CN113654882B - Experimental loading device of horizontal tail - Google Patents
Experimental loading device of horizontal tail Download PDFInfo
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- CN113654882B CN113654882B CN202110678050.5A CN202110678050A CN113654882B CN 113654882 B CN113654882 B CN 113654882B CN 202110678050 A CN202110678050 A CN 202110678050A CN 113654882 B CN113654882 B CN 113654882B
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- loading
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
Abstract
A horizontal tail test loading device comprises: two lateral load beams; the middle box section is connected between the two lateral loading beams, and a horizontal tail connecting joint is arranged on the rear side of the middle box section; and a screw actuator loading assembly connected to the front side of the middle box section. Wherein, be provided with on every side direction load beam: at least two heading-vertical load points, a plurality of lateral load points, and a plurality of vertical load points. The horizontal tail test loading device can realize loading of various loads of a horizontal tail dummy piece, and is relatively simple in structure, easy to assemble and process and low in production cost.
Description
Technical Field
The invention relates to a structural test device for an aircraft part, in particular to a test loading device for an aircraft horizontal tail wing.
Background
Civil aircrafts, especially civil large aircrafts, need to be tested in the design and manufacture process to verify the performances of static strength, fatigue strength and the like of the aircrafts so as to prove the seaworthiness of the aircrafts. At present, static tests are usually carried out on the aircraft on the ground to detect the influence of load transmission of various parts of the aircraft under different working conditions.
The test loading of the civil aircraft comprises various modes, such as adhesive tape lever system loading, bottom plate two-loading, tension and compression pad loading, joint loading, clamping plate loading, dummy piece loading and the like. In ground tests of civil aircraft, the load loading of many aircraft structures is carried out by using a dummy design, i.e. a dummy of the aircraft component to be tested is designed to simulate the load transfer of the component, including, for example, an engine loading dummy, an Auxiliary Power Unit (APU) loading dummy, etc.
Fig. 1a to 1c show a conventional horizontal tail test loading device 1 for loading a horizontal tail of an aircraft. The horizontal tail test loading device 1 comprises loading points 2 which are arranged at two lateral ends of the horizontal tail test loading device 1, a front joint connecting rod 3 is arranged at the front side of the horizontal tail test loading device 1, and the front joint connecting rod 3 is connected to the front side of the horizontal tail test loading device 1 through a front joint 4 (figure 1 b). The rear side of the horizontal tail test loading unit 1 is provided with rear end fittings 5 (two are shown in fig. 1 c).
With the increase of the requirement on the test loading precision, engineering testers find that the existing horizontal tail test loading device 1 has some problems, so that a need exists for further improvement.
For example, the horizontal tail test loading device 1 has fewer vertical loading points and smaller intervals between the vertical loading points, so that loading of vertical force is difficult to achieve, and the structure is difficult to load large pitching bending moment. For another example, the horizontal rear wing test loading device 1 with the above structure does not have a heading loading point and a lateral loading point, and thus cannot be used for loading the heading load and the lateral load of the horizontal rear wing. In addition, in the conventional horizontal tail test loading device 1, it is not possible to load the yaw moment and the roll moment. The loading of these moments is increasingly important for current tailplane static strength tests.
Accordingly, there is a need for an improved horizontal tail test loading device structure that overcomes the above-mentioned problems with existing horizontal tail test loading devices.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems occurring in the prior art. The invention aims to provide a horizontal tail test loading device with an improved structure, which can be suitable for loading various loads of a horizontal tail. Furthermore, the improvement of the horizontal tail test loading device can lead the horizontal tail test loading device to have simple structure, convenient processing and reduced cost.
The horizontal tail test loading device comprises:
two lateral load beams;
the middle box section is connected between the two lateral loading beams, and the rear side of the middle box section is provided with at least one horizontal tail wing connecting joint; and
the spiral actuator loading assembly is connected to the front side of the middle box section;
wherein, be provided with on each of two side direction load beams: the lateral loading device comprises at least two course-vertical loading points, a plurality of lateral loading points and a plurality of vertical loading points, wherein the at least two course-vertical loading points are respectively positioned at the front end and the rear end of the lateral loading beam, the plurality of lateral loading points are arranged between the two course-vertical loading points, and the plurality of vertical loading points are arranged at the upper side edge and/or the lower side edge of the lateral loading beam.
