Oblique nose cone of carrier rocket
By designing the combined structure of the launch vehicle slanted cone, the force transmission path is simplified, and the problems of complex force transmission path and high processing cost in the existing technology are solved, achieving the effects of low aerodynamics and low processing cost.
CN222689004UActive Publication Date: 2025-03-28ORIENTAL SPACE TECH (SHANDONG) CO LTD +1
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Patent Information
- Application Number
- CN202421538853.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-02
- Publication Date
- 2025-03-28
- Estimated Expiration
- 2034-07-02
AI Technical Summary
Technical Problem
The main bearing position of the existing launch vehicle ramp cone is located at the back end, and the force transmission path is complex, resulting in high processing costs.
Method used
A carrier rocket bevel cone is designed, which adopts a combined structure of end body, main bearing component and main body component. The main bearing component includes a bundled shell and a carrier. Through the bundled connection and skin stringer structure, the force transmission path is simplified.
Benefits of technology
It has achieved simplification of load-bearing and transfer mode, reduced pneumatic power, simple and reliable solution, low processing cost, and has hoisting support ears, which are easy to lift and transport.
✦ Generated by Eureka AI based on patent content.
Abstract
The utility model discloses an inclined nose cone of a carrier rocket, which belongs to the field of spacecraft structure design and comprises an end body, a main bearing component and a main body component. The main bearing component is arranged between the end body and the main body component; the upper end of the binding shell is fixedly connected with the end body, and the lower end is fixedly connected with the body component. The main bearing part comprises a binding shell and a bearing part used for binding connection and diffusing concentrated loads. The main body part is of a skin stringer structure and is in a hollow inclined cone shape; the main body part comprises a main shell and a shell rigid bearing part; the shell rigid bearing part is of a cage type structure, is fixedly connected with the main shell part and is used for ensuring the strength and rigidity of the main body part; a lower end frame is fixedly arranged at the lower end of the main shell. The oblique nose cone of the carrier rocket is simple in bearing force transmission mode, low in aerodynamic force, simple and reliable in scheme and low in machining cost.
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