CN217805240U - Precise compensation blade of aircraft - Google Patents
Precise compensation blade of aircraft Download PDFInfo
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- CN217805240U CN217805240U CN202221396845.3U CN202221396845U CN217805240U CN 217805240 U CN217805240 U CN 217805240U CN 202221396845 U CN202221396845 U CN 202221396845U CN 217805240 U CN217805240 U CN 217805240U
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Abstract
The utility model discloses an accurate compensation blade of an aircraft, which has the technical scheme that a positioning structure is arranged for solving the problem of inconvenient positioning and locking, and an installation structure is arranged for solving the problem of inconvenient disassembly and assembly of an installation plate and a compensation blade body; the mounting plate and the adjusting assembly of the aircraft are fixedly mounted through the matching of the external bolt and the fixing bolt hole, then the positioning pin is inserted into the positioning hole and clamped in the hole preset by the external bolt, so that the positioning and locking of the mounting plate and the adjusting assembly of the aircraft are realized, the firmness of the fixed connection of the mounting plate and the adjusting assembly of the aircraft is ensured, and the practicability of the mounting plate and the adjusting assembly of the aircraft is improved; through inside to the preformed groove with compensation blade body card to make the kelly card inside to the draw-in groove, rotate the fixed screw to precession screw hole again simultaneously, later make the locking board closure shelter from the mounting groove, and then realize the firm installation between mounting panel and the compensation blade body, and then the installation of being convenient for between mounting panel and the compensation blade body is dismantled, is convenient for maintain the operation.
Description
Technical Field
The utility model relates to an aircraft accessory field, in particular to accurate compensation blade of aircraft.
Background
The aircraft is an apparatus flyer which is manufactured by human beings, can fly off the ground, flies in space and is controlled by human beings to fly in the atmosphere or in the space outside the atmosphere, and in order to realize the adjustment of the flying direction of the aircraft, an adjusting component is needed to control a rudder sheet, namely the rotating angle of a corresponding blade, so that the blade has an important precise compensation function for the adjustment of the angle;
the existing compensation blade has certain defects when in use, and the bolt and an adjusting component of an aircraft are usually adopted for installation and fixation, but the fixed bolt is inconvenient to position and lock, so that the firm connection stability of the bolt and the bolt is further improved, and therefore, the accurate compensation blade of the aircraft is provided.
SUMMERY OF THE UTILITY MODEL
In order to overcome the not enough of prior art, an object of the utility model is to provide an accurate compensation blade of aircraft, through setting up location structure, cooperation through outside bolt and fixing bolt hole, carry out fixed mounting with the adjusting part of mounting panel and aircraft, stir the locating plate afterwards, make locating piece slip compression positioning spring to suitable position department, insert the locating pin inside the locating hole again, and block the hole that the outside bolt predetermines, realize the location locking of the adjusting part of mounting panel and aircraft, guarantee the two fixed connection fastness, later at positioning spring's elasticity, make the locating piece slip drive locating plate resume the normal position, compress tightly the positive locating pin of locating hole, further improve the location locking of the adjusting part of mounting panel and aircraft, guarantee its firm stability of installation, improve its practicality, through setting up mounting structure and reserve groove, through blocking to the reserve inslot portion with the compensation blade body, and make the kelly block to the inside the draw-in groove, rotate the fixing screw to the precession screw hole inside again simultaneously, later make the locking plate closure will shelter from the mounting groove, and then realize the firm installation between mounting panel and the compensation blade body, and the installation dismantlement of being convenient for, the installation between the compensation blade body, the maintenance operation is carried out.
The above technical purpose of the present invention can be achieved by the following technical solutions:
the utility model provides an accurate compensation blade of aircraft, includes the mounting panel, the fixing bolt hole has been seted up to one side of mounting panel, the positive one side swing joint of mounting panel has location structure, the reserve tank has been seted up to the opposite side of mounting panel, one side swing joint of reserve tank has extended to the compensation blade body, the inside swing joint of mounting panel of reserve tank top and below has mounting structure.
The locating structure comprises a locating hole, the locating hole is formed in the front side of the mounting plate, the locating groove is formed in the front side of the mounting plate on one side of the locating hole, a locating spring is fixedly connected to the inner side wall of the locating groove, a locating block is fixedly connected to one side of the locating spring, and the locating plate extends to the outside of the mounting plate.
Through the cooperation of outside bolt and fixing bolt hole, carry out fixed mounting with the adjusting part of mounting panel and aircraft, later stir the locating plate, make the locating piece slide in the constant head tank inside and compress positioning spring to suitable position department, insert the locating pin inside the locating hole again, and block the hole of outside bolt presetting, realize the location locking of the adjusting part of mounting panel and aircraft, guarantee the two fixed connection fastness, later elasticity at positioning spring, make the locating piece slide and drive the locating plate and resume the normal position, compress tightly the positive locating pin of locating hole, further improve the location locking of the adjusting part of mounting panel and aircraft, guarantee its firm stability of installation.
Furthermore, the shape of the positioning hole top view is convex, and one end of the positioning hole is communicated with the inside of the fixing bolt hole.
Through setting up protruding type locating hole, the block of inserting of locating pin of being convenient for.
Furthermore, a welding integrated structure is formed between one side of the positioning plate and the front surface of the positioning block, and the positioning plate forms a sliding structure through the positioning block and the inside of the positioning groove.