The horizontal tail test loading device with the structure can realize the loading of various loads of the horizontal tail dummy piece, and has the advantages of relatively simple structure, easy assembly and processing and low production cost.
Preferably, an upper lug is arranged on the upper side edge of the side loading beam, and at least one vertical loading point is formed on the upper lug; and a lower lug is arranged on the lower side edge of the side loading beam, and at least one vertical loading point is formed on the lower lug. The number of vertical load points on the upper and lower tabs may be set as desired.
Preferably, four lateral loading points are included, wherein two of the lateral loading points, in combination, load the horizontal tail, enabling the introduction of roll moment to the horizontal tail, and two of the lateral loading points, in combination, load the horizontal tail, enabling the introduction of yaw moment to the horizontal tail.
Preferably, an upper reinforcing angle bar is arranged at the upper side edge of the lateral loading beam; and/or a lower reinforcing angle bar is arranged at the lower side edge of the side loading beam. Through setting up the angle bar of strengthening, can improve the bending strength of side direction load roof beam. Further, the upper reinforcing angle bar and the lower reinforcing angle bar are connected with the side loading beam through a fastener mounting mode, and compared with a mode of integrally forming the I-shaped beam, the method is low in processing cost and easy to achieve.
Preferably, the lateral load points are attached to the lateral load beam by a plurality of high lock bolts. For example, each lateral load point is attached to the lateral load beam by four high lock bolts.
Specific configurations of the spiral actuator loading assembly may include:
two spiral actuator load beams extending at an angle to each other so as to assume a chevron shape, the spiral actuator load beams being connected to the middle box section at a flared end of the chevron shape;
the spiral actuator connecting joint is connected to one end, where the herringbone converges, of the spiral actuator loading beam; and
the spiral actuator loading connecting rod is connected to the spiral actuator connecting joint.
The spiral actuator loading beam can be an I-beam, so that the spiral actuator loading beam can have higher bending rigidity.
Preferably, the configuration of the screw actuator loading connection rod corresponds to the configuration of the screw actuator interface of the aircraft under test. In this way, the force transmission in the test can be made equivalent to the force transmission in the actual case.
Similarly, the form of the horizontal tail connection joint on the intermediate box section corresponds to the form of the suspension joint of the horizontal tail of the aircraft to be tested. In this way, the force transmission in the test can be made equivalent to the force transmission in the actual case.
Drawings
There is shown in the drawings, which are incorporated herein by reference, non-limiting preferred embodiments of the present invention, the features and advantages of which will be apparent. Wherein:
fig. 1a shows a perspective view of a conventional horizontal tail test loading device.
Fig. 1b shows an enlarged view of section I in fig. 1 a.
Fig. 1c shows an enlarged view of part II of fig. 1 b.
Fig. 2 shows a perspective view of the horizontal tail test loading device of the present invention.
Fig. 3 shows a side view of the horizontal tail test loading unit shown in fig. 2.
Fig. 4 shows a rear view of the horizontal tail test loading unit shown in fig. 2.
Fig. 5 shows a section through the middle box section of the horizontal tail test loading unit shown in fig. 2.
(symbol description)
100 horizontal tail wing test loading device
110 side loading beam
111 upper reinforcing angle bar
112 lower reinforcing angle section
113 first course-vertical load point
114 second heading-vertical load point
115a lateral load point
115b lateral load point
115c lateral load point
115d lateral load point
116a vertical load point
116b vertical load point
116c vertical load point
116d vertical load point
117 lateral load point connection
118 second connecting piece
120 middle box section
121 horizontal tail connecting joint
122 rectangular plate
123 connecting angle bar
130 spiral actuator loading assembly
131 spiral actuator loading beam
132 screw actuator connector
133 spiral actuator loading connecting rod
134 first connecting piece
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It is to be understood that the preferred embodiments of the present invention are shown in the drawings only, and are not to be considered limiting of the scope of the invention. Various obvious modifications, changes and equivalents of the embodiments of the invention shown in the drawings can be made by those skilled in the art, and all of them are within the scope of the invention.
