Stowed blade pneumatic clamp

1. An aircraft comprising:

a foldable proprotor blade;

a fluidic clamp comprising a first inflatable bladder and a pressurized fluid source in fluid connection with the first inflatable bladder, the first inflatable bladder positioned on a first side of an opening for receiving a portion of the foldable proprotor blade in a folded position;

a pylon rotatable relative to a wing;

a proprotor assembly carried by the pylon, the proprotor assembly comprising the foldable proprotor blade, the foldable proprotor blade being foldable to a stowed position extending substantially parallel to the pylon; and

wherein the fluidic clamp is positioned within the pylon and is configured to grip the foldable proprotor blade when the foldable proprotor blade is in the stowed position.

2. The aircraft of claim 1 , wherein the fluidic clamp is exposed at an outer mold line of a pylon fairing.

3. The aircraft of claim 1 , wherein the foldable proprotor blade comprises a tab extending from a trailing edge of the foldable proprotor blade, the tab being configured to be gripped by the fluidic clamp.

4. The aircraft of claim 1 , wherein the pressurized fluid source is located inside of a pylon fairing.

5. The aircraft of claim 1 , further comprising a compliant member positioned on a second side of the opening opposite from the first inflatable bladder.

6. The aircraft of claim 1 , further comprising a second inflatable bladder positioned on a second side of the opening opposite from the first inflatable bladder.

7. The aircraft of claim 1 , comprising:

a second inflatable bladder positioned on a second side of the opening opposite from the first inflatable bladder;

a controller in connection with the pressurized fluid source to selectively inflate the first and the second inflatable bladder; and

a sensor in communication with the controller and configured to sense a position of a proprotor blade.

8. The aircraft of claim 1 , wherein the portion of the foldable proprotor blade is a tab extending from a trailing edge of the foldable proprotor blade.

9. The aircraft of claim 1 , wherein the pressurized fluid source comprises at least one of a gas and a liquid.

10. The aircraft of claim 1 , further comprising a controller in connection with the pressurized fluid source to selectively inflate the first inflatable bladder.

11. The aircraft of claim 1 , further comprising:

a controller in connection with the pressurized fluid source to selectively inflate the first inflatable bladder; and

a sensor in communication with the controller and configured to sense a position of a proprotor blade.

12. A method comprising:

transitioning a tiltrotor aircraft from rotary flight to non-rotary flight;

wherein in non-rotary flight a proprotor blade has been folded to a stowed position extending substantially parallel to a pylon; and

gripping, in the stowed position, a portion of the proprotor blade with a fluidic clamp.

13. The method of claim 12 , wherein the portion comprises part of a trailing edge of the proprotor blade.

14. The method of claim 12 , wherein the portion is a tab extending from a trailing edge of the proprotor blade.

15. The method of claim 12 , wherein the fluidic clamp comprises:

a first inflatable bladder positioned on a first side of an opening for receiving a portion of a proprotor blade;

a second inflatable bladder positioned on a second side of the opening opposite from the first inflatable bladder; and

a pressurized fluid source in fluid connection with the first inflatable bladder.