CN211927520U

CN211927520U - Aircraft skin transverse butt joint fatigue test fixture

Info

Publication number: CN211927520U
Application number: CN201922388229.8U
Authority: CN
Inventors: 彭航; 张彦军; 王�锋; 严红
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2019-12-26
Filing date: 2019-12-26
Publication date: 2020-11-13
Anticipated expiration: 2029-12-26

Abstract

The utility model provides an aircraft skin transverse butt joint seam fatigue test anchor clamps, aircraft skin test piece contain two butt joint skins, have a lap joint plate in one side of butt joint seam, the butt joint of aircraft skin test piece and lap joint plate are skin overlap joint district, the lap joint plate both ends outside is skin transition district, test anchor clamps contain four vertical grip blocks and a plurality of transverse pressing plate, be equipped with corresponding connect the through-hole on vertical grip block with transverse pressing plate's both sides, test anchor clamps adopt upper, middle, lower symmetry syllogic transverse pressing plate, retrain spacing with the overlap joint district both sides and the skin transition district both sides of aircraft skin test piece respectively, the vertical grip block of reuse both sides is fixed with the transverse pressing plate centre gripping.

Description

Aircraft skin transverse butt joint fatigue test fixture

Technical Field

The utility model belongs to an aircraft structural strength test field relates to a design of aircraft skin transverse butt joint fatigue test spare anchor clamps.

Background

In an aircraft structural strength test, the fatigue performance of the circumferential butt joint of a fuselage skin needs to be examined and verified, wherein the key core is 2 points: 1. the problem of how to reduce because the additional moment of flexure that skin butt joint testpieces produced because asymmetry in the testing process is solved, guarantee that the testpieces atress accords with actual conditions. 2. The problem of the too big clamp force of anchor clamps to the load distribution's of testpieces influence is solved, guarantee that the distribution of load in the testpieces accords with reality.

Fuselage skin hoop is to seam test piece anchor clamps of prior art often only retrains the more obvious middle part of bending, lacks the restraint at test piece both ends, and does not carry out effective restraint in the thickness transition department at test piece both ends, and the effect of preventing bending is not obvious, still exists directly to pass through the clamp force centre gripping with anchor clamps on the test piece, has changed the load distribution of test piece. Therefore how to design a fuselage skin hoop is to seam test spare anchor clamps, can reduce the additional moment of flexure that produces because asymmetry for the test spare atress accords with actual conditions, simultaneously, reduces the clamp force of anchor clamps, makes the distribution of load in the test spare accord with reality, is the key place of solving this problem.

Disclosure of Invention

For the problem that solves prior art existence, the aim at of this application provides a horizontal butt joint fatigue test spare anchor clamps of aircraft skin.

The utility model provides an aircraft skin horizontal butt joint seam fatigue test anchor clamps, aircraft skin test piece contain two butt joint skins, have a lap joint board in one side of butt joint seam, the butt joint of aircraft skin test piece and lap joint board are the skin overlap joint district, the lap joint board both ends outside is skin transition district, a serial communication port, test anchor clamps contain four vertical grip blocks and a plurality of horizontal clamp plate, be equipped with corresponding connect the through-hole on vertical grip block and the both sides of horizontal clamp plate, test anchor clamps adopt upper, middle and lower symmetry syllogic horizontal clamp plate, retrain spacing with the overlap joint district both sides and the skin transition district both sides of aircraft skin test piece respectively, the vertical grip block centre gripping of reuse both sides is fixed with the horizontal clamp plate centre gripping.

The beneficial effect of this application lies in: through the overlap joint district and the transition zone of sectional type horizontal restraint test piece, avoided preventing that the bending effect is not good and the redistribution of load in the test piece causes the inconsistent problem of test piece atress and actual conditions.

The present application is described in further detail below with reference to the accompanying drawings of embodiments.

Drawings

FIG. 1 is a schematic structural view of an aircraft skin trial.

FIG. 2 is a structural schematic diagram of a clamp of a transverse butt-joint fatigue test piece of an aircraft skin.

Fig. 3 is a schematic view of an intermediate platen structure.

FIG. 4 is a schematic view of a longitudinal clamping plate structure.

Fig. 5 is a schematic view of a transition platen configuration.

FIG. 6 is a schematic view of a transition platen configuration with a depressed step.

FIG. 7 is a schematic diagram of the use state of the clamp of the aircraft skin transverse butt joint fatigue test piece.

