A device for measuring a deviation of a rudder angle

Abstract

The application relates to a rudder surface angle deviation measuring device and belongs to the technical field of assembly quality inspection. The device solves the problem that the measurement of the zero position angle deviation of a rudder surface cannot be quantified and the accuracy of the rudder surface angle deviation cannot be accurately judged in the prior art. The device comprises a base, a clamping unit and a measuring unit. The clamping unit and the measuring unit are arranged on the base. The device can measure and calculate the rudder surface angle deviation by accurately measuring the rudder surface deviation value, can be used for clamping tail wings of various specifications, and can adapt to the measurement needs of tail wings of different types.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of assembly quality inspection, and particularly relates to a rudder surface angle deviation measuring device. BACKGROUND

[0002] The tail wing structure is generally composed of an inner wing, an outer wing and a rudder surface.

[0003] In the final assembly debugging of the tail wing, the rudder surface symmetry plane and the inner wing symmetry plane should theoretically coincide, and the angle of the rudder surface symmetry plane around the rudder axis relative to the inner wing symmetry plane is substantially zero, which is referred to as the rudder surface zero position. The rudder surface zero position angle deviation is an important design index of the tail wing assembly precision. The angle of the rudder surface directly affects the control of the flight attitude of the aircraft, and serious deviation will directly lead to control failure, so it is necessary to re-adjust the assembly.

[0004] Now, whether the rudder surface zero position angle deviation value is out of tolerance is generally determined by manual judgment, and the hand feeling of the rudder surface and the inner wing at the joint and visual observation are estimated. This method is completely controlled by human senses and experience, has large error and no quantitative basis, and it is difficult to accurately determine whether the deviation meets the requirements. In order to better control the product quality, it is urgent to improve the existing measurement method, and to quantify the measurement result of the rudder surface zero position angle deviation, so as to accurately judge the precision of the rudder surface angle deviation, so as to avoid misjudgment and missed detection of out-of-tolerance products.

[0005] Therefore, there is an urgent need for a rudder surface angle deviation measuring device to overcome the shortcomings of the prior art and solve the above problems. SUMMARY

[0006] In view of the above analysis, the embodiments of the present application aim to provide a rudder surface angle deviation measuring device to solve the problem that the measurement of the rudder surface zero position angle deviation in the prior art cannot be quantified and the precision of the rudder surface angle deviation cannot be accurately judged.

[0007] The purpose of the present application is mainly realized through the following technical solutions:

[0008] A rudder surface angle deviation measuring device, comprising a base, a clamping unit and a measuring unit, the clamping unit and the measuring unit are both arranged on the base.

[0009] Further, the base comprises an upper end face and a lower end face, and the upper end face and the lower end face are parallel.

[0010] Further, the base further comprises a dovetail groove, the dovetail groove is arranged at one end of the base, and the clamping unit and the measuring unit are both connected with the dovetail groove.

[0011] Further, the dovetail groove comprises an end face opening and a bottom face, the end face opening is arranged on the upper end face, the bottom face is parallel to the upper end face, and the area of the bottom face is greater than the area of the end face opening.

[0012] Further, the clamping unit comprises a screw rod base fixed on the base by screws.

[0013] Further, the clamping unit further comprises a screw rod, two ends of the screw rod are connected with the screw rod bases respectively, and the screw rod is rotatable on the screw rod bases.

[0014] Further, the clamping unit further comprises a hand wheel, the hand wheel is arranged at one end of the screw rod, and the screw rod rotates along with the hand wheel when the hand wheel is rotated.

[0015] Further, the clamping unit further comprises a first clamping jaw and a second clamping jaw arranged on the screw rod.

[0016] Further, the screw rod comprises an external thread.

[0017] Further, one end of the first clamping jaw and the second clamping jaw is a nut, and the nut is provided with an internal thread.

[0018] Compared with the prior art, the present application can achieve at least one of the following beneficial effects:

[0019] (1) The measuring device provided by the present application can measure the rudder angle deviation by measuring the rudder deviation value. The present application uses a first dial gauge and a second dial gauge to read the rudder deviation value, and measures the deflection angle of the difference value through the two dial gauges, which has a simple structure.

