A method and apparatus comprising a composite spar. The composite spar has a root section and a main section. The root section is closed and has a shape configured to be connected to a blade retention system. The main section has an open channel. The composite spar is configured for placement inside
A method and apparatus comprising a composite spar. The composite spar has a root section and a main section. The root section is closed and has a shape configured to be connected to a blade retention system. The main section has an open channel. The composite spar is configured for placement inside of a blade.
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1. An apparatus comprising: a root section for a composite spar, such that the root section is configured to be connected to a blade retention system and comprises: a central group of composite material layers configured as a central axis of a wedge, the central group of composite material layers en
1. An apparatus comprising: a root section for a composite spar, such that the root section is configured to be connected to a blade retention system and comprises: a central group of composite material layers configured as a central axis of a wedge, the central group of composite material layers encircled by a layer that comprises a first number of weave plies, such that after a first ply in the first number of weave plies wraps around the central group, a first end of each ply of the first number of weave plies overlaps a second end of each ply of the first number of weave plies;a second group of composite material layers set around the first number of weave plies;additional alternating layers of additional weave plies such that each additional layer of weave plies wraps around an immediately interior second group of composite material layers that set around an immediately interior layer of additional weave plies until a final layer of weave plies forms an outer layer of the root section, such that after a first ply in the final layer of weave plies wraps around the immediately interior group of composite material, a first end of each ply of the final layer of weave plies overlaps a second end of each ply of the final layer of weave plies, and the root section comprises layers that form a wedge shape; anda main section for the composite spar, wherein the main section comprises an open channel that comprises a cap, a first flange, and a second flange, the composite spar being configured such that a compilation of the groups of composite material layers extend from the root section and increase a thickness of the cap, the first flange, and the second flange, and fills the channel at the root section. 2. The apparatus of claim 1, wherein the root section is substantially solid. 3. The apparatus of claim 2 further comprising: a transition section that changes from being substantially solid in the root section to having the open channel in the main section. 4. The apparatus of claim 1, wherein the shape is configured to be connected to the blade retention system without drilling holes in the root section. 5. The apparatus of claim 1, wherein the composite spar comprises: the cap;a first web;a second web;the first flange; andthe second flange, wherein the cap, the first web, and the second web, form walls that define the channel in the main section of the composite spar and wherein layers of unidirectional plies and layers of weave plies form the cap, the first web, the second web, the first flange, and the second flange with a solid section at the root section of the composite spar. 6. The apparatus of claim 1, wherein a cross section of the composite spar has an omega shape. 7. The apparatus of claim 5 further comprising: a first composite skin; anda second composite skin, wherein the first composite skin and the second composite skin are bonded to the composite spar to form the blade, wherein the first flange and the second flange of the composite spar are bonded to a first interior surface of the first composite skin of the blade and the cap is bonded to a second interior surface of the second composite skin. 8. The apparatus of claim 7 further comprising: a core filling cavities in an interior of the blade. 9. The apparatus of claim 1, wherein the composite spar is comprised of a plurality of layers of unidirectional plies and a plurality of weave plies laid up in a layup sequence to form the root section, a transition section, and the main section having the shape configured to be connected to the blade retention system. 10. The apparatus of claim 1 further comprising: a collet having a first piece and a second piece, wherein the collet is configured to retain at least a portion of a solid section with the wedge shape. 11. A method for manufacturing a composite structure, the method comprising: forming a composite spar comprising a root section and a main section comprising an open channel along a length of the composite spar via: laying up a first type of layers comprising a first number of weave plies comprising composite material;laying up a group of second type of layers of composite material on the first number of weave plies;laying up a second number of weave plies on the second type of layers;forming the root section of the composite spar via the group of second type of layers of composite material filling the open channel at the root section to form a closed wedge shape for the root section, and maintaining the channel in the main section.via a number of groups of second type of layers of composite material increasing a thickness of a cap, a first flange, and a second flange for the composite spar in the root section and folding over the first number of weave plies after the second number of weave plies are laid up, wherein the first number of weave plies are folded over in a reverse order from an order in which the first number of weave plies was laid up; andrepeating the steps of laying up the first number of weave plies comprising composite material for the composite spar and laying up the group of second type of layers of composite material for the composite spar until a plurality of layers of composite material for the composite spar is complete, wherein the root section has a shape configured to be connected to a blade retention system. 