The numbering in the figures illustrates: 1 first skin, 2 second skins, 3 pairs of seams, 4 lap plates, 5 longitudinal clamping plates, 6 transition pressing plates, 7 middle pressing plates, 8 observation holes and 9 sunken steps.

Detailed Description

Referring to the drawings, the aircraft skin test piece designed in the application is shown in fig. 1, the aircraft skin test piece comprises two butt joint skins, a first skin 1 and a second skin 2, a butt joint 3 of the first skin 1 and the second skin 2, and a lap plate 4 arranged on one side of the butt joint 3 and fixedly connecting the first skin 1 and the second skin 2 to form an integral structural member, the coverage area of the lap plate in the middle of the test piece is a lap joint area, the two ends of the test piece are test clamping areas, and the outer sides of the two ends of the lap plate are skin transition areas. In order to do the butt joint fatigue test to this overall structure spare, this application provides a horizontal butt joint fatigue test anchor clamps of aircraft skin, this test anchor clamps are shown as figure 2, contain four vertical grip blocks 5 and a plurality of horizontal clamp plate, be equipped with corresponding connect the through-hole on vertical grip block 5 and the both sides of horizontal clamp plate, the test anchor clamps adopt upper, middle, lower symmetry syllogic horizontal clamp plate, retrain spacing with the overlap joint district both sides and the skin transition district both sides of aircraft skin test spare respectively, the horizontal clamp plate centre gripping of reuse both sides is fixed.

The transverse pressing plate comprises a middle pressing plate 7 at the upper side and the lower side of the constraint overlapping area and transition pressing plates 6 at the upper side and the lower side of the transition areas at the two ends, the thickness of the transition pressing plates 6 is larger than that of the middle pressing plate 7, and the thickness difference corresponds to that of the overlapping plate 4.

In order to observe the state of the test piece conveniently, the transverse pressing plates are arranged in a segmented mode, and meanwhile, an observation hole 8 is formed in the middle pressing plate 7.

The transverse side of the transition pressboard 6 on the side of the bridging board 4 is provided with a sunken step 9, as shown in fig. 6, the height of which corresponds to the thickness of the bridging board 4, so that the transition pressboard 6 can better restrain the transition zone of the test piece.

The using state of the clamp for the aircraft skin transverse butt joint fatigue test piece is shown in fig. 7, a transverse pressing plate of the clamp is attached to the test piece by adopting an up-down symmetrical three-section layout, and the transverse pressing plate is arranged at a middle part which is easy to generate eccentricity and a skin part of a transition area of the test piece respectively to restrain the normal displacement of the test piece;

during clamping, each transverse pressing plate is connected with the clamping plate through a fastening piece, so that a smaller clamping force is applied between the clamp and the test piece, and the clamp is hung on the testing machine through a rope, so that the influence of the clamp on experimental data is reduced.

Claims

1. The utility model provides a horizontal butt joint seam fatigue test anchor clamps of aircraft skin, test fixture restraint on aircraft skin test piece, aircraft skin test piece contain two butt joint skins, there is a lap joint board in one side of butt joint seam, the butt joint seam and the lap joint board of aircraft skin test piece are the skin overlap joint district, the lap joint board both ends outside is the skin transition district, its characterized in that, test fixture contain four vertical grip blocks and a plurality of horizontal clamp plate, be equipped with corresponding connect the through-hole on vertical grip block with the both sides of horizontal clamp plate, test fixture adopts upper, middle, lower symmetry syllogic horizontal clamp plate, retrains spacingly with the overlap joint district both sides and the skin transition district both sides of aircraft skin test piece respectively, the vertical grip block of reuse both sides will transversely clamp the clamp plate centre gripping fixed.

2. The aircraft skin transverse butt seam fatigue test fixture of claim 1, wherein the transverse press plates comprise intermediate press plates for constraining the upper and lower sides of the lap joint region and transition press plates for constraining the upper and lower sides of the transition regions at the two ends, the thickness of the transition press plates is greater than that of the intermediate press plates, and the thickness difference corresponds to the thickness of the lap joint region.

3. The aircraft skin transverse butt seam fatigue test fixture of claim 2, wherein the transverse side edge of the transition pressure plate on one side of the lap plate is provided with a depressed step having a height corresponding to the thickness of the lap plate.

4. The aircraft skin transverse butt seam fatigue test fixture of claim 1, wherein a sight hole is provided in the intermediate platen.