[0020] (2) The measuring device provided by the present application can be applied to tail wings of various specifications. The distance between the first clamping jaw and the second clamping jaw is adjustable, and is suitable for tail wings of different thicknesses; and multiple clamping units can be used for clamping tail wings of various specifications.

[0021] (3) The distance between the first dial gauge and the second dial gauge of the present application and the base is adjustable, and can adapt to the measurement needs of tail wings of different models.

[0022] (4) The multiple clamping units of the present application can clamp the inner wing positioning surface, can make the inner wing symmetry plane coincide with the measurement symmetry plane, and the first positioning frame and the second positioning frame ensure that the first dial gauge and the second dial gauge measure the front reading to zero, which provides a guarantee for accurate measurement of the rudder zero angle deviation.

[0023] In the present application, the above technical solutions can be combined with each other to realize more preferred combination schemes. Other features and advantages of the present application will be described in the subsequent content, and some advantages will become apparent from the description or be understood through the implementation of the present application. The purpose and other advantages of the present application can be achieved and obtained through the content specifically pointed out in the text and the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0024] The accompanying drawings are included to provide a further understanding of the embodiments and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and are not intended to limit the scope of the application, and like reference numerals designate like parts throughout the drawings.

[0025] Figure 1 Fig. 1 is a schematic diagram of the overall structure of a rudder angle deviation measuring device;

[0026] Figure 2 Fig. 2 is a schematic diagram of the structure of a base;

[0027] Figure 3 Fig. 3 is a schematic diagram of the structure of a clamping unit;

[0028] Figure 4 Fig. 4 is a schematic diagram of the structure of a measuring unit;

[0029] Figure 5 Fig. 5 is a schematic diagram of the structure of a pressure bridge;

[0030] Figure 6 Fig. 6 is a schematic diagram of the structure of a positioning block;

[0031] Figure 7 Fig. 7 is a schematic diagram of the structure of a tail fin.

[0032] Reference signs: 1 - base; 2 - clamping unit; 3 - measuring unit; 4 - screw rod base; 5 - screw rod; 6 - hand wheel; 7 - cylindrical section; 8 - central groove; 9 - pressure bridge; 10 - positioning groove; 11 - dovetail groove; 12 - upper end face; 21 - first clamping jaw; 22 - second clamping jaw; 23 - gasket; 31 - first positioning frame; 32 - second positioning frame; 33 - first micrometer; 34 - second micrometer; 35 - first measuring rod; 36 - second measuring rod; 37 - shaft pin; 100 - tail fin; 101 - inner fin positioning face; 102 - rudder face; 103 - rudder face measuring point; 301 - movable rod; 302 - fixed rod; 303 - twisting shaft pin; 311 - first positioning block; 321 - second positioning block. DETAILED DESCRIPTION

[0033] The preferred embodiments of the present application will be described in detail below with reference to the drawings, which constitute a part of this specification, and are used to explain the principles of the embodiments of the present application, but are not intended to limit the scope of the present application.

[0034] One specific embodiment of the present application, as shown in Figure 1 Fig. 1, discloses a rudder angle deviation measuring device (hereinafter referred to as measuring device), which comprises a base 1, a clamping unit 2 and a measuring unit 3, and the clamping unit 2 and the measuring unit 3 are both arranged on the base 1.

[0035] The measuring device of the present application is suitable for measuring the zero angle deviation of a tail fin 100.

[0036] Preferably, asFigure 2 As shown in the figure, the base 1 includes an upper end surface 12 and a lower end surface (not shown in the figure), the upper end surface 12 and the lower end surface are parallel, and the base 1 further includes a dovetail groove 11, the dovetail groove 11 is arranged at one end of the base 1, and the clamping unit 2 and the measuring unit 3 are connected with the dovetail groove 11. The dovetail groove 11 includes an end surface opening and a bottom surface, the end surface opening is arranged on the upper end surface 12, and the bottom surface is parallel to the upper end surface 12, and the area of the bottom surface is greater than the area of the end surface opening. The clamping unit 2 and the measuring unit 3 can slide in the dovetail groove 11 along the dovetail groove 11, and the dovetail groove 11 ensures that the clamping unit 2 and the measuring unit 3 cannot be separated from the base 1 from the end surface opening.

