Manufacturing method of aircraft control surface and aircraft control surface
Through the integrated manufacturing method, a single composite prefabricated part is used to cure to form an integrated box and mechanically connect it, which solves the problems of many parts and complex components of the aircraft control surface, and realizes a high-strength and lightweight control surface with low cost, short time and convenient maintenance.
CN116161215BActive Publication Date: 2025-08-01AIRBUS OPERATIONS SL
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Patent Information
- Application Number
- CN202211135867.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Priority Date
- 2021-11-24
- Filing Date
- 2022-09-19
- Publication Date
- 2025-08-01
- Estimated Expiration
- 2042-09-19
AI Technical Summary
Technical Problem
The existing aircraft control surface has a large number of parts, complex components, high cost, long assembly time and inconvenient maintenance.
Method used
Using an integrated manufacturing method, a single composite prefabricated piece including upper skin, lower skin and ribs is used to cure it once to form an integrated box, reducing parts and components, and assemble using mechanical connectors such as T-components and non-metallic inserts.
Benefits of technology
The control surface is fully integrated, reducing the number of parts and components, reducing costs, simplifying assembly time, improving maintenance convenience, shortening lead time, and improving strength and lightweight effects.
✦ Generated by Eureka AI based on patent content.
Abstract
A manufacturing method of an aircraft control surface, the control surface comprising: an upper skin (1), a lower skin (2), and wing ribs (3) connecting the upper skin (1) and the lower skin (2) and located in the chord direction of the control surface, wherein the manufacturing method comprises the following steps: providing a single composite preform comprising the upper skin (1), the lower skin (2), and the wing ribs (3), and curing the single composite preform to form an integral box body (10) of the upper skin (1), the lower skin (2), and the wing ribs (3).
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