CN210036499U

CN210036499U - Measure aircraft step device

Info

Publication number: CN210036499U
Application number: CN201920861183.4U
Authority: CN
Inventors: 陈�胜; 余泽民; 朱卫; 李瑞朋; 胡静文; 袁春健
Original assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Current assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Priority date: 2019-06-10
Filing date: 2019-06-10
Publication date: 2020-02-07
Anticipated expiration: 2029-06-10

Abstract

The utility model discloses a measure aircraft jump device belongs to aircraft assembly technical field, for the flexibility limited, the precision is not high enough, the human error is big, the test equipment structure is complicated or too crude scheduling problem design of solving current measurement aircraft jump device. The device for measuring the aircraft step difference is used for measuring the coincidence step value of the head of the movable surface of the aircraft and the rear edge of the fixed wing, and comprises a clamping plate and a movable assembly, wherein the clamping plate is provided with a first working surface and a second working surface, the first working surface is suitable for stopping the rear edge of the fixed wing, the second working surface is positioned above the first working surface, the movable assembly is movably arranged on the clamping plate, and the movable assembly is suitable for stopping the head of the movable surface. The device has the advantages of convenient use, high measurement precision, simple structure, strong practicability and capability of quickly and accurately measuring the step value.

Description

Measure aircraft step device

Technical Field

The utility model relates to an aircraft assembly technical field especially relates to a measure aircraft jump device.

Background

After the aircraft is assembled with the movable surface (ailerons, spoilers, elevators and rudders), in order to ensure the overall aerodynamic shape, flight performance and assembly quality of the aircraft, the measurement of the step of the inosculation between the head of the movable surface of the aircraft and the rear edge of the fixed wing must be carried out. The coincidence step difference between the head of the movable surface of the airplane and the trailing edge of the fixed wing refers to the coincidence degree between the movable surface and the appearance of the adjacent airfoil surface when the movable surface is at a zero position. At present, the jump measurement of the airplane mostly adopts a digital measurement technology, and a laser measurement technology, such as a laser tracker and a three-coordinate measuring machine, is mostly applied. Although the measurement precision is high, the measurement range is wide, the three-dimensional coordinates of the target ball point can only be measured, the equipment is large, the measurement flexibility is limited, and the measurement cannot be carried out when the laser cannot be directly projected when the target is shielded. Therefore, the digital measurement is more applied to the assembly process between large components and fixed components such as fuselage butt joint and wing body butt joint. In the installation process of the rotating movable surface, the practicability of digital measurement is not strong, and the measurement of the step difference is still a method of manual measurement. For example: the measurement method of a certain branch airplane is the human eye observation carried out by using two pen rulers: one vertical movable surface is pressed on the fixed wing, the other vertical movable surface is erected on the movable surface, and the human eyes can directly read the number. However, this measurement method is too simple and crude, has large human error and is not high enough in precision. In conclusion, the prior art has the technical problems of limited flexibility, insufficient precision, large human error, complex or too simple and crude test equipment structure and the like.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a measure aircraft jump device, the purpose of the invention is in order to overcome the not enough on the traditional anastomotic jump measuring method, design one kind can convenient to use, precision height, simple structure, practicality strong measure aircraft jump device.

To achieve the purpose, the utility model adopts the following technical proposal:

the airplane jump measuring device is used for measuring the fit jump value of the head of a movable surface of an airplane and the trailing edge of a fixed wing, the head of the movable surface is connected with the trailing edge of the fixed wing, the airplane jump measuring device comprises a clamping plate and a movable assembly, the clamping plate is provided with a first working surface and a second working surface, the first working surface is suitable for abutting against the trailing edge of the fixed wing, and the second working surface is positioned above the first working surface; the movable assembly is movably arranged on the clamping plate and is suitable for being stopped against the head of the movable surface.

Optionally, the movable assembly comprises a movable member and a handle, the movable member is movably arranged on the clamping plate, and the lower end of the movable member is suitable for abutting against the head of the movable surface; the handle is connected with the movable piece in interference fit.

