CN218361419U - Hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy rudder face - Google Patents
Hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy rudder face Download PDFInfo
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- CN218361419U CN218361419U CN202222971589.2U CN202222971589U CN218361419U CN 218361419 U CN218361419 U CN 218361419U CN 202222971589 U CN202222971589 U CN 202222971589U CN 218361419 U CN218361419 U CN 218361419U
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Abstract
The application relates to a hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy control surface, include: the positioning seat, the first pressing plate and the second pressing plate are arranged on the base; a first correcting groove and a second correcting groove are formed in the positioning seat, the first correcting groove and the second correcting groove are arranged oppositely, the structure of the first correcting groove and the structure of the second correcting groove are matched with the control surface, and the first correcting groove and the second correcting groove are distributed on the positioning seat in a mirror image mode; the first pressure plate and the second pressure plate are detachably mounted on the positioning seat, the first pressure plate and the first calibration groove are oppositely arranged, and the second pressure plate and the second calibration groove are oppositely arranged; the first pressure plate has been seted up the first groove of stepping down towards one side of second pressure plate, and the second pressure plate has been seted up the second groove of stepping down towards one side of first pressure plate, and the first groove of stepping down and second groove of stepping down set up relatively, and the first groove of stepping down runs through the face setting of first pressure plate, and the second groove of stepping down runs through the face of second pressure plate. The thermal expansion coefficients of the tool and the control surface can control the correction accuracy of the control surface, and the size design requirement is guaranteed.
Description
Technical Field
The application relates to the field of aerospace, in particular to a thermal correction tool for a titanium alloy control surface of a supersonic speed unmanned aerial vehicle.
Background
With the increasing importance of countries in the world on new-generation aerospace equipment, the requirements on the manufacture of supersonic unmanned aerial vehicle parts are higher and higher, and most supersonic unmanned control surfaces adopt titanium alloy parts. But in order to ensure the symmetry degree of the profile of the control surface, the thermal correction of the control surface of the unmanned aerial vehicle is needed. The existing correction tool cannot meet the manufacturing quality requirement of the titanium alloy control surface, so that how to design a thermal correction tool for carrying out thermal correction on the control surface of the unmanned aerial vehicle is a problem to be solved urgently by technical personnel in the field.
Disclosure of Invention
In view of this, this application has proposed a hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy control surface, and it can control the school type precision of control surface with the thermal expansion coefficient of frock and control surface, guarantees the size design requirement.
According to an aspect of the application, a hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy control surface is provided, includes:
the positioning seat, the first pressing plate and the second pressing plate are arranged on the base;
a first correcting groove and a second correcting groove are formed in the positioning seat, the first correcting groove and the second correcting groove are oppositely arranged, the structure of the first correcting groove and the structure of the second correcting groove are matched with the control surface, and the first correcting groove and the second correcting groove are distributed on the positioning seat in a mirror image manner;
the first pressing plate and the second pressing plate are detachably mounted on the positioning seat, the first pressing plate and the first calibration groove are oppositely arranged, and the second pressing plate and the second calibration groove are oppositely arranged;
the first pressing plate faces one side of the second pressing plate and is provided with a first yielding groove, the second pressing plate faces one side of the first pressing plate and is provided with a second yielding groove, the first yielding groove and the second yielding groove are arranged oppositely, the first yielding groove penetrates through the surface of the first pressing plate, and the second yielding groove penetrates through the surface of the second pressing plate.
In one possible implementation manner, the positioning seat is of a plate-shaped structure;
the plate surface of the positioning seat is formed by splicing a rectangle and an isosceles trapezoid, so that the plate surface of the positioning seat is of a hexagonal structure.
In a possible implementation manner, the first pressing plate is of a rectangular plate-shaped structure, a corner of the first pressing plate is provided with a chamfer, and a bevel edge generated by the first pressing plate formed after the chamfer is cut is arranged in parallel with the waist of one side of the isosceles trapezoid of the positioning seat;
the bevel edge of the first pressing plate is arranged on the same side as the waist of one side of the isosceles trapezoid of the positioning seat;
the structure of the second pressing plate is the same as that of the first pressing plate;
the first pressing plate and the second pressing plate are distributed in a mirror image mode by taking a median line in the height direction of the isosceles trapezoid of the positioning seat as an axis.
