초록 ▼

Described herein is a rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position. The rigid rotor assembly includes a base including a shaft extending therethrough, a first spindle configured to enga

Described herein is a rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position. The rigid rotor assembly includes a base including a shaft extending therethrough, a first spindle configured to engage the shaft, and a second spindle configured for placement onto the shaft. The second spindle is operable to maintain a first position with respect to the first spindle via an attachment mechanism therebetween, the second spindle further operable to maintain a second position with respect to the first spindle via the attachment mechanism.

대표청구항 ▼

1. A rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position, the rigid rotor assembly comprising: a) a base comprising a shaft extending therethrough;b) a first spindle comprising a first apertur

1. A rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position, the rigid rotor assembly comprising: a) a base comprising a shaft extending therethrough;b) a first spindle comprising a first aperture, the first spindle configured to engage the shaft, the first spindle further configured to have a first plurality of rotor blades attached thereto; andc) a second spindle comprising a second aperture and a third aperture, the second spindle configured to have a second plurality of rotor blades attached thereto, the second spindle further configured for placement onto the shaft, the second spindle operable to maintain the second plurality of rotor blades in a deployed position with respect to the first plurality of rotor blades via a first retention pin inserted through the first aperture and the second aperture, the second spindle further operable to maintain the second plurality of rotor blades in a stowed position with respect to the first plurality of rotor blades by removing the first retention pin from the first aperture and the second aperture and inserting the first retention pin or a second pin through the first aperture and the third aperture. 2. The rigid rotor assembly according to claim 1, wherein: the shaft comprises a spline formed thereon; andthe first spindle is configured to engage the spline formed on the shaft. 3. The rigid rotor assembly according to claim 1, wherein the shaft further comprises a nut configured to ensure retention of the first spindle and the second spindle to the shaft under flight loading. 4. A helicopter comprising: a forward section;a tail section rearward of the forward section; anda rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position, the rigid rotor assembly comprising:a first spindle attached to a rotor shaft, the first spindle comprising a first plurality of rotor blades attached thereto and a first aperture; anda second spindle, the second spindle comprising a second plurality of rotor blades attached thereto, a second aperture, a third aperture, and a hub opening operable for placing the second spindle onto the shaft, the second spindle operable for maintaining the second plurality of rotor blades in a deployed position with respect to the first plurality of rotor blades by inserting a first retention pin through the first aperture and the second aperture, the second spindle further operable for maintaining the second plurality of rotor blades in a stowed position with respect to the first plurality of rotor blades by removing the first retention pin from the first aperture and the second aperture and inserting the first retention pin or a second retention pin through the first aperture and the third aperture. 5. The helicopter according to claim 4, wherein the first spindle is attached to the shaft via a spline. 6. The helicopter according to claim 4, wherein the shaft further comprises a nut configured to ensure retention of the first spindle and the second spindle to the shaft under flight loading. 7. A method for rotating helicopter rotor blades coupled to a rigid rotor assembly from a deployed position to a stowed position, the method comprising: removing at least one retention pin from a first aperture on a first spindle and a second aperture on a second spindle, the first aperture being aligned with the second aperture, the spindles configured for attachment of rotor blades thereto;rotating the first spindle about an axis of the rigid rotor assembly such that the first aperture on the first spindle is aligned with a third aperture on the second spindle; andinserting the at least one retention pin into the first aperture and the third aperture. 8. The method according to claim 7, wherein: alignment of the first aperture and the second aperture is operable to place rotor blades associated with the spindles into a deployed position; andalignment of the first aperture and the third aperture is operable to place rotor blades associated with the spindles into a stowed position. 9. The method according to claim 8, wherein the stowed position describes a first portion of the rotor blades extending generally toward a forward section of a helicopter and a second portion of the rotor blades extending generally toward a tail section of the helicopter.