[0037] Preferably, as shown in the figure, Figure 3 As shown in the figure, the clamping unit 2 includes a screw rod seat 4, a screw rod 5, a hand wheel 6, a first clamping jaw 21 and a second clamping jaw 22. The screw rod seat 4 is fixed on the base 1 by a screw, and the two ends of the screw rod 5 are respectively connected with the screw rod seat 4, the screw rod 5 can rotate on the screw rod seat 4, and the screw rod seat 4 ensures that the screw rod 5 cannot be separated from the screw rod seat 4.

[0038] Preferably, the hand wheel 6 is arranged at one end of the screw rod 5, and the screw rod 5 rotates when the hand wheel 6 is turned, and the hand wheel 6 makes the driving of the screw rod 5 more labor-saving.

[0039] Preferably, the first clamping jaw 21 and the second clamping jaw 22 are arranged on the screw rod 5, the screw rod 5 includes external threads, and one end of the first clamping jaw 21 and the second clamping jaw 22 is a nut, and the nut is provided with internal threads. The internal threads on the nut can cooperate with the external threads of the screw rod 5, and the screw rod 5 can drive the first clamping jaw 21 and the second clamping jaw 22 to slide on the screw rod 5.

[0040] Preferably, the screw rod 5 includes a first external thread section and a second external thread section, the first external thread section and the second external thread section are arranged at the two ends of the screw rod 5, the external threads are arranged on the first external thread section and the second external thread section, the external threads of the first external thread section and the second external thread section have equal pitches and opposite rotation directions; one end of the first clamping jaw 21 is a first nut, and one end of the second clamping jaw 22 is a second nut, the first nut is arranged on the first external thread section, and the second nut is arranged on the second external thread section. When the screw rod 5 is rotated, the first clamping jaw 21 and the second clamping jaw 22 can simultaneously move towards or away from each other, and the movement distance of each is equal. The longitudinal section of the first nut and the second nut is trapezoidal, the first nut and the second nut can slide in the dovetail groove 11 along the dovetail groove 11, the first nut and the second nut ensure that the first clamping jaw 21 and the second clamping jaw 22 cannot be separated from the base 1 from the end surface opening, and ensure that the first clamping jaw 21 and the second clamping jaw 22 cannot be tilted towards the base 1. When measuring the zero angle deviation of the rudder surface, the first clamping jaw 21 and the second clamping jaw 22 are used to clamp the tail fin 100, the distance between the first clamping jaw 21 and the second clamping jaw 22 is adjustable, and can be suitable for tail fins 100 of different thicknesses.

[0041] Preferably, the lead screw 5 is provided with a cylindrical section 7, which is arranged between the first and second external thread sections, is coaxial with the lead screw 5, and has a diameter smaller than the external diameter of the first and second external thread sections. The base 1 is provided with a fixing structure capable of clamping the cylindrical section 7, so that the lead screw 5 can rotate on the base 1, and the fixing structure can ensure that the lead screw 5 cannot move along the lead screw axis.

[0042] Preferably, the first and second clamping jaws 21 and 22 are mirror-symmetric relative to a measurement symmetry plane, and can be connected after moving towards each other, with the contact point being located on the measurement symmetry plane. The measurement symmetry plane is perpendicular to the axis of the cylindrical section 7 and equally divides the cylindrical section 7 in the axial direction. When measuring the zero angle deviation of the rudder surface, the first and second clamping jaws 21 and 22 clamp the fixed tail fin 100, at which time the inner wing symmetry plane coincides with the measurement symmetry plane.

[0043] Preferably, one end of each of the first and second clamping jaws 21 and 22 is provided with a gasket 23. The gasket 23 is conical or hemispherical, with the large end connected to one end of the first and second clamping jaws 21 and 22, and the small end connected to the tail fin 100, so as to clamp the inner wing positioning surface 101. The gasket 23 is used to increase the friction coefficient of the first and second clamping jaws 21 and 22, and ensure stable clamping of the tail fin 100.

