CN111717412A - Flexible missile wing skin deformation load testing device - Google Patents
Flexible missile wing skin deformation load testing device Download PDFInfo
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- CN111717412A CN111717412A CN202010552629.2A CN202010552629A CN111717412A CN 111717412 A CN111717412 A CN 111717412A CN 202010552629 A CN202010552629 A CN 202010552629A CN 111717412 A CN111717412 A CN 111717412A
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- connecting rod
- angle
- base
- wing skin
- missile wing
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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
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- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A flexible missile wing skin deformation load testing device is characterized in that an upper base, a lower base, an upper connecting rod and a lower connecting rod form a four-bar mechanism, a loading hole for loading a load is formed in the top of the upper base, a loading hole for loading the load is formed in the bottom of the lower base, an angle scale mark is arranged on the front end face of the upper base on the left side of the four-bar mechanism, an angle pointer is arranged at the upper end of the front end face of the lower base on the right side of the four-bar mechanism, the initial position of the angle pointer and a 0-degree scribed line are positioned on the same horizontal line, and a test piece is installed on the rear end faces of the upper; the flexible missile wing skin measuring device is simple in structure and easy to assemble, effectively solves the problem of measuring the load required by driving the flexible missile wing skin to change a certain sweepback angle, is provided with angle scale lines, and is convenient to read.
Description
Technical Field
The invention relates to the technical field of load testing, in particular to a flexible missile wing skin deformation load testing device.
Background
With the rapid development of the advanced technology of aircrafts in all countries of the world, the fixed layout of the traditional aircraft cannot meet the requirement of executing multiple tasks in the real battlefield environment. The variable-profile aircraft can timely adjust the aerodynamic configuration according to the change of external environments (such as height, speed, air resistance and the like) and the difference of flight tasks, and improves the flight performance of each task segment. The variable missile wing appearance technology meets the requirement of a combat mission of a scouting and fighting integrated aircraft by changing the wingspan and the sweepback angle of the missile wing, so that the aircraft can quickly reach a designated airspace and the air flight inspection time is prolonged.
The variable-appearance missile wing can be divided into an inner section wing and an outer section wing, the inner section wing and the fuselage and the outer section wing and the inner section wing are connected through hinges, the outer missile wing is made of flexible seamless skin, the inner part of the missile wing is actuated through a driver and used for partially or completely opening the wing, and the driver is required to provide certain driving load in order to unfold the missile wing to a certain angle. Therefore, a special load testing device is required to determine the magnitude of the driving load in the design stage to properly select the driver.
Disclosure of Invention
The invention aims to provide a flexible missile wing skin deformation load testing device to solve the problems in the background art.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a flexible missile wing skin deformation load testing device comprises an upper base, a lower base, an upper connecting rod, a lower connecting rod and a test piece, wherein the upper base, the lower base, the upper connecting rod and the lower connecting rod form a four-bar mechanism, a loading hole for loading a load is formed in the top of the upper base, a loading hole for loading the load is formed in the bottom of the lower base, an angle scale mark is formed in the front end face of the upper base on the left side of the four-bar mechanism, an angle pointer is arranged on the front end face of the lower base on the right side of the four-bar mechanism, the initial position of the angle pointer and a 0-degree scale mark are located on the same horizontal line, and the test piece is installed on the rear end faces of the upper;
during testing, the upper base is fixed, a load is applied to the lower base, and a test piece deflects, so that a test piece deflection angle is formed between the upper connecting rod and the upper base provided with the loading hole, the test piece deflection angle is equal to a connecting rod deflection angle formed between the upper connecting rod and the angle pointer, and the length of the angle pointer and the test piece deflection angle are known, and the length of a right-angle side corresponding to the connecting rod deflection angle is calculated by a sine formula, so that the required driving load size can be quickly known when the test piece deflects by a certain sweepback angle.
In the invention, the upper base is composed of two connecting plates which are vertical to each other, one connecting plate is provided with a cylindrical section, the cylindrical section is provided with a loading hole, and the other connecting plate is provided with a through hole for connecting the upper connecting rod and the lower connecting rod through inserting a connecting shaft and a groove for inserting the upper connecting rod and the lower connecting rod.
In the invention, the lower base is composed of two connecting plates which are vertical to each other, one connecting plate is provided with a cylindrical section, the cylindrical section is provided with a loading hole, and the other connecting plate is provided with a through hole for connecting the upper connecting rod and the lower connecting rod through inserting a connecting shaft and a groove for inserting the upper connecting rod and the lower connecting rod.
In the invention, the angle pointer is arranged on the connecting shaft at the upper end of the connecting plate provided with the through hole, and the pointer line of the angle pointer passes through the axis of the connecting shaft for mounting the angle pointer.
In the invention, the rear end faces of the upper base and the lower base are respectively provided with 3 threaded holes, and the test pieces are respectively fixed in the threaded holes of the upper base and the lower base by the pressing plate through fasteners.
In the invention, the upper connecting rod and the lower connecting rod have the same structure, and two ends of the upper connecting rod are respectively provided with a mounting hole for inserting the connecting shaft.
