CN110160731B - Adjustable gap device for flutter test - Google Patents
Adjustable gap device for flutter test Download PDFInfo
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- CN110160731B CN110160731B CN201810899719.1A CN201810899719A CN110160731B CN 110160731 B CN110160731 B CN 110160731B CN 201810899719 A CN201810899719 A CN 201810899719A CN 110160731 B CN110160731 B CN 110160731B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Abstract
The invention provides an adjustable gap device for a flutter test, which comprises a base, a rotating rigidity spring part, an ejector pin, a fixing clip, a first fastening assembly, a gap adjusting ring and a second fastening assembly, wherein the ejector pin is fixedly arranged on the rotating rigidity spring part, the open end of the fixing clip is used for accommodating a rudder shaft, a first connecting section of the ejector pin is positioned in an accommodating hole of the fixing clip, the first fastening assembly is used for fixedly arranging the fixing clip on the rudder shaft, the gap adjusting ring is sleeved on the first connecting section of the ejector pin and positioned in the accommodating hole of the fixing clip, the second fastening assembly is sleeved on the first connecting section of the ejector pin, the second fastening assembly is used for fastening the gap adjusting ring to adjust the height of the gap adjusting ring, and the adjustable gap device adjusts the gap on the rotating freedom degree of the rudder shaft by adjusting the height of the gap adjusting ring. By applying the technical scheme of the invention, the technical problem that the influence rule of different gap sizes on the flutter characteristic cannot be obtained in the prior art is solved.
Description
Technical Field
The invention relates to the technical field of gap nonlinearity research, in particular to an adjustable gap device for a flutter test.
Background
The control surface is an important control surface on the missile, and when the control surface is connected with the steering engine, the control surface usually has larger clearance in the rotational freedom degree. Due to the presence of the gap, limit ring oscillations may occur during flight testing, and may even diverge. During flutter test, the change rule of the wing/rudder along with bending rigidity and torsional rigidity can be obtained, and the influence of design parameters on flutter characteristics is clarified. Because the real wing/rudder system has a gap, the influence of the gap on the flutter characteristic of the structure is obtained through a flutter test, and the influence rule of the gap on the limit ring and the flutter is clarified. However, in the prior art, the influence rule of different gap sizes on the flutter characteristics cannot be obtained.
Disclosure of Invention
The invention provides an adjustable gap device for a flutter test, which can solve the technical problem that the influence rule of different gap sizes on the flutter characteristic cannot be obtained in the prior art.
The invention provides an adjustable gap device for a flutter test, which comprises: a base; the rotating stiffness spring part is fixedly arranged on the base; the thimble is fixedly arranged on the rotary stiffness spring part and comprises a first positioning ring and a first connecting section, and the diameter of the first positioning ring is larger than that of the first connecting section; the fixing clip is provided with an opening end and a connecting end, the opening end of the fixing clip is used for accommodating the rudder shaft, the connecting end of the fixing clip is provided with an accommodating hole, the first connecting section of the thimble is positioned in the accommodating hole, the first positioning ring is used for positioning the connecting end of the fixing clip, and the axis direction of the rudder shaft is respectively vertical to the axis direction of the thimble and the length direction of the fixing clip; the first fastening assembly is arranged at the opening end of the fixing clip and is used for fixedly arranging the fixing clip on the rudder shaft; the clearance adjusting ring is sleeved on the first connecting section of the thimble and is positioned in the accommodating hole of the fixing clip, and the connecting end of the clearance adjusting ring and the connecting end of the fixing clip are in clearance fit; the second fastening assembly is sleeved on the first connecting section of the thimble, the gap adjusting ring is arranged between the first positioning ring and the second fastening assembly, the second fastening assembly is used for fastening the gap adjusting ring to adjust the height of the gap adjusting ring, and the gap adjusting device adjusts the gap on the rotation freedom degree of the rudder shaft by adjusting the height of the gap adjusting ring.
Furthermore, the first connecting section of thimble has the external screw thread, and second fastening components includes first nut, and first nut and first connecting section screw-thread fit, adjustable clearance device is through screwing up first nut in order to adjust the height of clearance adjustment ring.
Further, the clearance in the rotational degree of freedom of the rudder shaft can be determined according to
Where h is the height of the gap adjustment ring, h0In order to fix the height of the connecting end of the clamp, delta l is the deformation of the clearance adjusting ring in the height direction, l is the distance from the center of the accommodating hole to the axis direction of the rudder shaft, M is the tightening torque of the first nut, k is the torsional coefficient, d is the thread engineering diameter of the first connecting section, and P is the diameter of the first connecting section0Is a first screwThe tightening force of the nut, a is the sectional area of the gap adjustment ring, and E is the elastic modulus of the gap adjustment ring.