[0044] Preferably, the gasket 23 is an elastic polymer gasket, which ensures that the first and second clamping jaws 21 and 22 will not damage the surface of the tail fin 100 when clamping the tail fin 100.

[0045] Preferably, as shown in Figure 4 the measurement unit 3 includes a lead screw seat 4, a lead screw 5, a hand wheel 6, a first positioning frame 31, a second positioning frame 32, a first micrometer 33, and a second micrometer 34. The lead screw 5 includes a cylindrical section 7, a first external thread section, and a second external thread section. The first positioning frame 31 is arranged on the first external thread section, and the second positioning frame 32 is arranged on the second external thread section. One end of the first positioning frame 31 is provided with a first nut, and the other end is a first measuring rod 35. One end of the second positioning frame 32 is provided with a second nut, and the other end is a second measuring rod 36. The first micrometer 33 is fixedly arranged at one end of the first measuring rod 35, and the second micrometer 34 is fixedly arranged at one end of the second measuring rod 36.

[0046] The longitudinal section of the first and second nuts is trapezoidal, and the first and second nuts can slide in the dovetail groove 11. The first and second nuts ensure that the first and second positioning frames 31 and 32 cannot be separated from the base 1 from the end face opening, and also ensure that the first and second positioning frames 31 and 32 cannot be tilted towards the base 1.

[0047] Preferably, the first positioning frame 31 and the second positioning frame 32 are mirror-symmetrical with respect to the measurement symmetry plane. Rotating the lead screw 5 allows the first positioning frame 31 and the second positioning frame 32 to move simultaneously towards or away from each other, with each moving equal distance. The first positioning frame 31 and the second positioning frame 32 drive the first dial indicator 33 and the second dial indicator 34 to move towards or away from each other, connecting or moving the first dial indicator 33 and the second dial indicator 34 away from the tail fin 100 to measure the zero-position angle deviation of the control surface.

[0048] Preferably, the first positioning frame 31 is provided with a first positioning block 311, and the second positioning frame 32 is provided with a second positioning block 321. The first positioning block 311 and the second positioning block 321 are protrusions on the first positioning frame 31 and the second positioning frame 32, respectively. When the first positioning frame 31 and the second positioning frame 32 move towards each other, the first positioning block 311 and the second positioning block 321 can connect, and their contact point is located on the measurement symmetry plane. The first positioning block 311 and the second positioning block 321 can stop the relative movement of the first positioning frame 31 and the second positioning frame 32 and fix the stopping position of the first positioning frame 31 and the second positioning frame 32. At this time, the first positioning frame 31 and the second positioning frame 32 are mirror symmetrical with respect to the measurement symmetry plane. This position is the zero position of the first positioning frame 31 and the second positioning frame 32, and also the zero position of the measurement unit 3.

[0049] Both the first dial indicator 33 and the second dial indicator 34 are mature distance measurement dial indicators in the prior art, and both include probes. The probes of the first dial indicator 33 and the second dial indicator 34 are arranged opposite each other. The first dial indicator 33 and the second dial indicator 34 are driven by the first positioning frame 31 and the second positioning frame 32 to achieve simultaneous or opposite movements, and their respective movement distances are equal. After the measuring unit 3 reaches the zero position, the probes of the first dial indicator 33 and the second dial indicator 34 can connect, and the probe contact point is located on the measurement symmetry plane. At this time, the readings of the first dial indicator 33 and the second dial indicator 34 are zeroed. When measuring the zero-position angle deviation of the control surface, the probes of the first dial indicator 33 and the second dial indicator 34 can connect to the control surface 103 to realize the measurement of the zero-position angle deviation of the control surface.

[0050] Preferably, such as Figure 5 As shown, the fixing structure on the base 1 consists of a central groove 8 and a pressure bridge 9. The pressure bridge 9 is disposed within the central groove 8 and can be fixedly connected to the base 1. The pressure bridge 9 is used to hold the lead screw 5 of the clamping unit 2 and the measuring unit 3.

