一种航空航天异型壳体工装
By designing a sliding block and slip ring structure driven by multiple sets of clamping components and threaded rods, the internal and external clamping switching of irregularly shaped housing tooling was realized, which solved the problem of insufficient flexibility of existing tooling and improved the fixing effect and adaptability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Filing Date
- 2025-04-23
- Publication Date
- 2026-07-17
AI Technical Summary
Existing tooling is difficult to fix irregularly shaped shells from both inside and outside simultaneously, and it is also difficult to switch between fixing methods, resulting in insufficient flexibility.
A tooling for aerospace irregular-shaped housings was designed, which uses multiple sets of clamping components, including an outer clamping rod and an inner clamping rod. The slide block and slip ring are driven by a threaded rod to achieve external and internal clamping. The outer clamping rod cooperates with the top slide groove and the oblique slide groove, while the inner clamping rod achieves internal wall clamping through the oblique slide groove and the transverse slide groove, allowing for flexible switching of clamping methods.
It enables flexible fixing of irregularly shaped shells, allowing for both external clamping and internal limiting, thus improving the flexibility and adaptability of the tooling and meeting the fixing needs of different irregularly shaped shells.
Smart Images
Figure CN224509389U_ABST
Abstract
Claims
1. An aerospace non-orthogonal shell tooling, characterized by, include: The base (1) has multiple sets of top sliding grooves (2) arranged in a ring at equal intervals on its top. Multiple clamping components (3), each clamping component (3) includes a slide (9), an outer clamping rod (12) and an inner clamping rod (5). The slide (9) is slidably connected in the corresponding top slide groove (2). A first threaded rod (6) is rotatably connected to one side of the top slide groove (2). One end of the first threaded rod (6) extends through to the outside of the base (1) and is threadedly connected to the slide (9). The top of the slide block (9) is provided with a movable groove (15), the bottom end of the outer clamping rod (12) is fixed to one side of the movable groove (15), the inner walls of both sides of the movable groove (15) are provided with inclined sliding grooves (14) and transverse sliding grooves (13) communicating with the inclined sliding grooves (14), and the inner clamping rod (5) is fixed with side rods on both sides, and the side rods are slidably engaged with the corresponding inclined sliding grooves (14) and transverse sliding grooves (13). The bottom of the movable groove (15) is provided with a bottom groove (8), and a second screw (11) is provided in the bottom groove (8). One end of the second screw (11) extends to the outside of the base (1). A slip ring (7) is slidably provided in the bottom groove (8). The slip ring (7) is threadedly connected to the second screw (11). A top rod (4) is fixed on the top of the slip ring (7). The inner clamping rod (5) is sleeved on the outer periphery of the top rod (4). When the second screw (11) is rotated, the side rod rises along the inclined slide groove (14) to the horizontal slide groove (13), and then the inner clamping rod (5) moves horizontally to abut against the inner wall of the housing.
2. The aerospace contoured shell tooling of claim 1, wherein, The base (1) has multiple through holes (10) on its side, and the end of the second screw (11) passes through the through holes (10) and extends to the outside of the base (1).
3. The aerospace contoured shell tooling of Claim 1, wherein, The inclined angle of the inclined slide (14) is 30°-60°, and the extension direction of the horizontal slide (13) is parallel to that of the top slide (2).
4. The aerospace contoured shell tooling of any one of claims 1-3, wherein, The ends of the outer clamping rod (12) and the inner clamping rod (5) are provided with anti-slip rubber layers.
5. The aerospace contoured shell tooling of Claim 1, wherein, The number of top sliding grooves (2) is 3-6 sets, and each set of top sliding grooves (2) is provided with at least one clamping member (3).
6. The aerospace contoured shell tooling of Claim 1, wherein, Both the first threaded rod (6) and the second threaded rod (11) are equipped with handwheels or hexagonal heads at their ends.
7. The aerospace contoured shell tooling of Claim 1, wherein, A linear guide rail is provided between the slide block (9) and the top slide groove (2), and the bottom of the slide block (9) is fitted with balls.
8. The aerospace contoured shell tooling of Claim 1, wherein, The top rod (4) and the inner clamping rod (5) are connected by an interference fit or a key.