Further, the rotary stiffness spring part is provided with a first connecting hole and a first locating hole which are communicated, the ejector pin further comprises a second locating ring and a second connecting section, the second locating ring is matched with the first locating hole, the second connecting section is arranged in the first connecting hole, the second connecting section is provided with an external thread, the adjustable clearance device further comprises a second nut, and the second nut is in threaded fit with the second connecting section so as to fix the ejector pin on the rotary stiffness spring part.
Furthermore, the first connecting hole and the accommodating hole of the fixing clip are coaxially arranged.
Further, the fixing clip comprises a fixed connection section, a first clamping jaw and a second clamping jaw, the first clamping jaw and the second clamping jaw are arranged in parallel and are connected with the fixed connection section, the first clamping jaw and the second clamping jaw form an opening end, and the accommodating hole is formed in the fixed connection section.
Further, the first fastening assembly comprises a fastening screw and a third nut, and the fastening screw respectively penetrates through the first jaw and the second jaw and is matched with the third nut to fixedly arrange the fixing clip on the rudder shaft.
Further, the sectional area of the gap adjusting ring is 1 to 2 times of the thread area of the first connecting section of the thimble.
Further, the adjustable gap device further comprises a first gasket, and the first gasket is arranged between the first nut and the gap adjusting ring.
Further, the adjustable gap device further comprises a second gasket and a third gasket, the second gasket is arranged between the second nut and the rotational stiffness spring part, and the third gasket is arranged between the third nut and the first jaw.
By applying the technical scheme of the invention, the fixing clip is arranged on the rudder shaft through the first fastening assembly, the thimble is fixed on the rotating rigidity spring plate, the gap adjusting ring is sleeved on the thimble and penetrates through the accommodating cavity of the fixing clip, and the gap adjusting ring is screwed through the second fastening assembly, so that the structure forms a gap structure with the rotating (twisting) freedom degree of the rudder shaft. In this way, the purpose of controlling the rotation (torsion) freedom degree gap of the rudder shaft can be achieved by changing the height of the gap adjusting ring. Because the control surface and the control shaft are designed into a whole, the purpose of controlling the clearance of the rotation (torsion) freedom degree of the control surface can be achieved by changing the height of the clearance adjusting ring. By adopting the technical scheme of the invention, the controllable structural clearance can be obtained, the controllability of the clearance of the rotational (torsional) freedom degree in the flutter test process is realized, and the method has wide application prospect in the aspect of nonlinear flutter test.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 illustrates a cross-sectional view of an adjustable clearance device for flutter testing provided in accordance with a particular embodiment of the present invention;
FIG. 2 shows an enlarged partial view at A of the adjustable clearance device for flutter testing provided in FIG. 1;
FIG. 3 shows a front view of the adjustable clearance device provided in FIG. 1 for flutter testing;
FIG. 4 shows a top view of the adjustable clearance device provided in FIG. 1 for flutter testing;
fig. 5 shows a dimensional schematic diagram of an adjustable gap device for flutter testing provided according to a specific embodiment of the invention.
