Aircraft guide rail type composite launching device
Through the combined design of roller guide rail sliders and standard sliders, the complex structure and aerodynamic drag problems of the existing guide rail launcher are solved, and the stable linear gliding and rapid derailment of the aircraft are achieved, which enhances the reliability and safety of the device.
CN223200290UActive Publication Date: 2025-08-08INNER MONGOLIA INST OF POWER MASCH
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Patent Information
- Application Number
- CN202421977214.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-15
- Publication Date
- 2025-08-08
- Estimated Expiration
- 2034-08-15
AI Technical Summary
Technical Problem
The existing guide rail launcher has a complex structure, high weight and large aerodynamic resistance, which affects the aircraft's off-rail speed and stability.
Method used
The combination design of roller guide rail slider and standard slider is adopted, and is fixed with the aircraft through threaded connection, slot connection or welding, so as to achieve linear contact, share weight, reduce friction resistance, and simplify the structure.
Benefits of technology
The aircraft is achieved with a stable linear gliding, accelerating off-rail, reducing attitude angle changes caused by center of gravity offset, reducing aerodynamic drag and structural complexity, and improving reliability and safety.
✦ Generated by Eureka AI based on patent content.
Abstract
The utility model relates to the technical field of aircraft launching, in particular to a guide rail type composite launching device for an aircraft. Comprising a roller guide rail sliding block, a first standard sliding block, a second standard sliding block and a sliding guide rail, the roller guide rail sliding block, the first standard sliding block and the second standard sliding block are sequentially and fixedly connected with an aircraft, and the roller guide rail sliding block is in linear contact with the guide rail and can share the total missile weight borne by the standard sliding block; the multiple faces of the standard sliding block make contact with the guide rail, so that the aircraft can only keep linear sliding acceleration along the guide rail, and it is guaranteed that the aircraft directionally and stably slides on the guide rail in a linear mode. The first standard sliding block and the second standard sliding block are located on the two sides of the gravity center of the aircraft. The roller guide rail sliding block is formed by combining a supporting frame and six rollers, the supporting frame is in an I shape, the middle axial face of the supporting frame serves as the symmetry plane, and the two rows of rollers are distributed at the two ends. According to the utility model, not only are the structure and the installation process simplified, but also the reliability and the safety are enhanced.
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