In a possible implementation manner, a first through groove is formed in the plate surface of the first pressing plate, and a second through groove is formed in the second pressing plate;
the first through groove and the first calibration groove are arranged oppositely, and the second through groove and the second calibration groove are arranged oppositely.
In a possible implementation manner, the notch of the first through groove is in a right-angled trapezoid structure, and the structure of the second through groove is matched with the structure of the first through groove.
In a possible implementation manner, the edge where the waist of the first through groove is located is arranged in parallel with the trimming edge of the first pressing plate;
the second through grooves and the first through grooves are distributed in an axial symmetry mode by taking the mirror image axes of the first pressing plate and the second pressing plate as axes.
In a possible implementation manner, a plurality of first connection holes are formed in the edge position of the plate surface of the first pressing plate, and the plurality of first connection holes are distributed at intervals along the edge position of the first pressing plate;
a plurality of second connecting holes are formed in the edge position of the plate surface of the second pressing plate, and are distributed at intervals along the edge position of the second pressing plate;
the positioning seat is provided with mounting holes, the number of the mounting holes is equal to the sum of the number of the first connecting holes and the number of the second connecting holes, the mounting holes on one side of the first pressing plate are arranged opposite to the first connecting holes, and the mounting holes on one side of the second pressing plate are arranged opposite to the second connecting holes;
the first connecting hole, the second connecting hole and the mounting hole are threaded holes.
In a possible implementation manner, the positioning seat, the first pressing plate and the second pressing plate are all made of silicon-molybdenum ball-milling cast iron.
In a possible implementation manner, the outer wall of the positioning seat, the outer wall of the first pressing plate and the outer wall of the second pressing plate are coated with high-temperature protective layers.
The hot school type frock setting of supersonic speed unmanned aerial vehicle titanium alloy rudder face is divided into positioning seat, first clamp plate and second clamp plate three, wherein, first clamp plate with clamp plate demountable installation is in one side of positioning seat. A first calibration groove and a second calibration groove are formed in the positioning seat and respectively correspond to the first pressing plate and the second pressing plate, so that two control surfaces placed in the first calibration groove and the second calibration groove are respectively pressed through the first pressing plate and the second pressing plate. The first pressure plate and the second pressure plate are respectively provided with the first abdicating groove and the second abdicating groove, so that the convex part of the control surface can be abdicating, and the conflict between the control surfaces of the first pressure plate and the second pressure plate is prevented. When the control surfaces are subjected to thermal correction, the two control surfaces are respectively placed into a first correction groove and a second correction groove, a first pressing plate and a second pressing plate are installed on the positioning seat, the two control surfaces are pressed by the first pressing plate and the second pressing plate, and then the control surfaces are integrally placed into a shaft furnace for temperature rise correction. Therefore, according to the embodiment of the application, the calibration accuracy of the control surface can be controlled by the aid of the thermal expansion coefficients of the tool and the control surface through the structure, and size design requirements are guaranteed.
Other features and aspects of the present application will become apparent from the following detailed description of exemplary embodiments, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments, features, and aspects of the application and, together with the description, serve to explain the principles of the application.
Fig. 1 shows a front view of a thermal correction tool for a titanium alloy rudder surface of a supersonic unmanned aerial vehicle according to an embodiment of the present application;
FIG. 2 shows a top view of a thermal calibration fixture for a titanium alloy control surface of a supersonic unmanned aerial vehicle according to an embodiment of the application;
fig. 3 shows a left side view of a thermal calibration fixture for a titanium alloy control surface of a supersonic unmanned aerial vehicle according to an embodiment of the present application.