Has the advantages that: the flexible missile wing skin measuring device is simple in structure and easy to assemble, effectively solves the problem of measuring the load required by driving the flexible missile wing skin to change a certain sweepback angle, is provided with angle scale lines, and is convenient to read.
Drawings
Fig. 1 is a front view of a preferred embodiment of the present invention.
Fig. 2 is a rear view of the preferred embodiment of the present invention.
FIGS. 3-4 are schematic views of the upper base structure in the preferred embodiment of the invention.
FIG. 5 is a schematic view of the upper link structure in the preferred embodiment of the present invention.
FIG. 6 is a schematic diagram of the preferred embodiment of the present invention.
FIG. 7 is a schematic view of test piece deflection in a preferred embodiment of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Referring to fig. 1-5, a flexible missile wing skin deformation load testing device comprises an upper base 1, a lower base 2, an upper connecting rod 3, a lower connecting rod 4, an angle pointer 5, a connecting shaft 6, a pressing plate 7, a test piece 8 and a fastener 9, wherein the upper base 1 consists of two mutually perpendicular connecting plates, one connecting plate is provided with a cylindrical section, the cylindrical section is provided with a loading hole, the other connecting plate is provided with a through hole for connecting one end of the upper connecting rod 3 and the lower connecting rod 4 through inserting the connecting shaft 6 and a groove for inserting one end of the upper connecting rod 3 and one end of the lower connecting rod 4, and meanwhile, the front end face of the connecting plate provided with the through hole is provided with an angle scale mark; the lower base 2 is composed of two connecting plates which are vertical to each other, one connecting plate is provided with a cylindrical section, the cylindrical section is provided with a loading hole, the other connecting plate is provided with a through hole which is used for connecting the other ends of the upper connecting rod 3 and the lower connecting rod 4 through an inserted connecting shaft 6 and a groove which is used for inserting the other ends of the upper connecting rod 3 and the lower connecting rod 4, the angle pointer 5 is arranged on the connecting shaft 6 at the upper end of the connecting plate provided with the through hole and moves along with the lower base 2, and meanwhile, a pointer line of the angle pointer 5 passes through the axis of the connecting shaft 6 for installing the angle pointer 5; the four connecting shafts 6 are connected with the upper connecting rod 3, the lower connecting rod 4, the upper base 1 and the lower base 2 to form a four-bar linkage;
the rear end face homonymy of going up base 1 and going down base 2 is equipped with 3 screw holes respectively, and clamp plate 7 is fixed in the screw hole of going up base 1 and going down base 2 respectively with test piece 8 through fastener 9.
In the present embodiment, the upper link 3 has the same structure as the lower link 4, and both ends of the upper link 3 are respectively provided with a mounting hole for inserting the connecting shaft 6.
In the present embodiment, the initial position of the angle indicator 5 is in the same horizontal line as the 0 ° line.
The working principle is as follows: as can be seen from fig. 6 and 7, at the beginning of the test, the angle pointer 5 points to the 0 ° line and is flush with the 0 ° line, and the quadrilateral OACO' is always a parallelogram; when the test piece 8 deflects to generate a test piece deflection angle alpha, as shown in fig. 6, angle alpha = [ OAB ], while OAB is constant as right triangle, OAB is a connecting rod deflection angle, and then
sinα=
（1）
It is obtained that,
OB=OA×sinα
the OA length is known, so the length value of OB can be calculated after the angle alpha value is given, the size of OB can be obtained according to different angle values, and the scribing and the angle recording are made on the upper base 1.
The test process comprises the following steps: during the test, the upper base 1 is fixed, the load is applied to the lower base 2, and the required driving load when the skin deflects by a certain sweepback angle can be quickly known by observing the direction of the angle pointer 5.
Claims (9)
1. A flexible missile wing skin deformation load testing device comprises an upper base, a lower base, an upper connecting rod, a lower connecting rod and a test piece, and is characterized in that the upper base, the lower base, the upper connecting rod and the lower connecting rod form a four-bar mechanism, a loading hole for loading a load is formed in the top of the upper base, the bottom of the lower base is provided with the loading hole for loading the load, an angle scale mark is formed in the front end face of the upper base on the left side of the four-bar mechanism, an angle pointer is arranged at the upper end of the front end face of the lower base on the right side of the four-bar mechanism, the initial position of the angle pointer and the 0-degree scale mark are in the same horizontal line, and the test piece is installed on the rear;
during testing, the upper base is fixed, a load is applied to the lower base, and a test piece deflects, so that a test piece deflection angle is formed between the upper connecting rod and the upper base provided with the loading hole, the test piece deflection angle is equal to a connecting rod deflection angle formed between the upper connecting rod and the angle pointer, and the length of the angle pointer and the test piece deflection angle are known, and the length of a right-angle side corresponding to the connecting rod deflection angle is calculated by a sine formula, so that the required driving load size can be quickly known when the test piece deflects by a certain sweepback angle.