[0051] Preferably, the pressing bridge 9 is provided with a positioning groove 10, the opening of the positioning groove 10 is towards one end of the pressing bridge 9, the cylindrical segment 7 can be clamped into the positioning groove 10 and can rotate in the positioning groove 10, the positioning groove 10 ensures that the lead screw 5 cannot move in the axial direction of the lead screw 5, thereby ensuring that the first clamping jaw 21 and the second clamping jaw 22 and the first positioning frame 31 and the second positioning frame 32 are mirror-symmetric relative to the measurement symmetry plane.

[0052] The first clamping jaw 21 and the second clamping jaw 22 of the plurality of clamping units 2 can clamp the inner wing positioning surface 101, and can make the inner wing symmetry plane coincide with the measurement symmetry plane, and the first positioning frame 31 and the second positioning frame 32 ensure that the first micrometer 33 and the second micrometer 34 measure the front reading to zero, which provides a guarantee for accurate measurement of the rudder zero angle deviation.

[0053] Preferably, as shown in Figure 6 The first measuring rod 35 and the second measuring rod 36 are both foldable structures, and each includes a movable rod 301, a fixed rod 302, and a hinge pin 303, and the movable rod 301 and the fixed rod 302 are hinged by the hinge pin 303. The first micrometer 33 is arranged at one end of the movable rod 301 of the first measuring rod 35, and the second micrometer 34 is arranged at one end of the movable rod 301 of the second measuring rod 36. By folding the two movable rods 301, the distance between the first micrometer 33 and the second micrometer 34 and the base 1 can be adjusted to adapt to the measurement needs of different models of tail wings 100.

[0054] Preferably, the hinge pin 303 is a screw, by loosening the hinge pin 303, the movable rod 301 can freely rotate around the hinge pin 303, and by tightening the hinge pin 303, the movable rod 301 is fixedly connected with the fixed rod 302. The hinge pin 303 can not only freely adjust the first micrometer 33 and the second micrometer 34, but also fix the distance between the first micrometer 33 and the second micrometer 34 and the base 1, so as to adapt to the measurement needs of different models of tail wings 100.

[0055] In use, as shown in FIG. 7, first, the model of the tail fin 100 and the specific position of the rudder surface measuring point 103 are determined; then the twist shaft pin 303 is loosened, the distance between the first and second micrometers 33 and 34 and the base 1 is adjusted, so that the distance between the probes of the first and second micrometers 33 and 34 and the base 1 is equal to the distance from the rudder surface measuring point 103 to the bottom edge of the tail fin 100; the twist shaft pin 303 is tightened to fix the positions of the first and second micrometers 33 and 34; the hand wheel 6 of the measuring unit 3 is rotated to rotate the lead screw 5, so that the first and second positioning frames 31 and 32 drive the first and second micrometers 33 and 34 to move towards each other until the first and second positioning blocks 311 and 321 are connected to each other, at which time the readings of the first and second micrometers 33 and 34 are zeroed; the distance between the first and second clamping jaws 21 and 22 and the first and second positioning frames 31 and 32 is increased, and the tail fin 100 is vertically placed on the base 1 of the measuring device; the first and second positioning frames 31 and 32 are moved towards each other to adjust the position of the tail fin 100, so that the probes of the first and second micrometers 33 and 34 are aligned with the rudder surface measuring point 103; the first and second clamping jaws 21 and 22 are moved towards each other to clamp the inner wing positioning surface 101 and fix the tail fin 100, at which time the inner wing symmetry plane coincides with the measuring symmetry plane; the first and second positioning frames 31 and 32 drive the first and second micrometers 33 and 34 to move towards each other until the first and second positioning blocks 311 and 321 are connected to each other, and the readings of the first and second micrometers 33 and 34 are read to calculate the rudder surface zero position angle deviation.