Optionally, the clamping plate comprises a first protruding part and a flat part, the first protruding part is connected with the flat part, the bottom surface of the first protruding part is formed into the first working surface, and the bottom surface of the flat part is formed into the second working surface.

Optionally, the moving part is a bolt, the moving part is provided with an external thread, the clamping plate further comprises a second protruding portion, and the second protruding portion is provided with an internal thread matched with the moving part.

Optionally, the number of the second protrusions is two, and the two second protrusions are symmetrically distributed around a center line of the card board.

Optionally, the first working surface and the second working surface are both smooth surfaces.

Optionally, the step difference between the first working surface and the second working surface is 5 ± 0.05 mm.

Optionally, the number of the movable assemblies is two, and the two movable assemblies are symmetrically distributed around the center line of the clamping plate.

Optionally, the handle is threadedly connected to the moveable member.

Optionally, the height of the movable member is greater than the height of the first protrusion.

Compared with the prior art, the application has the following technical effects: the airplane step difference measuring device enables the first working surface to be abutted against the rear edge of the fixed wing, the movable component is screwed to just abut against the head of the movable surface of the airplane, and the fit step difference value of the head of the movable surface of the airplane and the rear edge of the fixed wing is calculated by measuring the gap between the movable surface of the airplane and the second working surface. The device has the advantages of convenient use, high measurement precision, simple structure, strong practicability and capability of quickly and accurately measuring the step value.

Drawings

Fig. 1 is a schematic structural diagram of an aircraft step difference measuring device according to an embodiment of the present invention;

fig. 2 is a front view of the device for measuring aircraft step difference according to the embodiment of the present invention in an unmeasured state;

fig. 3 is a front view of the device for measuring aircraft step difference according to the embodiment of the present invention.

Reference numerals:

1-catch plate, 11-first projection, 12-flat part, 13-second projection, 2-movable component, 21-movable part, 22-handle, S1-first working surface, S2-second working surface.

Detailed Description

In order to make the technical problem solved by the present invention, the technical solution adopted by the present invention and the technical effect achieved by the present invention clearer, the technical solution of the present invention will be further explained by combining the drawings and by means of the specific implementation manner.

The following describes a specific structure of an aircraft step measurement device according to an embodiment of the present invention with reference to fig. 1 to 3.

As shown in fig. 1, the utility model discloses a measure aircraft jump number device is used for measuring the anastomotic jump number value of aircraft activity face head and stationary vane trailing edge, and the activity face head is connected with the stationary vane trailing edge, measures aircraft jump number device and includes cardboard 1 and movable part 2, cardboard 1 has first working face S1 and second working face S2, and first working face S1 is suitable for ending and supports at the stationary vane trailing edge, and second working face S2 is located first working face S1' S top; the movable component 2 is movably arranged on the clamping plate 1, and the movable component 2 is suitable for being stopped against the head of the movable surface.

It will be appreciated that the device for measuring the aircraft step stops the first working surface S1 at the trailing edge of the fixed wing, and the screw-movable assembly 2 is stopped just at the head of the aircraft active surface, and the gap between the aircraft active surface and the second working surface S2 is measured to calculate the value of the step of conformance between the head of the aircraft active surface and the trailing edge of the fixed wing. The device has the advantages of convenient use, high measurement precision, simple structure, strong practicability and capability of quickly and accurately measuring the step value.

In addition, cardboard 1 is the steel material body, has guaranteed the hardness and the rigidity of measuring aircraft jump device, and difficult deformation.