Wherein the figures include the following reference numerals:
10. a base; 20. a rotational stiffness spring member; 21. a first connection hole; 22. a first positioning hole; 30. a thimble; 31. a first positioning ring; 32. a first connection section; 33. a second positioning ring; 34. a second connection section; 40. fixing the clip; 41. a fixed connection section; 42. a first jaw; 43. a second jaw; 50. a first fastening component; 51. fastening screws; 52. a third nut; 60. a gap adjusting ring; 70. a first nut; 80. a second nut; 90. a first gasket; 100. a second gasket; 110. a third gasket; 200. a rudder shaft.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 to 5, according to an embodiment of the present invention, there is provided an adjustable gap device for flutter test, the adjustable gap device includes a base 10, a rotational stiffness spring member 20, an ejector pin 30, a fixing clip 40, a first fastening member 50, a gap adjustment ring 60, and a second fastening member, the rotational stiffness spring member 20 is fixedly disposed on the base 10, the ejector pin 30 is fixedly disposed on the rotational stiffness spring member 20, the ejector pin 30 includes a first positioning ring 31 and a first connecting section 32, a diameter of the first positioning ring 31 is larger than a diameter of the first connecting section 32, the fixing clip 40 has an open end and a connecting end, the open end of the fixing clip 40 is used for receiving a rudder shaft, the connecting end of the fixing clip 40 has a receiving hole, the first connecting section 32 of the ejector pin 30 is located in the receiving hole, the first positioning ring 31 is used for positioning the connecting end of the fixing clip 40, an axial direction of the rudder shaft is respectively perpendicular to an axial direction of the ejector pin 30 and a length direction of the fixing clip, the first fastening assembly 50 is arranged at an opening end of the fixing clip 40, the first fastening assembly 50 is used for fixedly arranging the fixing clip 40 on the rudder shaft, the gap adjusting ring 60 is sleeved on the first connecting section 32 of the thimble 30 and is located in an accommodating hole of the fixing clip 40, the connecting end of the gap adjusting ring 60 and the fixing clip 40 is in clearance fit, the second fastening assembly is sleeved on the first connecting section 32 of the thimble 30, the gap adjusting ring 60 is arranged between the first positioning ring 31 and the second fastening assembly, the second fastening assembly is used for fastening the gap adjusting ring 60 to adjust the height of the gap adjusting ring 60, and the adjustable gap device adjusts the gap on the rotation freedom degree of the rudder shaft 200 by adjusting the height of the gap adjusting ring 60.
By applying the configuration mode, the fixing clip is installed on the rudder shaft through the first fastening assembly, the thimble is fixed on the rotating rigidity spring plate, the gap adjusting ring is sleeved on the thimble and penetrates through the accommodating cavity of the fixing clip, and the gap adjusting ring is screwed through the second fastening assembly, so that the structure forms a rotating (twisting) freedom gap structure of the rudder shaft. In this way, the purpose of controlling the rotation (torsion) freedom degree gap of the rudder shaft can be achieved by changing the height of the gap adjusting ring. Because the control surface and the control shaft are designed into a whole, the purpose of controlling the clearance of the rotation (torsion) freedom degree of the control surface can be achieved by changing the height of the clearance adjusting ring. By adopting the technical scheme of the invention, the controllable structural clearance can be obtained, the controllability of the clearance of the rotational (torsional) freedom degree in the flutter test process is realized, and the method has wide application prospect in the aspect of nonlinear flutter test. Meanwhile, the adjustable gap device can also be used for other gap structure designs.
Further, in the present invention, in consideration of structural complexity, the first connection section 32 of the thimble 30 may be configured to have an external thread, the second fastening assembly includes a first nut 70, the first nut 70 is screw-engaged with the first connection section 32, and the adjustable gap means adjusts the height of the gap adjustment ring 60 by tightening the first nut 70. With this arrangement, different forces are applied to the gap adjustment ring 60 by the first nut 70 to change the height of the gap adjustment ring 60, thereby enabling an adjustable gap with rotational (torsional) freedom. When the flutter research is carried out, according to different clearance states, structural responses under different clearance states can be obtained, the influence rule of the clearance on the flutter characteristic and the limit ring characteristic is obtained, and the knowledge of the nonlinear clearance is improved.
Specifically, in the present invention, as shown in fig. 2 and 5, the clearance in the rotational degree of freedom of the rudder shaft 200 may be determined according to
Where h is the height of the gap adjustment ring 60, h0To fix the height of the connection end of the clip 40, Δ l is the amount of deformation in the height direction of the gap adjustment ring 60, l is the distance of the center of the accommodation hole from the axis direction of the rudder shaft, M is the tightening torque of the first nut 70, k is the torsional coefficient, d is the thread engineering diameter of the first connection section 32, P0The tightening force of the first nut 70 is a cross-sectional area of the gap adjustment ring 60, and E is an elastic modulus of the gap adjustment ring 60.
With this arrangement, the height of the clearance adjustment ring 60 can be adjusted by applying different forces to the clearance adjustment ring 60 by the first nut 70, and the clearance in the rotational degree of freedom of the rudder shaft 200 can be obtained according to the above formula. Therefore, the device can realize the gap nonlinearity of the rotation freedom degree, and the research on the influence rule of the gap nonlinearity of the rotation (torsion) freedom degree on the flutter characteristic of the control surface is realized.
Further, in the present invention, in order to achieve the fixed connection between the thimble 30 and the rotational stiffness spring member 20, the rotational stiffness spring member 20 may be configured to have a first connection hole 21 and a first positioning hole 22 which are communicated with each other, the thimble 30 further includes a second positioning ring 33 and a second connection section 34, the second positioning ring 33 is matched with the first positioning hole 22, the second connection section 34 is disposed in the first connection hole 21, the second connection section 34 has an external thread, and the adjustable gap device further includes a second nut 80, and the second nut 80 is in threaded engagement with the second connection section 34 to fix the thimble 30 on the rotational stiffness spring member 20.