[0056] Compared with the prior art, the distance between the first and second clamping jaws 21 and 22 is adjustable, which can be suitable for tail fins 100 of different thicknesses; when measuring the rudder surface zero position angle deviation, the probes of the first and second micrometers 33 and 34 can be connected to the rudder surface 102 to realize the measurement of the rudder surface zero position angle deviation; the first and second clamping jaws 21 and 22 of the multiple sets of clamping units 2 can clamp the inner wing positioning surface 101, so that the inner wing symmetry plane coincides with the measuring symmetry plane, and the first and second positioning frames 31 and 32 ensure that the readings of the first and second micrometers 33 and 34 are zeroed before measurement, which provides a guarantee for accurate measurement of the rudder surface zero position angle deviation. The distance between the first and second micrometers 33 and 34 and the base 1 can be adjusted to adapt to the measurement needs of tail fins 100 of different models.

[0057] The above describes only the preferred specific embodiments of the present application, but the protection scope of the present application is not limited thereto, and any changes or replacements within the technical scope disclosed by the present application can be easily thought of by those skilled in the art, which should be covered within the protection scope of the present application.

Claims

1. A device for measuring the angle deviation of a control surface, characterized in that, It includes a base (1), a clamping unit (2) and a measuring unit (3), both of which are mounted on the base (1); The clamping unit (2) includes a lead screw seat (4), a lead screw (5), a first jaw (21), and a second jaw (22). The lead screw seat (4) is fixed to the base (1) by screws, and the lead screw (5) can rotate on the lead screw seat (4). The lead screw (5) includes a cylindrical section (7), a first external thread section, and a second external thread section. The external thread pitch of the first external thread section and the second external thread section are equal and the rotation directions are opposite. The first nut of the first jaw (21) is set on the first external thread section, and the second nut of the second jaw (22) is set on the second external thread section. The first jaw (21) and the second jaw (22) can move in a mirror-symmetric manner relative to the measurement symmetry plane. The cylindrical section (7) is set between the first external thread section and the second external thread section, and the diameter of the cylindrical section (7) is smaller than the outer diameter of the first external thread section and the second external thread section. The measuring unit (3) includes a lead screw seat (4), a lead screw (5), a first positioning frame (31), a second positioning frame (32), a first dial indicator (33), and a second dial indicator (34). The first positioning frame (31) is set on the first external thread section of the lead screw (5), and the second positioning frame (32) is set on the second external thread section of the lead screw (5). One end of the first positioning frame (31) is provided with a first nut, and the other end is a first measuring rod (35). One end of the second positioning frame (32) is provided with a second nut, and the other end is a second measuring rod (36). The first dial indicator (33) is fixedly set on one end of the first measuring rod (35), and the second dial indicator (34) is fixedly set on one end of the second measuring rod (36). The base (1) also includes a pressure bridge (9), which can be fixedly connected to the base (1). A positioning groove (10) is provided on the pressure bridge (9). The cylindrical section (7) can be inserted into the positioning groove (10) and can rotate in the positioning groove (10). The positioning groove (10) ensures that the lead screw (5) cannot move axially, thereby ensuring that the first gripper (21) and the second gripper (22), as well as the first positioning frame (31) and the second positioning frame (32), are mirror symmetrical with respect to the measurement symmetry plane.

2. The rudder surface angle deviation measuring device according to claim 1, characterized in that, The base (1) includes an upper end face (12) and a lower end face, which are parallel to each other.

3. The rudder surface angle deviation measuring device according to claim 2, characterized in that, The base (1) also includes a dovetail groove (11), which is located at one end of the base (1). The clamping unit (2) and the measuring unit (3) are both connected to the dovetail groove (11).

4. The rudder surface angle deviation measuring device according to claim 3, characterized in that, The dovetail groove (11) includes an end face opening and a bottom face. The end face opening is located on the upper end face (12), and the bottom face is parallel to the upper end face (12). The area of ​​the bottom face is larger than the area of ​​the end face opening.

5. The rudder surface angle deviation measuring device according to claim 1, characterized in that, The clamping unit (2) also includes a handwheel (6), which is located at one end of the lead screw (5). When the handwheel (6) is turned, the lead screw (5) rotates accordingly.

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