# US 2016/0355259 A1 · Hardpoint Strain Reliefs

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- Number: US 2016/0355259 A1
- Document ID: US20160355259A1
- Status: Published application
- Kind: A1
- Application number: 15/171,984
- Filed: 2016-06-02
- Published: 2016-12-08
- Earliest claimed: 2015-06-03
- Assignees: Google Inc.
- Applicants: Google Inc.
- Inventors: Damon Vander Lind; Gregor Boone Cadman
- Web page: https://patentgrep.com/patent/US20160355259A1

## CPC

- B64D 1/08: the articles being load-carrying devices
- B64C 31/06: Kites (toy aspects A63H27/08; airborne towed targets, e.g. kites F41J9/10)
- F03D 9/255: {connected to electrical distribution networks; Arrangements therefor}
- F03D 9/32: on moving objects, e.g. vehicles
- B64C 27/04: Helicopters
- B64C 39/10: All-wing aircraft
- B64F 3/02: with means for supplying electricity to aircraft during flight
- B64U 10/60: Tethered aircraft
- B64U 30/20: Rotors; Rotor supports
- B64U 50/19: using electrically powered motors
- B64U 50/31: generated by photovoltaics
- B64U 2101/10: for generating power to be supplied to a remote station, e.g. UAVs with solar panels
- B64U 2201/104: using satellite radio beacon positioning systems, e.g. GPS
- Y02E 10/72: Wind turbines with rotation axis in wind direction
- Y02E 10/728: Onshore wind turbines
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64C: AEROPLANES; HELICOPTERS
- F03D: WIND MOTORS
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION

## Abstract

A hardpoint relief pad is described and includes a base surface, a hardpoint overlay, and a first stress relief area. The base surface is configured to conform to and be fixedly attached to an interior surface of an aerial vehicle wing. The hardpoint overlay protrudes above adjacent areas of the hardpoint relief pad and is adapted to conform to a hardpoint. The hardpoint protrudes from the interior surface of the wing and is configured to carry a load fixed to the hardpoint. The hardpoint overlay includes an oculus that is configured to allow the load to be fixed to the hardpoint through the hardpoint overlay. The first stress relief area protrudes above adjacent areas of the hardpoint relief pad and also forms a hollow cavity between the first stress relief area and the interior surface of the wing.

## Claims

### Claim 1

A hardpoint relief pad comprising:
a base surface, wherein at least a portion of the base surface is configured to conform to and be fixedly attached to an interior surface of an aerial vehicle wing;
a hardpoint overlay protruding above adjacent areas of the hardpoint relief pad and adapted to conform to a hardpoint protruding from the interior surface of the wing, wherein the hardpoint is configured to carry a load fixed to the hardpoint, further wherein the hardpoint overlay comprises an oculus configured to allow the load to be fixed to the hardpoint through the hardpoint overlay; and
a first stress relief area protruding above adjacent areas of the hardpoint relief pad and forming a hollow cavity between the first stress relief area and the interior surface of the wing, wherein the first stress relief area is configured to deform in one or more axes when stress is applied to the hardpoint via the load.

### Claim 2 (depends on 1)

The hardpoint relief pad of claim 1, further comprising:
a second stress relief area protruding above adjacent areas of the hardpoint relief pad and forming another hollow cavity between the second stress relief area and the interior surface of the wing.

### Claim 3 (depends on 2)

The hardpoint relief pad of claim 2, wherein the first stress relief area and the second stress relief area are symmetrically spaced about the hardpoint.

### Claim 4 (depends on 1)

The hardpoint relief pad of claim 1, wherein the first stress relief area is elongated along a longitudinal axis.

### Claim 5 (depends on 1)

The hardpoint relief pad of claim 1, wherein the first stress relief area is elongated along a longitudinal axis a first distance and is located a second distance from the hardpoint overlay, wherein the first distance is the same as the second distance.

### Claim 6 (depends on 1)

The hardpoint relief pad of claim 1, wherein the first stress relief area is circular and centered on the hardpoint.