Optionally, as shown in fig. 1, the movable assembly 2 includes a movable member 21 and a handle 22, the movable member 21 is movably disposed on the card board 1, and a lower end of the movable member 21 is adapted to abut against a head of the movable surface; the handle 22 is connected with the movable piece 21 in interference fit. Here, the lower end surface of the movable element 21 is a smooth surface, and when the lower end surface of the movable element 21 is adapted to abut against the head of the movable surface, the lower end surface of the movable element 21 and the movable surface make surface-to-surface contact without a gap or with a very small gap. In addition, the movable piece 21 is movably arranged on the card board 1, which is helpful for adjusting the position of the lower end surface of the movable piece 21 and realizing the lifting of the lower end surface of the movable piece 21. The handle 22 may be an aluminum material, but other materials may be selected according to specific requirements in other embodiments of the present invention.

In addition, the lower part of the moving part 21 is made of rubber, so that the movable surface of the airplane is well protected in the adjusting process, and the abrasion and paint falling of the movable surface of the airplane are avoided.

Alternatively, as shown in fig. 1, the card board 1 includes a first projecting portion 11 and a flat portion 12, the first projecting portion 11 is connected to the flat portion 12, a bottom surface of the first projecting portion 11 is formed as a first working surface S1, and a bottom surface of the flat portion 12 is formed as a second working surface S2. It will be appreciated that the first boss 11 is placed at the trailing edge of the aircraft fixed wing, such that the first working surface S1 stops at the trailing edge of the aircraft fixed wing; when the lower end surface of the movable member 21 abuts against the head of the movable surface, the step value can be calculated by measuring the distance between the second working surface S2 and the lower end surface of the movable member 21.

Optionally, the movable member 21 is a bolt, the movable member 21 is provided with an external thread, the clamping plate 1 further includes a second protruding portion 13, and the second protruding portion 13 is provided with an internal thread matching the movable member 21. It can be understood that the movable member 21 and the snap-gauge 1 are connected in a matching manner through a bolt, and the matching manner can conveniently realize the movement of the movable member 21 relative to the snap-gauge 1, thereby facilitating the operation of a user. Of course, in other embodiments of the present invention, the movable member 21 may also select other connecting members according to specific requirements.

Alternatively, as shown in fig. 1, there are two second protrusions 13, and the two second protrusions 13 are symmetrically distributed about the center line of the card 1. It should be noted here that the two second convex portions 13 symmetrically distributed about the center line contribute to improving the smoothness of the device for measuring the aircraft step difference, and at the same time, indirectly improve the accuracy of the device for measuring the aircraft step difference. In other embodiments of the present invention, the number of the second protruding portions 13 is not limited to two, and the number of the second protruding portions 13 can be selected according to actual needs.

Optionally, the first working surface S1 and the second working surface S2 are both smooth surfaces. It can be understood that the first working surface S1 is a smooth surface, and when the first working surface S1 is stopped at the trailing edge of the fixed wing of the airplane, the measurement error is effectively reduced, and the accuracy of the measurement step difference is ensured to a certain extent; the second working surface S2 is a smooth surface, which is helpful for indirectly improving the accuracy of measuring the step difference when the vernier caliper is used for measuring the gap value between the second working surface S2 and the lower end surface of the movable piece 21.

Advantageously, the first working surface S1 and the second working surface S2 are in a parallel relationship.

Optionally, the step difference between the first working surface S1 and the second working surface S2 is 5 ± 0.05 mm. Here, when a gap value X (unit: mm) between the movable surface of the airplane and the second working surface S2 is measured by a vernier caliper, if X is equal to or greater than 5mm, a step value D is X-5(mm) and the compliance step is a negative value, based on the measured gap value; if X <5mm, the step value D is 5-X (mm), and the anastomotic step at this time is a positive value. For the measurement of special cases, if the step difference of the coincidence is positive and greater than 5mm, the step difference between the first working surface S1 and the second working surface S2 in the device can be made larger, but the using, measuring and calculating methods are the same as those described above.

Optionally, there are two movable assemblies 2, and the two movable assemblies 2 are symmetrically distributed around the center line of the card board 1. It should be noted here that the two movable assemblies 2 symmetrically distributed about the center line contribute to improving the smoothness of the measuring device of the aircraft step difference, and at the same time, further improve the accuracy of the measuring device. In other embodiments of the present invention, the number of the movable assemblies 2 is not limited to two, and the number of the movable assemblies 2 can be selected according to actual needs.