In the following description of the exemplary construction of the present invention, terms such as "upper", "lower", "front", "rear", and the like, with respect to orientation, are used for convenience of description with reference to what is shown in the drawings, and in actual use, the orientation of the device may be changed.
< horizontal rear wing test loading device overall structure >
Fig. 2 shows a perspective view of the horizontal tail test loading device 100 of the present invention. The tailplane test loading unit 100 includes two side loading beams 110, the two side loading beams 110 extending substantially parallel. The side load beam 110 is preferably an i-beam, as will be described in detail below, to provide better bending stiffness.
The middle box section 120 is connected between the two lateral load beams 110 and extends substantially perpendicular to the lateral load beams 110. The rear side of the middle box section 120 is provided with at least one and preferably a plurality of horizontal tail connection joints 121 (two horizontal tail connection joints 121 are shown in the figure). The tailplane attachment joint 121 is used to connect with an attachment joint on a tailplane (not shown) to be tested. Also, the tailplane attachment joints 121 preferably conform to the form of the hanging joints on the tailplane to ensure that the transfer of forces and loads on the tailplane dummy under test is equivalent to that of an actual tailplane.
At the front side of the middle box section 120 is connected a spiral actuator loading assembly 130, and the spiral actuator loading assembly 130 is used to connect a spiral actuator, the specific structure of which will be described in detail below.
Next, specific structures of the respective constituent parts of the horizontal tail test loading device 100 will be described separately.
< side load Beam >
The side load beam 110 of the present invention includes two side load beams 110 arranged substantially in parallel, and the structure of the two side load beams 110 may be the same, so that only the structure of one of the side load beams 110 will be described hereinafter, and the described structure is equally applicable to the other side load beam 110.
Fig. 3 shows a side view of the horizontal tail test loading unit 100. As can be seen from fig. 3, upper and lower reinforcing angle bars 111 and 112 are provided on upper and lower sides of the side load beam 110, respectively. The upper and lower reinforcement angles 111, 112 are secured to the side load beam 110, for example, by a row of fasteners, such as screws. It is noted here that the upper reinforcement angle 111 and the lower reinforcement angle 112 are preferred structures that can improve the bending rigidity of the side load beam 110. However, it is within the scope of the present invention for the side load beam 110 to not include at least one of the upper reinforcement angle 111 and the lower reinforcement angle 112.
The upper and lower reinforcing angles 111, 112 are formed integrally with the side load beam 110 by fasteners. In this way, a single i-beam need not be formed by machining, and thus the machining cost can be reduced while securing the bending rigidity of the side load beam 110.
A first course-vertical load point 113 is provided at the front end of the side load beam 110 and a second course-vertical load point 114 is provided at the rear end thereof.
The side load beam 110 is further provided with a plurality of side load points, for example, as shown in fig. 3, four side load points 115a, 115b, 115c, 115d are provided on the side load beam 110, and the side load points 115a, 115b, 115c, 115d are located between the first heading-vertical load point 113 and the second heading-vertical load point 114. In the particular configuration shown, these lateral load points 115a, 115b, 115c, 115d are located near the second heading-vertical load point 114, i.e., approximately at the rear of the lateral load beam 110. These lateral load points 115a, 115b, 115c, 115d are arranged in a substantially quadrangular shape. Also, these side load points 115a, 115b, 115c, 115d may be fixedly mounted to the side load beam 110 by fasteners.
Fig. 4 shows a rear view of the tailplane test loading unit 100, from which it can be seen that the lateral load points 115a, 115b, 115c, 115d are fixed to the lateral load beam 110 by means of lateral load point connections 117. The side load point connections 117 may be a combination structure including fasteners and mounting holes in the side load beam 110. Preferably, the fasteners used to mount the lateral load points 115a, 115b, 115c, 115d to the lateral load beam 110 are high lock bolts, for example, each lateral load point 115a, 115b, 115c, 115d is attached to the lateral load beam 110 by four high lock bolts.