### Claim 7 (depends on 2)

The hardpoint relief pad of claim 2, wherein the first and the second stress relief areas are circular and concentric about the hardpoint.

### Claim 8 (depends on 1)

The hardpoint relief pad of claim 1, wherein the first stress relief area is configured to deform along at least one of a longitudinal axis, a transverse axis, and a vertical axis.

### Claim 9 (depends on 1)

The hardpoint relief pad of claim 1, further comprising:
a second hardpoint overlay protruding above adjacent areas of the hardpoint relief pad and adapted to conform to a second hardpoint protruding from the interior surface of the wing, wherein the second hardpoint is also configured to carry the load, further wherein the second hardpoint overlay comprises an oculus configured to allow the load to be fixed to the second hardpoint through the second hardpoint overlay.

### Claim 10 (depends on 9)

The hardpoint relief pad of claim 9, further comprising:
at least two additional stress relief areas protruding above adjacent areas of the hardpoint relief pad and forming hollow cavities between the at least two additional stress relief areas and the interior surface of the wing, wherein the first stress relief area and the at least two additional stress relief areas are spaced symmetrically about the first and the second hardpoints.

### Claim 11 (depends on 1)

The hardpoint relief pad of claim 1, wherein the load fixed to the hardpoint comprises a load from a pylon or a tail boom.

### Claim 12

An aerial vehicle wing comprising:
a hardpoint protruding from an interior surface of the aerial vehicle wing, wherein the hardpoint is configured to carry a load fixed to the hardpoint; and
a first stress relief area integrated into the interior surface of the wing a first distance from the hardpoint, wherein the first stress relief area protrudes above adjacent areas of the interior surface of the wing forming a hollow cavity within the interior surface of the wing.

### Claim 13 (depends on 12)

The aerial vehicle wing of claim 12, wherein the first stress relief area is laminated into the interior surface of the wing.

### Claim 14 (depends on 12)

The aerial vehicle wing of claim 12, wherein the load fixed to the hardpoint comprises a load from a pylon or a tail boom.

### Claim 15 (depends on 12)

The aerial vehicle wing of claim 12, further comprising:
a second stress relief area integrated into the interior surface of the wing a second distance from the hardpoint, wherein the second stress relief area protrudes above adjacent areas of the interior surface of the wing forming another hollow cavity between the second stress relief area and the interior surface of the wing.

### Claim 16 (depends on 15)

The aerial vehicle wing of claim 15, wherein the first distance and the second distance are the same.

### Claim 17 (depends on 12)

The aerial vehicle wing of claim 12, wherein the first stress relief area is elongated along a longitudinal axis.

### Claim 18 (depends on 12)

The aerial vehicle wing of claim 12, wherein the first stress relief area is circular and centered on the hardpoint.

### Claim 19 (depends on 12)

The aerial vehicle wing of claim 12, wherein the first stress relief area is configured to deform along at least one of a longitudinal axis, a transverse axis, and a vertical axis when stress is applied via the load.

### Claim 20

An aerial vehicle comprising:
a pylon fixedly attached to a first hardpoint that protrudes from an interior surface of a wing of the aerial vehicle;
a tail boom fixedly attached to a second hardpoint that protrudes from the interior surface of the wing;
a first hardpoint relief pad corresponding to the first hardpoint; and
a second hardpoint relief pad corresponding to the second hardpoint, wherein each the first and the second hardpoint relief pad comprises:
a base surface, wherein at least a portion of the base surface is configured to conform to and be fixedly attached to the interior surface of the wing;
a hardpoint overlay protruding above adjacent areas of the hardpoint relief pad and adapted to conform to at least one of the first and the second hardpoints, wherein the hardpoint overlay comprises an oculus configured to allow the pylon or the tail boom to be fixed to the first or the second hardpoint through the hardpoint overlay;
a first stress relief area protruding above adjacent areas of the hardpoint relief pad and forming a hollow cavity between the first stress relief area and the interior surface of the wing, wherein the hardpoint relief pad is configured to deform in one or more axes when stress is applied to the first or the second hardpoint via the pylon or the tail boom.