As an embodiment of the present invention, one end of the rotational stiffness spring member 20 is fixedly disposed on the base 10 by a screw, the other end of the rotational stiffness spring member 20 is formed with a first connection hole 21 and a first positioning hole 22, when the thimble 30 is mounted, the second positioning ring 33 of the thimble 30 is matched with the first positioning hole 22 of the rotational stiffness spring member 20, the second connection section 34 is disposed in the first connection hole 21, and the second nut 80 is threadedly matched with the second connection section 34 to fixedly dispose the thimble 30 on the rotational stiffness spring member 20.
Further, in the present invention, in order to improve the accuracy of the adjustable gap device in performing the chattering test, the first connection hole 21 and the receiving hole of the fixing clip 40 may be arranged to be coaxially disposed.
Further, as an embodiment of the present invention, as shown in fig. 1, the fixing clip 40 includes a fixing connection section 41, a first claw 42 and a second claw 43, the first claw 42 and the second claw 43 are arranged in parallel and are both connected to the fixing connection section 41, the first claw 42 and the second claw 43 form an open end, and the receiving hole is provided on the fixing connection section 41.
With this configuration, when the fixing clip 40 is mounted on the rudder shaft 200, the fixing clip 40 is sleeved outside the rudder shaft 200 through the opening end formed by the first claw 42 and the second claw 43, and then the first fastening assembly 50 fastens the fixing clip 40 to the rudder shaft 200. Specifically, in the present invention, the first fastening assembly 50 includes a fastening screw 51 and a third nut 52, and the fastening screw 51 passes through the first jaw 42 and the second jaw 43, respectively, and cooperates with the third nut 52 to fixedly dispose the fixing clip 40 on the rudder shaft.
Further, in the present invention, in order to facilitate the adjustment of the gap, the cross-sectional area of the gap adjustment ring 60 may be configured to be 1 to 2 times the threaded area of the first connection section 32 of the thimble 30. In an embodiment of the present invention, the gap adjustment ring 60 is a circular tube, and is in a clearance fit with the receiving hole of the fixing clip 40, the diameter of the receiving hole of the fixing clip is slightly larger than the outer diameter of the gap adjustment ring, and the cross-sectional area of the gap adjustment ring 60 is 1 to 2 times of the threaded area of the first connecting section 32 of the thimble 30. In the present invention, since the gap adjustment ring 60 has an inner hole, and is fitted around the outside of the thimble 30 through the inner hole, the sectional area of the gap adjustment ring 60 referred to herein is an annular sectional area of the gap adjustment ring 60.
In the present invention, in order to improve the adjustment accuracy of the adjustable gap means, the adjustable gap means may be configured to further include a first washer 90, a second washer 100, and a third washer 110, the first washer 90 being disposed between the first nut 70 and the gap adjustment ring 60, the second washer 100 being disposed between the second nut 80 and the rotational stiffness spring member 20, and the third washer 110 being disposed between the third nut 52 and the first pawl 42.
For further understanding of the present invention, the operation of the adjustable gap device for flutter test of the present invention will be described in detail with reference to fig. 1 to 5.
As shown in fig. 1 to 5, as an embodiment of the present invention, the adjustable gap device includes a base 10, a rotational stiffness spring member 20, a thimble 30, a fixing clip 40, a first fastening assembly 50, a gap adjusting ring 60, a first nut 70, a second nut 80, a first washer 90, a second washer 100, and a third washer 110, the fixing clip 40 includes a fixing connection section 41, a first jaw 42, and a second jaw 43, the first jaw 42 and the second jaw 43 are disposed in parallel and are connected to the fixing connection section 41, the first jaw 42 and the second jaw 43 form an open end, and a receiving hole is disposed on the fixing connection section 41.
In operation, the fixing clip 40 is firstly sleeved outside the rudder shaft 200 through an opening end formed by the first jaw 42 and the second jaw 43, and then the fastening screw 51 passes through the first jaw 42 and the second jaw 43 respectively and is matched with the third nut 52, and at this time, the fastening screw 51 is in an incompletely tightened state. The rotational stiffness spring member 20 is pre-fixed to the base 10 by a screw.
