SITIS Topic Details |
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| Proposals Accepted: | |
| Program: | SBIR |
| Topic Number: | AF103-006 (AirForce) |
| Title: | Unitized Composite Airframe Structures with Three Dimensional (3-D) Preforms for Elevated Temperature Applications | Research & Technical Areas: | Air Platform, Materials/Processes |
| Objective: | Develop & apply novel joining concepts for unitized composite airframe structure using 3D textile preforms (woven, braided, warp-knitted, etc.) w/thermal gradient for elevated temperature applications
| Description: | Composite airframe design is driven by strength, durability, damage tolerance, temperature suitability, and sustainment requirements. Some novel solutions, using textile preforms and the through-thickness stitching methods, have been developed for specific airframe structures to avoid the weight and cost penalties associated with fasteners-[1, 2]. This has resulted in new approaches for “damage-arrest” designs in composite structures. However, higher levels of airframe unitization require that solutions be developed to solve for the integration of dissimilar materials to accommodate varying temperature gradients in a structure.
This topic seeks novel concepts and methods of manufacturing complex airframe composite structures using components reinforced with 3-D textile preforms subjected to elevated temperature gradient applications. This will be achieved by infusing multiple matrix materials into the textile structural architecture, each featuring a distinct temperature capable regime. Components may include skin, stiffeners and frames. Two principal requirements include: 1) delamination propagation must be arrested, without degradation to the structural performance, and 2) the textile joint must be impregnated with a minimum of two different temperature class resins and/or metals. The textile itself can be a metallic, carbon, or glass perform, or a combination of fibers. Example matrix materials could include the use of high temperature polyimide, bismaleimide, and epoxy, all impregnated into the same textile skin/joint architecture.
| PHASE I: Design & demonstrate an innovative small prototype unitized composite structural component w/ integral skin & stiffeners impregnated w/ two or more matrix materials & cured/consolidated as a single piece. This can be achieved by staging the resins to control flow & inhibit chemical incompatibilities
| PHASE II: Demonstrate material property sustainability, in the elevated temperature range, on a large unitized composite structure. Perform preliminary analysis, design, fabrication and conduct testing of the unitized composite structure to demonstrate predictability of its properties and structural response.
| PHASE III | DUAL USE COMMERCIALIZATION:
Military Application: The structural technology developed will be applicable to transports, fighters, supersonic long-range, strike and hypersonic vehicles.
Commercial Application: The technology will be applicable to commercial aircraft.
| References: |
1. A. Velicki and P. Thrash, “Advanced Structural Concept Development Using Stitched Composites,” Proc. of the 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 7-10 April, 2008, Schaumburg, IL, AIAA Paper 2008-2329. 2. A. Velicki, P.J. Thrash, and A.V. Hawley, “Preliminary Design Requirements,” Damage Arresting Composites for Shaped Vehicles, Contract NNL07AA48C, Report for 20 December 2007. 3. A.E. Bogdanovich and M.H. Mohamed, “Three-Dimensional Reinforcements for Composites,” SAMPE Journal, Vol. 45, No. 6, November/December 2009, pp. 8-28. 4. J. Brandt, K. Drechsler, and F.-J. Arendts, “Mechanical Performance of Composites Based on Various Three-Dimensional Woven-Fibre Preforms,” Composites Science and Technology, Vol. 56, 1996, pp. 381-386. 5. D. Mungalov and A. Bogdanovich, “Complex Shape 3-D Braided Composite Preforms: Structural Shapes for Marine and Aerospace,” SAMPE Journal, Vol. 40, No. 3, May/June 2004, pp. 7-20. |
| Keywords: | composites, 3-D preform, airframe structures, unitized composites, elevated temperature, thermal gradient |
Questions and Answers: |
No questions posed on this topic at this time |
As of midnight September 1, questions for solicitations SBIR 10.3 and STTR 10.B will no longer be accepted.
To read the solicitation for full proposal preparation and submission details click here. |