12. The method of claim 11 further comprising: bonding the composite spar to a first skin for a composite blade; andbonding a second skin for the composite blade to the composite spar and the first skin, wherein the main section extends from the root section towards a tip of the composite blade. 13. The method of claim 11, wherein the root section has the shape configured to be retained by the blade retention system based entirely on the shape of the root section and a corresponding shape of the blade retention system without forming holes for fasteners in the root section. 14. The method of claim 11, wherein the group of second type of layers of composite material is configured to form a solid section in the root section of the composite spar and the solid section of the root section is configured to distribute loads on the composite structure throughout the root section. 15. The method of claim 11, wherein the group of second type of layers of composite material has a number of lengths selected to provide desired properties for a section along a length of the composite structure. 16. A method for operating a vehicle, the method comprising: rotating a propeller with blades;forming a composite spar comprising a root section and a main section comprising an open channel along a length of the composite spar via: laying up a first type of layers comprising a first number of weave plies comprising composite material;laying up a group of second type of layers of composite material on the first number of weave plies;laying up a second number of weave plies on the second type of layers;forming the root section of the composite spar via the group of second type of layers of composite material filling the open channel at the root section to form a closed wedge shape for the root section, and maintaining the channel in the main section.via a number of groups of second type of layers of composite material increasing a thickness of a cap, a first flange, and a second flange for the composite spar in the root section and folding over the first number of weave plies after the second number of weave plies are laid up, wherein the first number of weave plies are folded over in a reverse order from an order in which the first number of weave plies was laid up;repeating the steps of laying up the first number of weave plies comprising composite material for the composite spar and laying up the group of second type of layers of composite material for the composite spar until a plurality of layers of composite material for the composite spar is complete; andretaining a blade of the blades through the root section of a spar in the blade of the blades being retained to a blade retention system, wherein the root section is shaped and configured to be retained within a corresponding shape for the blade retention system entirely by the shape of the root section and the corresponding shape of the blade retention system. 17. A blade system comprising: a blade having a root section shaped and configured to be retained within a correspondingly shaped blade retention system entirely by a shape of the root section and a corresponding shape of the blade retention system, such that the root section comprises: a central group of composite material layers configured as a central axis of a wedge, the central group of composite material layers encircled by a layer that comprises a first number of weave plies, such that after a first ply in the first number of weave plies wraps around the central group, a first end of each ply of the first number of weave plies overlaps a second end of each ply of the first number of weave plies;a second group of composite material layers set around the first number of weave plies;additional alternating layers of additional weave plies such that each additional layer of weave plies wraps around an immediately interior second group of composite material layers that set around an immediately interior layer of additional weave plies until a final layer of weave plies forms an outer layer of the root section, such that after a first ply in the final layer of weave plies wraps around the immediately interior group of composite material, a first end of each ply of the final layer of weave plies overlaps a second end of each ply of the final layer of weave plies, and the root section comprises layers that form a wedge shape, such that a compilation of the groups of composite material layers extend from the root section and increase a thickness of a cap, a first flange, and a second flange, of a main section of a spar in the blade, and fills a channel in the main section at the root section. 18. The blade system of claim 17, wherein the root section is part of the spar in the blade. 19. The blade system of claim 18, wherein the spar is comprised of a material selected from one of a composite material, a metal, a metal alloy, aluminum, titanium, and steel. 20. The blade system of claim 17, wherein the shape of the root section is selected to reduce undesired loads on the root section during operation of a platform using the blade retention system. 21. The blade system of claim 17, wherein the shape of the root section is configured to be retained by the corresponding shape in a collet in the blade retention system without fasteners.
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