coupled with a deicing control system; and

a third standoff proximate to said first standoff and coupled to a skin third region;

said third standoff being configured to receive an impact from said first standoff and to communicate said impact from said first standoff to a skin third region.

2. The aircraft leading edge electro-expulsive deicing apparatus of claim 1 , further comprising:

a fourth standoff proximate to said second standoff and coupled to a skin fourth region;

said fourth standoff being configured to receive an impact from said second standoff and to communicate said impact from said second standoff to said skin fourth region.

3. A method of deicing an aircraft leading edge comprising:

providing an aircraft leading edge electro-expulsive deicing apparatus comprising:

a leading edge comprising a skin;

said skin comprising first and second regions;

a first standoff coupled with said first region;

an actuator comprising:

electrical conductors;

wherein at least one first conductor is coupled with said first standoff;

wherein at least one second conductor is coupled with said second region;

a second standoff interposed between and coupling said at least one second conductor and said skin second region;

wherein said at least one first and second conductors are positioned proximate to each other;

wherein said at least one first and second conductors are electrically coupled with a deicing control system; and

a third standoff proximate to said first standoff and coupled to a skin third region;

said third standoff being configured to receive an impact from said first standoff and to communicate said impact from said first standoff to a skin third region;

creating forces on said at least one first and second conductors by passing current pulses through said at least one first and second conductors; and

communicating said forces on said at least one first and second conductors to said skin first, second and third regions to deice said surface.

4. The method of deicing an aircraft leading edge of claim 3 , further comprising:

providing a fourth standoff proximate to said second standoff and coupled to a skin fourth region;

said fourth standoff being configured to receive an impact from said second standoff and to communicate said impact to a skin fourth region; and

wherein the step of communicating said forces on said at least one first and second conductors includes communicating said forces to said skin fourth region.

5. An electro-expulsive apparatus comprising:

an object comprising a surface;

said surface comprising first and second regions;

a first standoff coupled with said first region;

an actuator comprising:

electrical conductors;

wherein at least one first conductor is coupled with said first standoff;

wherein at least one second conductor is coupled with said second region;

a second standoff interposed between and coupling said at least one second conductor and said skin second region;

wherein said at least one first and second conductors are positioned proximate to each other;

wherein said at least one first and second conductors are electrically coupled with a deicing control system; and

a third standoff positioned proximate to said first standoff and coupled to a surface third region; and

said third standoff being configured to receive an impact from said first standoff and to communicate said impact from said first standoff to the surface third region; and

wherein said deicing control system is configured to pass current pulses through said at least one first and second conductors, thereby creating forces in said at least one first and second conductors to shed ice from the surface of the object.

Continuity (2)
Provisional Application 62296053 · Feb 16, 2016
Related Publication 20170233085A1 · Aug 17, 2017