Detailed Description
Various exemplary embodiments, features and aspects of the present application will be described in detail below with reference to the accompanying drawings. In the drawings, like reference numbers can indicate functionally identical or similar elements. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
It is to be understood, however, that the terms "central," "longitudinal," "lateral," "length," "width," "up," "down," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in an orientation or positional relationship indicated in the drawings which is based on the orientation or positional relationship as shown in the drawings and is for convenience in describing the present invention or in a simplified manner, rather than to indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be considered as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "plurality" means two or more unless specifically limited otherwise.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments.
Furthermore, in the following detailed description, numerous specific details are set forth in order to provide a better understanding of the present application. It will be understood by those skilled in the art that the present application may be practiced without some of these specific details. In some instances, methods, means, elements and circuits that are well known to those skilled in the art have not been described in detail so as not to obscure the present application.
Fig. 1 shows a front view of a hot sizing tool for a titanium alloy rudder surface of a supersonic unmanned aerial vehicle according to an embodiment of the present application.
Fig. 2 shows a top view of a thermal calibration fixture for a titanium alloy control surface of a supersonic unmanned aerial vehicle according to an embodiment of the present application.
Fig. 3 shows a left side view of a supersonic unmanned aerial vehicle titanium alloy control surface thermal correction tool in an embodiment of the application. As shown in fig. 1 to 3, the thermal calibration fixture for the titanium alloy control surface of the supersonic unmanned aerial vehicle comprises: the positioning seat 100 is provided with a first calibration groove 110 and a second calibration groove 120, the first calibration groove 110 and the second calibration groove 120 are oppositely arranged, the structure of the first calibration groove 110 and the structure of the second calibration groove 120 are both matched with the control surface, and the first calibration groove 110 and the second calibration groove 120 are distributed on the positioning seat 100 in a mirror image manner. The first pressing plate 200 and the second pressing plate 300 are detachably mounted on the positioning seat 100, the first pressing plate 200 is opposite to the first calibration groove 110, and the second pressing plate 300 is opposite to the second calibration groove 120. The first pressing plate 200 has a first abdicating groove 210 on one side facing the second pressing plate 300, the second pressing plate 300 has a second abdicating groove 310 on one side facing the first pressing plate 200, the first abdicating groove 210 and the second abdicating groove 310 are arranged oppositely, the first abdicating groove 210 runs through the surface of the first pressing plate 200, and the second abdicating groove 310 runs through the surface of the second pressing plate 300.
The hot school type frock setting of supersonic speed unmanned aerial vehicle titanium alloy rudder face is divided into positioning seat 100, first clamp plate 200 and 300 triplexes of second clamp plate, wherein, first clamp plate 200 with clamp plate demountable installation is in one side of positioning seat 100. A first calibration groove 110 and a second calibration groove 120 are formed in the positioning seat 100, and the first calibration groove 110 and the second calibration groove 120 respectively correspond to the first pressing plate 200 and the second pressing plate 300, so that two rudder faces placed in the first calibration groove 110 and the second calibration groove 120 are respectively pressed by the first pressing plate 200 and the second pressing plate 300. The first pressure plate 200 and the second pressure plate 300 are respectively provided with the first abdicating groove 210 and the second abdicating groove 310, so that the abdicating part of the control surface can be abdicating, and the conflict between the control surfaces of the first pressure plate 200 and the second pressure plate 300 is prevented. When the thermal correction is carried out on the control surfaces, the two control surfaces are respectively placed into the first correction groove 110 and the second correction groove 120, the first pressing plate 200 and the second pressing plate 300 are installed on the positioning seat 100, the two control surfaces are pressed by the first pressing plate 200 and the second pressing plate 300, and then the whole control surfaces are placed into the shaft furnace for temperature rise correction. Therefore, according to the embodiment of the application, the calibration accuracy of the control surface can be controlled by using the thermal expansion coefficients of the tool and the control surface through the structure, and the size design requirement is ensured.
Here, it should be noted that in one possible implementation, the positioning socket 100 may have a symmetrically distributed geometric structure, thereby further optimizing the structure of the embodiment of the present application.
In a possible implementation manner, the positioning seat 100 is of a plate-shaped structure, and the plate surface of the positioning seat 100 is formed by splicing a rectangle and an isosceles trapezoid, so that the plate surface of the positioning seat 100 is of a hexagonal structure.