Then, an appropriate thimble 30 is selected, and the gap adjusting ring 60 is fitted over the thimble 30. The thimble 30 includes a first retaining ring 31, a first connection section 32, a second retaining ring 33, and a second connection section 34, the second retaining ring 33 of the thimble 30 is engaged with the first retaining hole 22 of the rotational stiffness spring member 20, the second connection section 34 is disposed in the first connection hole 21, a second nut 80 is threadedly engaged with the second connection section 34 to fixedly dispose one end of the thimble 30 on the rotational stiffness spring member 20, and at this time, the second nut 80 is in an incompletely tightened state. The first positioning ring 31 of the thimble 30 is matched and positioned with the connecting end of the fixing clip 40, and the first connecting section 32 of the thimble 30 and the gap adjusting ring 60 are located in the receiving hole of the connecting end of the fixing clip 40 together.
Then, the relative positions of the fixing clip 40 and the rudder shaft 200 and the rotational stiffness spring member 20 and the base 10 are finely adjusted, so that the first connection hole 21 of the rotational stiffness spring member 20 is coaxial with the accommodation hole of the fixing clip 40 and the thimble 30. The fastening screw 51 is tightened to fix the fixing clip 40 to the rudder shaft 200, and the connection screw of the rotational stiffness spring member 20 to the base 10 is tightened to completely fix the rotational stiffness spring member 20 to the base 10. The second nut 80 is tightened, the distance l from the center of the receiving hole of the fixing clip 40 to the axis direction of the rudder shaft 200 is measured, the height h of the gap adjusting ring 60 is measured, and the gap adjusting ring 60 is mounted on the fixing clip 40.
Finally, the first nut 70 at the clearance adjustment ring 60 is tightened using a torque wrench, noting the firstTightening torque M of nut 70. According to the formula
To obtain the clearance in the rotational degree of freedom of the rudder shaft 200, wherein h is the height of the clearance adjusting ring 60, h0To fix the height at the connection end of the clip 40, Δ l is the amount of deformation in the height direction of the gap adjustment ring 60, l is the distance from the center of the accommodation hole to the axis direction of the rudder shaft, M is the tightening torque of the first nut 70, k is the torsional coefficient, d is the thread engineering diameter of the first connection section 32, P0The tightening force of the first nut 70 is a cross-sectional area of the gap adjustment ring 60, and E is an elastic modulus of the gap adjustment ring 60. Thus, different gap values can be obtained by adjusting the height of the gap adjustment ring 60. The device realizes the gap nonlinearity of the rotational degree of freedom and the research on the influence rule of the gap nonlinearity of the rotational (torsional) degree of freedom on the flutter characteristic of the control surface.
In summary, compared with the prior art, the adjustable gap device for the flutter test provided by the invention realizes the structural realization problem that the rotation (or torsion) freedom degree of the flutter test model design has the adjustable gap. In the test process, the adjustable clearance of the rotation (torsion) freedom degree is realized by adjusting the height of the clearance adjusting ring, and the influence rule of the clearance on the flutter characteristic and the limit ring characteristic is obtained. Therefore, the invention has advanced technology, simple and practical test implementation method, greatly reduces the difficulty of model design and the cost of wind tunnel test, saves the development cost and has higher model practical value.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An adjustable gap device for flutter testing, comprising:
a base (10);
a rotational stiffness spring member (20), the rotational stiffness spring member (20) being fixedly disposed on the base (10);
the thimble (30), the thimble (30) is fixedly arranged on the rotational stiffness spring piece (20), the thimble (30) comprises a first positioning ring (31) and a first connecting section (32), and the diameter of the first positioning ring (31) is larger than that of the first connecting section (32);
the fixing clip (40) is provided with an opening end and a connecting end, the opening end of the fixing clip (40) is used for accommodating the rudder shaft, the connecting end of the fixing clip (40) is provided with an accommodating hole, the first connecting section (32) of the thimble (30) is located in the accommodating hole, the first positioning ring (31) is used for positioning the connecting end of the fixing clip (40), and the axial direction of the rudder shaft is respectively perpendicular to the axial direction of the thimble (30) and the length direction of the fixing clip (40);
a first fastening assembly (50), wherein the first fastening assembly (50) is arranged at the opening end of the fixing clip (40), and the first fastening assembly (50) is used for fixedly arranging the fixing clip (40) on the rudder shaft;
the clearance adjusting ring (60) is sleeved on the first connecting section (32) of the thimble (30) and is positioned in the accommodating hole of the fixed clamp (40), and the connecting end of the clearance adjusting ring (60) and the fixed clamp (40) is in clearance fit;
the second fastening assembly is sleeved on the first connecting section (32) of the thimble (30), the gap adjusting ring (60) is arranged between the first positioning ring (31) and the second fastening assembly, the second fastening assembly is used for fastening the gap adjusting ring (60) to adjust the height of the gap adjusting ring (60), and the gap adjusting device adjusts the gap on the rotation freedom degree of the rudder shaft by adjusting the height of the gap adjusting ring (60).