Optionally, the handle 22 is threadably connected to the moveable member 21. Of course, in other embodiments of the present invention, the connection mode between the handle 22 and the movable element 21 may be selected according to specific requirements.

Alternatively, as shown in fig. 2 to 3, the height of the movable piece 21 is greater than the height of the first protrusion 11. It will be understood that in the case of negative values of the step at the nose of the active surface of the aircraft and at the trailing edge of the fixed wing, the height of the mobile element 21 needs to be greater than the height of the first raised portion 11 in order to measure the compliance step in this case.

The utility model discloses a survey aircraft jump device's application method overview:

placing the first boss 11 at the trailing edge of the aircraft fixed wing, with the first working surface S1 resting on the trailing edge surface of the aircraft fixed wing; twisting the handle 22 to drive the movable piece 21, so that the movable piece 21 just abuts against the head of the movable plane of the airplane; measuring a gap value (unit: mm) between the movable plane and the second working plane S2 by using a vernier caliper; according to the measured gap value, if X is more than or equal to 5mm, the step difference value D is X-5(mm), and the anastomosis step difference is a negative value; if X <5mm, the step value D is 5-X (mm), and the anastomotic step at this time is a positive value. For the measurement of special cases, if the step difference of the coincidence is positive and greater than 5mm, the step difference between the first working surface S1 and the second working surface S2 in the device can be made larger, but the using, measuring and calculating methods are the same as those described above.

In the description herein, references to the description of "some embodiments," "other embodiments," or the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above description is only for the preferred embodiment of the present invention, and for those skilled in the art, there are variations on the detailed description and the application scope according to the idea of the present invention, and the content of the description should not be construed as a limitation to the present invention.

Claims

1. An aircraft step-difference measuring device for measuring the coincidence step-difference value between the head of an aircraft movable surface and the trailing edge of a fixed wing, wherein the head of the aircraft movable surface is connected with the trailing edge of the fixed wing, the aircraft step-difference measuring device comprising:

the clamping plate is provided with a first working surface and a second working surface, the first working surface is suitable for being abutted against the rear edge of the fixed wing, and the second working surface is positioned above the first working surface;

the movable assembly is movably arranged on the clamping plate and is suitable for stopping against the head of the movable surface.

2. The apparatus for measuring aircraft jump as defined in claim 1, wherein said movable assembly comprises:

the movable piece is movably arranged on the clamping plate, and the lower end of the movable piece is suitable for abutting against the head of the movable surface;

the handle is connected with the movable piece in interference tight fit.

3. An aircraft step-difference measuring device according to claim 2, wherein said card comprises a first raised portion and a flat portion, said first raised portion being connected to said flat portion, a bottom surface of said first raised portion being formed as said first working surface, and a bottom surface of said flat portion being formed as said second working surface.

4. An aircraft jump measuring device according to claim 2, wherein the movable member is a bolt, the movable member is provided with an external thread, and the catch plate further comprises a second projection provided with an internal thread for engaging the movable member.

5. An aircraft step-difference measuring device according to claim 4, wherein the number of the second protrusions is two, and the two second protrusions are symmetrically distributed about the centerline of the card.

6. An aircraft step-difference measuring device according to claim 1, wherein said first working surface and said second working surface are both smooth surfaces.

7. An aircraft step-difference measuring device according to claim 1, wherein the step difference between the first working surface and the second working surface is 5 ± 0.05 mm.

8. An aircraft step-difference measuring device according to claim 1, wherein there are two movable assemblies, and the two movable assemblies are symmetrically distributed about a center line of the card.

9. An aircraft jump measuring device according to claim 2, wherein said handle is threadedly connected to said movable member.

10. An aircraft step-difference measuring apparatus according to claim 3, wherein the height of the movable member is greater than the height of the first protrusion.