The side load beam 110 further includes a plurality of vertical load points, which are preferably disposed on at least one of the upper and lower sides of the side load beam 110. In the exemplary configuration shown in fig. 3, the side load beam 110 includes four vertical load points 116a, 116b, 116c, 116d thereon, wherein a lower tab is provided on the underside of the side load beam 110, on which one vertical load point 116a is provided, and an upper tab is provided on the upper side of the side load beam 110, on which three vertical load points 116b, 116c, 116d are provided. Of course, other numbers and/or arrangements of vertical load points may be included, such as two vertical load points on the top side, two vertical load points on the bottom side, or one vertical load point on the top side, two vertical load points on the bottom side, etc.
< intermediate Box section >
As shown in fig. 2, connected between the two side load beams 110 is a middle box section 120. Fig. 5 shows a cross-sectional view of the middle box section 120, from which it can be clearly seen that in a preferred construction of the middle box section 120, four rectangular plates 122 are included, and each two rectangular plates 122 are connected together by a connecting angle 123. The connecting angle 123 has an L-shaped cross section, in which one side of the L-shape is fixed to one rectangular plate 122 by a fastener, such as a row of screws, and the other side of the L-shape is fixed to an adjacent one of the rectangular plates 122 by a fastener, thereby achieving a fixed connection between two adjacent rectangular plates 122.
Returning to fig. 4, the side load beam 110 and the middle box section 120 are connected together by a second connecting strap 118. The second connecting tab 118 is also preferably an L-shaped angle. In the preferred construction shown in the drawings, a second connecting piece 118 is provided on each of the upper and lower front and rear sides of the middle box section 120 to achieve a secure connection between the middle box section 120 and the side load beam 110.
The connection between the lateral load beam 110 and the middle box section 120 can be achieved by fixing both side edges of the L-shape of the second connecting piece 118 to the lateral load beam 110 and the middle box section 120, respectively, by fasteners such as screws. Of course, the connection can also be realized in other ways than a screw-tight connection, for example by welding or the like.
< screw actuator Loading Assembly >
Turning to fig. 2 and 3, the structure of the spiral actuator loading assembly 130 can be clearly seen.
The spiral actuator loading assembly 130 includes two spiral actuator loading beams 131, the two spiral actuator loading beams 131 extending at an acute angle to each other forming an approximate chevron. The spiral actuator load beam 131 is preferably an i-beam to enable better bending stiffness.
A screw actuator connector 132 is provided at the converging end of the screw actuator load beam 131, and a screw actuator load linkage 133 is connected to the screw actuator connector 132. The configuration of the screw actuator loading linkage 133 is preferably consistent with the configuration of the screw actuator of the aircraft being tested, thereby ensuring that the torque transfer during testing is consistent with what is actually being done.
At the flared end of the spiral actuator load beam 131, the spiral actuator load beam 131 is fixedly connected to the middle box section 120 by a first connecting strap 134. A portion of the first connecting piece 134 is fixed to the middle box section 120 by a fixing means such as a screw, a welding, or the like, and another portion of the first connecting piece 134 is fixed to the screw actuator load beam 131 by a fixing means such as a screw, a welding, or the like, so that a fixed connection therebetween is achieved.
Preferably, first attachment tabs 134 are provided on the upper and lower sides of each of the screw actuator load beams 131, respectively, and a row of screws are provided on each of the first attachment tabs 134 to secure the screw actuator load beams 131 to the middle box section 120 on both the upper and lower sides.
< Loading of horizontal Tail test Loading device >
The line clearance description of the preferred embodiment of the horizontal tail test loading device 100 of the present invention has been made above. A method of loading the load of the horizontal rear wing using the horizontal rear wing test loading apparatus 100 will be described in detail below.
