一种飞机吊舱静力试验加载装置

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By combining motor-driven worm gear transmission and electric push rod, the static test loading device for aircraft pods accurately simulates the actual flight stress state, solving the problem that existing technologies cannot simulate complex stress states, and improving test efficiency and data accuracy.

CN224511470UActive Publication Date: 2026-07-17XIAN HANGFENG TESTING TECH CO LTD

Patent Information

Authority / Receiving Office: CN · China
Patent Type: Utility models(China)
Current Assignee / Owner: XIAN HANGFENG TESTING TECH CO LTD
Filing Date: 2025-07-07
Publication Date: 2026-07-17

AI Technical Summary

Technical Problem

Existing static test loading devices for aircraft pods cannot simulate the complex stress state of an aircraft in actual flight, resulting in deviations between test results and actual operating conditions.

Method used

The first motor drives the first worm gear transmission to rotate the rotating ring and transmission ring, causing the slide bar to slide in the arc-shaped groove. Combined with the second motor driving the second worm gear transmission, the clamping block is evenly clamped. Through the combination of electric push rod and static pressure block, precise static loads can be applied to the pod from different directions to simulate the force state in actual flight.

Benefits of technology

It significantly improves the efficiency and data accuracy of the test, ensures the stability of the clamping and the flexibility of the loading direction, and meets the needs of different aircraft pods and diverse static tests.

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Abstract

本实用新型公开了一种飞机吊舱静力试验加载装置，属于飞机吊舱静力试验领域，包括底座和飞机吊舱，底座的顶端设置有夹持固定组件，夹持固定组件的前方设置有静力试验组件，飞机吊舱位于夹持固定组件和静力试验组件的内部；静力试验组件包括固定安装于底座顶端的固定座，通过第一电机驱动第一蜗杆蜗轮传动，带动旋转环及传动环转动，使滑杆在弧形滑槽内滑动，从而实现夹持块均匀地夹持飞机吊舱，配合第二电机驱动第二蜗杆蜗轮传动，带动连接环旋转，使电动推杆和静力施压块可绕定位环轴线任意调整角度，结合电动推杆的伸缩功能，能从不同方向对吊舱施加精准的静力载荷，模拟实际飞行中复杂的受力状态，显著提升试验的效率与数据精度。

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Claims

1. An aircraft pod static test loading device, characterized by: It includes a base (1) and an aircraft pod (4). The top of the base (1) is provided with a clamping and fixing assembly (2), and a static test assembly (3) is provided in front of the clamping and fixing assembly (2). The aircraft pod (4) is located inside the clamping and fixing assembly (2) and the static test assembly (3). The static test assembly (3) includes a fixed seat (301) fixedly installed on the top of the base (1). A positioning ring (302) is fixedly connected inside the fixed seat (301). A connecting ring (304) is rotatably connected to the front end of the positioning ring (302). A second worm gear (303) is fixedly fitted on the outside of the connecting ring (304). A fixing block (305) is fixedly connected to the inner wall of the connecting ring (304). An electric push rod (306) is fixedly connected to the inner end of the fixing block (305). A static pressure block (307) is fixedly connected to the transmission end of the electric push rod (306). The inner end of the static pressure block (307) is in contact with the outer wall of the aircraft pod (4).

2. The static test loading device for a nacelle of an aircraft according to claim 1, characterized in that: The inner wall of the fixed base (301) is fixedly connected to a second motor (308), and the transmission end of the second motor (308) is fixedly connected to a second worm (309) that meshes with the second worm wheel (303).

3. The static test loading device for a nacelle of an aircraft according to claim 1, characterized in that: The clamping and fixing assembly (2) includes a fixed base (201), the top of which is fixedly connected to a shell (202), and the inner wall of the shell (202) is rotatably connected to a limiting ring (203), and the inner end of the limiting ring (203) is fitted with a rotating ring (204).

4. The static test loading device for a nacelle of an aircraft according to claim 3, characterized in that: The front end of the rotating ring (204) is fixedly connected to a transmission ring (208), and the front end of the transmission ring (208) is provided with multiple arc-shaped grooves.

5. The aircraft nacelle static test loading device of claim 4, wherein: A fixed ring (209) is provided in front of the transmission ring (208). Multiple fixed posts (210) are fixedly connected to the outer wall of the fixed ring (209) and are equidistant from each other. The end of the fixed post (210) away from the fixed ring (209) is fixedly connected to the inner wall of the outer shell (202).

6. The aircraft nacelle static test loading device of claim 5, wherein: The middle part of the fixed ring (209) is slidably connected to a plurality of sliders (211) that are staggered with the fixed post (210). The inner end of the slider (211) penetrates the inner wall of the fixed ring (209) and is fixedly connected to a clamping block (212). The rear end of the slider (211) is fixedly connected to a slide rod (213) that penetrates the rear end of the fixed ring (209). The end of the slide rod (213) away from the slider (211) extends into the interior of the arc-shaped slide groove. The slide rod (213) is slidably connected to the arc-shaped slide groove.

7. The static test loading device for a nacelle of an aircraft according to claim 4, characterized in that: The rear end of the rotating ring (204) is fixedly connected to the first worm gear (205).

8. The static test loading device for a nacelle of an aircraft according to claim 5, characterized in that: The first motor (206) is fixedly connected inside the outer casing (202), and the transmission end of the first motor (206) is fixedly connected to the first worm (207) that meshes with the first worm wheel (205).