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Method for supporting static test for light-aircraft fore fuselages

A static test and light aircraft technology, applied in the direction of aircraft component testing, machine/structural component testing, measuring devices, etc., can solve problems such as high cost, complicated operation, and large impact on test results, and achieve low cost and simple operation , the effect of shortening the test cycle

Active Publication Date: 2010-07-28
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0004] The purpose of the present invention is: in order to solve the problems that the prior art light aircraft static strength test support method has great influence on test results, complicated operation and high cost, the present invention provides a method that has little influence on test results, simple operation and low cost. Lower Light Aircraft Forward Fuselage Static Test Support Methods

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  • Method for supporting static test for light-aircraft fore fuselages
  • Method for supporting static test for light-aircraft fore fuselages
  • Method for supporting static test for light-aircraft fore fuselages

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Embodiment Construction

[0015] Below by specific embodiment the present invention is described in further detail:

[0016] Please also see figure 1 and figure 2 ,in figure 1 It is a schematic diagram of the aircraft support method involved in the light aircraft front fuselage static strength test support method of the present invention, figure 2 yes figure 1 A-A cutaway view. In this embodiment, the light aircraft is the Kitty Hawk-500, and its own structure has few vertical load-bearing parts and its rigidity is relatively weak. Therefore, when carrying out the static strength test to its front fuselage, the present invention is provided with two hoops 3 at the straight frame 4 of the rear fuselage of the aircraft, wherein, a hoop 3 is arranged on the rear between the wing and the flat tail of the aircraft. There are 4 places on the straight frame of the fuselage, and the clamp 3 is arranged as far away from the wing structure as possible under the premise of being able to bear the load of th...

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Abstract

The invention relates to an aircraft supporting-fixing method in static strength test, in particular to an aircraft-supporting method in static strength test for fore fuselages. The method for supporting static test for light-aircraft fore fuselages comprises that: a straight frame of an aircraft rear fuselage is provided with two clamp hoops; the clamp hoops and the fuselage are tightly clamped; each clamp hoop is connected with two upright columns arranged on two sides of the fuselage; the width of a clamp-hoop edge strip is not greater than that of a fuselage edge strip where the clamp-hoop edge strip is arranged; one clamp hoop is arranged on the fuselage straight frame between aircraft wings and an aircraft horizontal tail, and the other clamp hoop is arranged at the aircraft tail end after the aircraft horizontal tail is detached; a longitudinal part is arranged on the fuselage between the two clamp hoops; and the longitudinal part is a long truss on the fuselage. The method for supporting static test for light-aircraft fore fuselages has the advantage of effectively solving the problem of supporting the whole fore fuselage of a light aircraft in static strength test, along with simple operation, little influence on test results, high precision, low cost and great practical application value.

Description

technical field [0001] The invention relates to a method for supporting and fixing an aircraft during a static strength test, in particular to an aircraft supporting method during a static strength test of a front fuselage. Background technique [0002] Aircraft static strength test, also known as static force test, mainly tests the structural performance of the aircraft, and is an important part of aircraft finalization. When the static strength test of the aircraft is carried out, the aircraft needs to be fixed and supported, especially the support position of the aircraft should be as far away from the static strength test area as possible to ensure the test accuracy. In conventional aircraft static strength tests, a three-point support method for the landing gear is adopted. For light aircraft, due to the small load of the aircraft, the three-point support method of the conventional landing gear has a great influence on the strength test of the front fuselage, and the t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M19/00G01M99/00B64F5/60
Inventor 张兆斌惠红军单群
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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