一种直升机桨叶用热缩性芯模气囊结构设计方法
By designing a heat-shrinkable mandrel airbag structure and using a combination of heated heat-shrinkable materials and support rods with mortise and tenon splicing technology, the problems of insufficient rigidity and difficult demolding in the manufacturing of large-size composite material blade hollow beams were solved, achieving high-precision and low-cost manufacturing results.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- 哈尔滨哈飞航空工业有限责任公司
- Filing Date
- 2022-12-09
- Publication Date
- 2026-07-17
AI Technical Summary
Traditional mandrels suffer from insufficient stiffness, excessive weight, difficulty in demolding, high cost, and uneven compaction in the manufacturing of large-size helicopter composite material rotor blade hollow beams, making it difficult to meet the manufacturing requirements of large-size, variable cross-section hollow beams.
A heat-shrinkable mandrel airbag structure is designed. The mandrel is manufactured by heating heat-shrinkable material, and the outer surface is covered with a proportionally shrinkable airbag. Support rods are added inside. The airbag mold is formed by mortise and tenon splicing process and vacuum membrane laying method, achieving high rigidity and easy demolding.
It improves manufacturing precision and the layup effect of composite materials, ensuring that the inner surface of the product is smooth, dense, and strong, solving the problems of step difference and wrinkles caused by traditional core molds, and reducing manufacturing costs.
Smart Images
Figure CN115795685B_ABST