2. The adjustable clearance device for flutter testing according to claim 1, wherein the first connection section (32) of the ejector pin (30) has an external thread, the second fastening assembly comprises a first nut (70), the first nut (70) is in threaded engagement with the first connection section (32), and the adjustable clearance device adjusts the height of the clearance adjustment ring (60) by tightening the first nut (70).
3. The adjustable clearance device for flutter test according to claim 2, wherein the clearance in the rotational degree of freedom of the rudder shaft is determined according to
Where h is the height of the gap adjusting ring (60), h is0In order to fix the height of the connection end of the clip (40), Deltal is the deformation amount of the clearance adjusting ring (60) in the height direction, and l is the center distance of the receiving holeThe distance of the rudder shaft in the axial direction, M is the tightening torque of the first nut (70), k is the torsional coefficient, d is the thread engineering diameter of the first connecting section (32), and P0A is a tightening force of the first nut (70), A is a cross-sectional area of the clearance adjustment ring (60), and E is an elastic modulus of the clearance adjustment ring (60).
4. The adjustable clearance device for flutter testing of claim 1, wherein said rotational stiffness spring member (20) has a first connection hole (21) and a first retention hole (22) in communication, said ejector pin (30) further comprises a second retention ring (33) and a second connection section (34), said second retention ring (33) cooperating with said first retention hole (22), said second connection section (34) disposed within said first connection hole (21), said second connection section (34) having external threads, said adjustable clearance device further comprising a second nut (80), said second nut (80) threadingly cooperating with said second connection section (34) to fixedly dispose said ejector pin (30) on said rotational stiffness spring member (20).
5. The adjustable gap device for flutter test according to claim 4, wherein the first connection hole (21) is coaxially disposed with the receiving hole of the fixing clip (40).
6. The adjustable gap device for the flutter test according to claim 4, wherein the fixing clip (40) comprises a fixing connection section (41), a first jaw (42) and a second jaw (43), the first jaw (42) and the second jaw (43) are arranged in parallel and are both connected with the fixing connection section (41), the first jaw (42) and the second jaw (43) form the open end, and the receiving hole is provided on the fixing connection section (41).
7. The adjustable gap device for flutter test according to claim 6, wherein the first fastening assembly (50) comprises a fastening screw (51) and a third nut (52), the fastening screw (51) passes through the first jaw (42) and the second jaw (43) respectively and cooperates with the third nut (52) to fixedly arrange the fixing clip (40) on a rudder shaft.
8. The adjustable clearance device for flutter testing according to claim 1, wherein the clearance adjusting ring (60) has a cross-sectional area 1 to 2 times a threaded area of the first connection section (32) of the ejector pin (30).
9. The adjustable clearance device for flutter testing of claim 1, further comprising a first shim (90), the first shim (90) disposed between a first nut (70) and the clearance adjustment ring (60).
10. The adjustable gap device for flutter testing according to claim 1, further comprising a second washer (100) and a third washer (110), the second washer (100) disposed between a second nut (80) and the rotational stiffness spring member (20), the third washer (110) disposed between a third nut (52) and the first pawl (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810899719.1A CN110160731B (en) | 2018-08-09 | 2018-08-09 | Adjustable gap device for flutter test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810899719.1A CN110160731B (en) | 2018-08-09 | 2018-08-09 | Adjustable gap device for flutter test |
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| Publication Number | Publication Date |
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| CN110160731A CN110160731A (en) | 2019-08-23 |
| CN110160731B true CN110160731B (en) | 2020-11-13 |
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| CN201810899719.1A Active CN110160731B (en) | 2018-08-09 | 2018-08-09 | Adjustable gap device for flutter test |
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| CN111982460A (en) * | 2020-08-07 | 2020-11-24 | 北京航空航天大学 | Clearance simulation device of wind tunnel model |
| CN112213070B (en) * | 2020-09-21 | 2023-03-14 | 中国航空工业集团公司沈阳飞机设计研究所 | External object hangs clearance analogue means under flutter wind tunnel test wing |
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