A lightweight loading device and its design method for low-altitude propeller balances

By designing a lightweight loading device suitable for low-altitude propeller balances, the problem that existing devices cannot meet the requirements of high rigidity and lightweight calibration is solved, achieving high-precision testing results and meeting the calibration needs of low-altitude propeller balances.

CN122084231AActive Publication Date: 2026-05-26CHINA AVIATION IND CORP HARBIN AERODYNAMICS RESEARCH INSTITUTE
View PDF 9 Cites 0 Cited by

Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CHINA AVIATION IND CORP HARBIN AERODYNAMICS RESEARCH INSTITUTE
Filing Date
2026-04-24
Publication Date
2026-05-26

AI Technical Summary

Technical Problem

Existing wind tunnel balance loading devices cannot meet the requirements of low-altitude propeller balances for simulating real installation methods, high rigidity, and lightweight calibration, especially for propeller balances with a diameter of less than 200mm.

Method used

A lightweight loading device suitable for low-altitude propeller balances was designed, including components such as a lifting base, a lower connector of the balance, a central body, a drag lug, and a rolling moment lifting ring. The strength and stiffness were checked using finite element analysis software to ensure the high stiffness and lightweight characteristics of the loading device, and the actual installation method was simulated.

Benefits of technology

The loading device achieves high rigidity, lightweight, accurate positioning, and precise dimensions, improving test accuracy and enabling static calibration of propeller balances with diameters below 200mm, thus enhancing the applicability and reliability of the test.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure CN122084231A_ABST
    Figure CN122084231A_ABST
Patent Text Reader

Abstract

This invention proposes a lightweight loading device and its design method suitable for low-altitude propeller balances, belonging to the technical field of low-altitude aircraft test balances. The aim is to solve the problem that existing loading devices cannot meet the requirements of low-altitude propeller six-component balances with diameters less than 200mm for simulating real-world installation methods, high rigidity, and lightweight calibration. In this invention, the low-altitude propeller balance is horizontally mounted on a raised base via a lower balance connector, and the upper surface of the low-altitude propeller balance is connected to the upper balance connecting plate. The central body is mounted on the outside of the low-altitude propeller balance; the front and rear, and left and right cantilever arms are all mounted on the central body; drag lugs are installed on both sides of the left and right cantilever arms, and normal force and roll moment lugs are installed on the left and right cantilever arms; pitch moment lugs are installed on the front and rear cantilever arms. This invention solves the problem that existing loading devices cannot meet the requirements of low-altitude propeller six-component balances with diameters less than 200mm for simulating real-world installation methods, high rigidity, and lightweight calibration.
Need to check novelty before this filing date? Find Prior Art

Citation Information

Patent Citations

  • In-situ loading calibration device for five-component force measuring balance of pneumatic test of helicopter rotor

    CN108896271A

  • Balance system and method for accurately measuring aerodynamic load of rotor wing

    CN111175014A

  • Wind tunnel balance loading method

    CN113049213A

  • Combined loading field checking device and method for rotor wing balance-mounted test bed

    CN113173261A

  • Balance loading verification device and method

    CN115839818A