In the horizontal rear wing test loading device 100 of the present invention, a plurality of loading points are provided, and by applying these loading points in combination, a plurality of kinds of load loading can be realized. Specifically, the method comprises the following steps:
the horizontal tail wing is loaded by adopting the combination of the first course-vertical load loading point 113, the second course-vertical load loading point 114 and the lateral loading points 115a, 115b, 115c and 115d, the vertical load is loaded, and the introduction of the pitch moment can be realized.
The introduction of the rolling moment can be achieved by loading the side load through the combination of the side load points 115b and 115 d.
By loading the side load through a combination of side load points 115a and 115c, the introduction of yaw moment can be achieved.
Claims (9)
1. A horizontal tail test loading device, comprising:
two lateral load beams;
the middle box section is connected between the two lateral loading beams, and at least one horizontal tail connecting joint is arranged at the rear side of the middle box section; and
a helical actuator loading assembly connected to a front side of the middle box section;
the lateral loading device is characterized in that each of the two lateral loading beams is provided with: the lateral loading device comprises at least two course-vertical load loading points, a plurality of lateral loading points and a plurality of vertical loading points, wherein the at least two course-vertical load loading points are respectively positioned at the front end and the rear end of the lateral loading beam, the plurality of lateral loading points are arranged between the two course-vertical load loading points, and the plurality of vertical loading points are arranged at the upper side edge and/or the lower side edge of the lateral loading beam.
2. The tailplane test loading unit as set forth in claim 1, wherein an upper protruding piece is provided at an upper side edge of the side loading beam, and at least one vertical loading point is formed on the upper protruding piece; and
and a lower convex sheet is arranged at the lower side edge of the side loading beam, and at least one vertical loading point is formed on the lower convex sheet.
3. The tailplane test loading apparatus as set forth in claim 1, comprising four of the side loading points, wherein two of the side loading points, in combination, load a tailplane to enable the introduction of roll torque to the tailplane, and two of the side loading points, in combination, load the tailplane to enable the introduction of yaw torque to the tailplane.
4. The tailplane test loading unit as set forth in claim 1, wherein an upper reinforcing angle is provided at an upper side edge of the side loading beam; and/or
And a lower reinforcing angle bar is arranged at the lower side edge of the lateral loading beam.
5. The tailplane test loading apparatus as set forth in claim 1, wherein the lateral loading points are attached to the lateral loading beam by a plurality of high lock bolts.
6. The tailplane test loading apparatus as set forth in claim 1, wherein the screw actuator loading assembly comprises:
two spiral actuator load beams extending at an angle to each other so as to assume a chevron shape, said spiral actuator load beams being connected at a flared end of said chevron shape to a front side of said middle box section;
a helical actuator connector connected to one end of the helical actuator load beam at the convergence of the chevrons; and
a screw actuator loading connecting rod connected to the screw actuator connection joint.
7. The tailplane test loading unit of claim 6, wherein the screw actuator loading beam is an i-beam.
8. A tailplane test loading apparatus as claimed in claim 6, wherein the screw actuator loading attachment lever is configured in a manner corresponding to the configuration of the screw actuator interface of the aircraft under test.
9. A tailplane test loading apparatus as defined in claim 1, wherein the tailplane attachment joint has a configuration corresponding to a configuration of a suspension joint of a tailplane of an aircraft under test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110678050.5A CN113654882B (en) | 2021-06-18 | 2021-06-18 | Experimental loading device of horizontal tail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110678050.5A CN113654882B (en) | 2021-06-18 | 2021-06-18 | Experimental loading device of horizontal tail |
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| Publication Number | Publication Date |
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| CN113654882A CN113654882A (en) | 2021-11-16 |
| CN113654882B true CN113654882B (en) | 2022-04-26 |
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| CN202110678050.5A Active CN113654882B (en) | 2021-06-18 | 2021-06-18 | Experimental loading device of horizontal tail |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113955080B (en) * | 2021-11-29 | 2023-10-20 | 中国商用飞机有限责任公司 | Trimming type horizontal tail connecting structure |
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