Here, it should be noted that, in one possible implementation, the positioning seat 100 includes a rectangular portion and a trapezoidal portion, wherein the rectangular portion has a rectangular plate-shaped structure, and the trapezoidal portion has an isosceles trapezoidal plate-shaped structure, wherein the long bottom side of the trapezoidal portion is connected to the rectangular portion, and the length of the long bottom side of the trapezoidal portion is the same as the side length of the connected rectangular portion.
Here, it should also be noted that, in one possible implementation, the rectangular portion and the trapezoidal portion are integrally formed.
Furthermore, in a possible implementation method, the first pressing plate 200 is a rectangular plate-shaped structure, a corner of the first pressing plate 200 is provided with a chamfer, a bevel edge generated by the first pressing plate 200 formed after the chamfer is cut is arranged in parallel with a waist of one side of the isosceles trapezoid of the positioning seat 100, the bevel edge of the first pressing plate 200 is arranged on the same side as the waist of one side of the isosceles trapezoid of the positioning seat 100, and the structure of the second pressing plate 300 is the same as that of the first pressing plate 200. The first pressing plate 200 and the second pressing plate 300 are distributed in a mirror image manner with the median line in the height direction of the isosceles trapezoid of the positioning socket 100 as an axis.
Here, it should be noted that in one possible implementation, the mirror axes of the first calibration groove 110 and the second calibration groove 120 are the same axis as the mirror axes of the first pressing plate 200 and the second pressing plate 300.
In a possible implementation manner, a first through groove is formed on the plate surface of the first pressing plate 200, a second through groove is formed on the second pressing plate 300, the first through groove is opposite to the first calibration groove 110, and the second through groove is opposite to the second calibration groove 120. Thus, the weight of the embodiments of the present application is reduced.
Furthermore, in a possible implementation manner, the notch of the first through groove is in a right-angled trapezoid structure, and the structure of the second through groove is matched with the structure of the first through groove.
Here, it should be noted that in one possible implementation, the corners of the first through slots are rounded.
Further, in a possible implementation manner, the side where the waist of the first through groove is located is parallel to the cut edge of the first pressing plate 200, and the second through groove and the first through groove are symmetrically distributed by taking the mirror image axes of the first pressing plate 200 and the second pressing plate 300 as axes.
In a possible implementation manner, a plurality of first connection holes are formed at an edge position of a plate surface of the first pressing plate 200, and the plurality of first connection holes are distributed at intervals along the edge position of the first pressing plate 200. A plurality of second connection holes are formed at the edge of the plate surface of the second pressing plate 300, and the second connection holes are distributed at intervals along the edge of the second pressing plate 300. The positioning seat 100 is provided with mounting holes, the number of the mounting holes is equal to the number of the first connecting holes and the second connecting holes, the mounting hole on one side of the first pressing plate 200 is opposite to the first connecting holes, and the mounting hole on one side of the second pressing plate 300 is opposite to the second connecting holes. The first connecting hole, the second connecting hole and the mounting hole are threaded holes.
Here, it should be noted that in one possible implementation, there is one screw and one nut at each threaded hole, wherein the nuts are disposed on the sides of the first and second pressure plates 200 and 300 facing away from the positioning seat 100.
In one possible implementation, the positioning seat 100, the first pressing plate 200 and the second pressing plate 300 are made of silicon-molybdenum ball-milling cast iron.
In a possible implementation manner, the outer wall of the positioning seat 100, the outer wall of the first pressing plate 200 and the outer wall of the second pressing plate 300 are coated with high-temperature protective layers.
Having described embodiments of the present application, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.