2. The flexible missile wing skin deformation load testing device of claim 1, wherein the upper base is composed of two connecting plates which are perpendicular to each other.
3. The flexible missile wing skin deformation load testing device as claimed in claim 2, wherein one of the connecting plates is provided with a cylindrical section, the cylindrical section is provided with a loading hole, and the other connecting plate is provided with a through hole for connecting the upper connecting rod and the lower connecting rod through an inserted connecting shaft and a groove for inserting the upper connecting rod and the lower connecting rod.
4. The flexible missile wing skin deformation load testing device of claim 1, wherein the lower base is composed of two connecting plates which are perpendicular to each other.
5. The flexible missile wing skin deformation load testing device as claimed in claim 4, wherein one of the connecting plates is provided with a cylindrical section, the cylindrical section is provided with a loading hole, and the other connecting plate is provided with a through hole for connecting the upper connecting rod and the lower connecting rod through an inserted connecting shaft and a groove for inserting the upper connecting rod and the lower connecting rod.
6. The flexible missile wing skin deformation load testing device of claim 5, wherein the angle indicator is installed on a connecting shaft at the upper end of the connecting plate provided with the through hole, and an indicator line of the angle indicator passes through the axis of the connecting shaft for installing the angle indicator.
7. The flexible missile wing skin deformation load testing device of claim 1, wherein the rear end surfaces of the upper base and the lower base are respectively provided with 3 threaded holes.
8. The flexible missile wing skin deformation load testing device of claim 1, wherein the upper connecting rod and the lower connecting rod are of the same structure.
9. The flexible missile wing skin deformation load testing device as recited in claim 8, wherein the two ends of the upper connecting rod are respectively provided with a mounting hole for inserting the connecting shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010552629.2A CN111717412B (en) | 2020-06-17 | 2020-06-17 | Flexible missile wing skin deformation load testing device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010552629.2A CN111717412B (en) | 2020-06-17 | 2020-06-17 | Flexible missile wing skin deformation load testing device |
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| Publication Number | Publication Date |
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| CN111717412A true CN111717412A (en) | 2020-09-29 |
| CN111717412B CN111717412B (en) | 2022-05-06 |
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| CN202010552629.2A Active CN111717412B (en) | 2020-06-17 | 2020-06-17 | Flexible missile wing skin deformation load testing device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113602524A (en) * | 2021-08-11 | 2021-11-05 | 北京航空航天大学 | Test platform for performance of flexible skin of trailing edge variable camber wing |
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| GB639596A (en) * | 1948-02-16 | 1950-06-28 | Short Brothers & Harland Ltd | Improvements in aeroplanes having swept-back wings |
| GB664058A (en) * | 1949-03-11 | 1951-01-02 | Leslie Everett Baynes | Improvements in high-speed aircraft |
| US3510088A (en) * | 1967-02-06 | 1970-05-05 | British Aircraft Corp Ltd | Variable-geometry aircraft |
| US5181678A (en) * | 1991-02-04 | 1993-01-26 | Flex Foil Technology, Inc. | Flexible tailored elastic airfoil section |
| US20060145029A1 (en) * | 2003-06-07 | 2006-07-06 | Hans Lonsinger | Wing, especially a carrier wing of an aeroplane, having an adaptable profile |
| CN202783799U (en) * | 2012-07-13 | 2013-03-13 | 哈尔滨飞机工业集团有限责任公司 | Combined spar and leading edge loading device |
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2020
- 2020-06-17 CN CN202010552629.2A patent/CN111717412B/en active Active
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|---|---|---|---|---|
| GB639596A (en) * | 1948-02-16 | 1950-06-28 | Short Brothers & Harland Ltd | Improvements in aeroplanes having swept-back wings |
| GB664058A (en) * | 1949-03-11 | 1951-01-02 | Leslie Everett Baynes | Improvements in high-speed aircraft |
| US3510088A (en) * | 1967-02-06 | 1970-05-05 | British Aircraft Corp Ltd | Variable-geometry aircraft |
| US5181678A (en) * | 1991-02-04 | 1993-01-26 | Flex Foil Technology, Inc. | Flexible tailored elastic airfoil section |
| US20060145029A1 (en) * | 2003-06-07 | 2006-07-06 | Hans Lonsinger | Wing, especially a carrier wing of an aeroplane, having an adaptable profile |
| CN202783799U (en) * | 2012-07-13 | 2013-03-13 | 哈尔滨飞机工业集团有限责任公司 | Combined spar and leading edge loading device |
| CN110753612A (en) * | 2017-06-09 | 2020-02-04 | 世联股份有限公司 | Composite material for vehicle interior decoration |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113602524A (en) * | 2021-08-11 | 2021-11-05 | 北京航空航天大学 | Test platform for performance of flexible skin of trailing edge variable camber wing |
| CN113602524B (en) * | 2021-08-11 | 2024-01-30 | 北京航空航天大学 | Test platform for flexible skin performance of trailing edge camber wing |
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| CN111717412B (en) | 2022-05-06 |
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