Claims (9)
1. The utility model provides a hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy control surface which characterized in that includes:
the positioning seat, the first pressing plate and the second pressing plate are arranged on the base;
a first correcting groove and a second correcting groove are formed in the positioning seat, the first correcting groove and the second correcting groove are oppositely arranged, the structure of the first correcting groove and the structure of the second correcting groove are matched with the control surface, and the first correcting groove and the second correcting groove are distributed on the positioning seat in a mirror image manner;
the first pressing plate and the second pressing plate are detachably mounted on the positioning seat, the first pressing plate and the first calibration groove are oppositely arranged, and the second pressing plate and the second calibration groove are oppositely arranged;
the first pressing plate faces one side of the second pressing plate and is provided with a first yielding groove, the second pressing plate faces one side of the first pressing plate and is provided with a second yielding groove, the first yielding groove and the second yielding groove are arranged oppositely, the first yielding groove penetrates through the surface of the first pressing plate, and the second yielding groove penetrates through the surface of the second pressing plate.
2. The supersonic unmanned aerial vehicle titanium alloy control surface thermal correction tooling of claim 1, wherein the positioning seat is of a plate-shaped structure;
the plate surface of the positioning seat is formed by splicing a rectangle and an isosceles trapezoid, so that the plate surface of the positioning seat is of a hexagonal structure.
3. The thermal correction tooling for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 2, wherein the first pressing plate is of a rectangular plate-shaped structure, a corner of the first pressing plate is provided with a chamfer, and a bevel edge generated by the first pressing plate after the chamfer is formed is arranged in parallel with a waist of one side of an isosceles trapezoid of the positioning seat;
the bevel edge of the first pressing plate is arranged on the same side as the waist of one side of the isosceles trapezoid of the positioning seat;
the structure of the second pressing plate is the same as that of the first pressing plate;
the first pressing plate and the second pressing plate are distributed in a mirror image mode by taking a median line in the height direction of the isosceles trapezoid of the positioning seat as an axis.
4. The thermal sizing tool for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 2, wherein a first through groove is formed in a plate surface of the first pressing plate, and a second through groove is formed in the second pressing plate;
the first through groove is opposite to the first calibration groove, and the second through groove is opposite to the second calibration groove.
5. The thermal sizing tooling for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 4, wherein the notch of the first through groove is in a right trapezoid structure, and the structure of the second through groove is matched with the structure of the first through groove.
6. The thermal sizing tool for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 5, wherein an edge where the waist of the first through groove is located is arranged in parallel with the cut edge of the first pressing plate;
the second through grooves and the first through grooves are distributed in an axial symmetry mode by taking mirror image axes of the first pressing plate and the second pressing plate as axes.
7. The thermal correction tool for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 1, wherein a plurality of first connection holes are formed in the edge of the surface of the first pressing plate, and the first connection holes are distributed at intervals along the edge of the first pressing plate;
a plurality of second connecting holes are formed in the edge position of the plate surface of the second pressing plate and are distributed at intervals along the edge position of the second pressing plate;
the positioning seat is provided with mounting holes, the number of the mounting holes is equal to the sum of the number of the first connecting holes and the number of the second connecting holes, the mounting holes on one side of the first pressing plate are arranged opposite to the first connecting holes, and the mounting holes on one side of the second pressing plate are arranged opposite to the second connecting holes;
the first connecting hole, the second connecting hole and the mounting hole are threaded holes.
8. The thermal sizing tool for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 1, wherein the positioning seat, the first pressing plate and the second pressing plate are made of silicon-molybdenum ball-milled cast iron.
9. The thermal correction tooling for the titanium alloy control surface of the supersonic unmanned aerial vehicle as claimed in claim 1, wherein the outer wall of the positioning seat, the outer wall of the first pressing plate and the outer wall of the second pressing plate are coated with high temperature protection layers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222971589.2U CN218361419U (en) | 2022-11-08 | 2022-11-08 | Hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy rudder face |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222971589.2U CN218361419U (en) | 2022-11-08 | 2022-11-08 | Hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy rudder face |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218361419U true CN218361419U (en) | 2023-01-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222971589.2U Active CN218361419U (en) | 2022-11-08 | 2022-11-08 | Hot school type frock of supersonic speed unmanned aerial vehicle titanium alloy rudder face |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218361419U (en) |
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2022
- 2022-11-08 CN CN202222971589.2U patent/CN218361419U/en active Active
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