Through the sliding of the positioning block in the positioning groove, the positioning plate can move more stably.
Furthermore, a limiting groove is formed in one side of the front face of the positioning groove, and the length of the limiting groove is larger than the diameter of the cross section of the positioning hole.
Through setting up longer spacing groove for the locating piece has enough removal space, makes the locating plate can remove to the separation with the locating hole completely.
Further, mounting structure includes the mounting groove, the top and the bottom at mounting panel one side are seted up to the mounting groove, and one side of mounting groove is through hinge fixedly connected with locking plate, the both sides swing joint of mounting groove inner wall has the fixed screw, and the top and the bottom of compensating blade body one side set up with fixed screw matched with screw hole, the draw-in groove has been seted up to one side of compensating blade body, and reserve groove inside wall fixedly connected with and draw-in groove matched with kelly.
Through inside to the preformed groove with compensation blade body card, and make the kelly card inside to the draw-in groove, rotate the fixed screw to precession screw hole again simultaneously, later make the locking plate closure shelter from the mounting groove, and then realize the firm installation between mounting panel and the compensation blade body, and during the dismantlement, rotating fixed screw breaks away from to inside with the screw hole completely, later pulling compensation blade body, realize dismantling the action, and then the installation between the mounting panel of being convenient for and the compensation blade body is dismantled, be convenient for maintain the operation.
Furthermore, an interference clamping structure is formed between the clamping rod and the inside of the clamping groove, and the clamping rod and the clamping groove are rectangular.
Through the interference block of rectangle kelly and draw-in groove, guarantee the installation stability of mounting panel and compensation blade body.
Furthermore, the quantity of screw hole and set screw is four, and screw hole and set screw are about the horizontal axis symmetric distribution in preformed groove.
Through the cooperation of a plurality of screw holes of symmetry and fixed screw, realize that the multiple spot installation between mounting panel and the compensation blade body is fixed, guarantee the firm stability of installation.
Furthermore, the shape of the cross section of the preformed groove is C-shaped, and a clamping structure is formed between the preformed groove and one side of the compensation blade body.
Through the block of C type preformed groove and compensation blade body one side, realize that the preliminary installation of the two is fixed.
To sum up, the utility model discloses following beneficial effect has:
1. the mounting plate and the adjusting component of the aircraft are fixedly mounted through the matching of an external bolt and a fixing bolt hole, then the positioning plate is shifted, the positioning block is made to slide and compress the positioning spring to a proper position, then the positioning pin is inserted into the positioning hole and clamped in a hole preset by the external bolt, the positioning and locking of the mounting plate and the adjusting component of the aircraft are realized, the fixing and connecting firmness of the mounting plate and the adjusting component of the aircraft are ensured, then the positioning block is made to slide to drive the positioning plate to recover to the original position under the elastic force of the positioning spring, the positioning pin in front of the positioning hole is compressed, the positioning and locking of the mounting plate and the adjusting component of the aircraft are further improved, the mounting firmness and stability are ensured, the practicability of the mounting plate and the adjusting component of the aircraft are improved, and the problem that the fixing bolt is inconvenient to position and lock is solved;
2. through the mounting groove that sets up, the kelly, the screw hole, the fixed screw, draw-in groove and reservation groove, through with compensating blade body card to reservation inslot portion, and make the kelly card inside the draw-in groove, rotate fixed screw to precession screw hole inside simultaneously again, later make the locking plate closure shelter from the mounting groove, and then realize the firm installation between mounting panel and the compensating blade body, and then the installation of being convenient for between mounting panel and the compensating blade body is dismantled, be convenient for maintain the operation, improve its practicality, thereby the problem of inconvenient installation dismantlement has been solved.
Drawings
Fig. 1 is a schematic perspective view of the present invention;
fig. 2 is a schematic side view of the present invention;
fig. 3 is a schematic front view of the present invention;
FIG. 4 is a schematic view of the mounting plate according to the present invention showing a partially overlooked enlarged structure;
fig. 5 is a schematic diagram of the local overlooking enlarged structure at the preformed groove of the present invention.
In the figure: 1. a mounting structure; 101. mounting grooves; 102. a clamping rod; 103. a screw hole; 104. fixing screws; 105. a locking plate; 106. a card slot; 2. fixing bolt holes; 3. a positioning structure; 301. positioning holes; 302. positioning a plate; 303. a positioning spring; 304. a limiting groove; 305. positioning a groove; 306. positioning blocks; 4. mounting a plate; 5. a compensating blade body; 6. and (5) reserving a groove.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
In which like parts are designated by like reference numerals. It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "bottom" and "top," "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.
Referring to fig. 1, do the utility model discloses in the preferred embodiment an accurate compensation blade of aircraft, including mounting panel 4, fixing bolt hole 2 has been seted up to one side of mounting panel 4, and the positive one side swing joint of mounting panel 4 has location structure 3, and preformed groove 6 has been seted up to the opposite side of mounting panel 4, and one side swing joint of preformed groove 6 has and extends to compensation blade body 5, and the inside swing joint of mounting panel 4 of preformed groove 6 top and below has mounting structure 1.
Referring to fig. 1, 3 and 4, the positioning structure 3 includes a positioning hole 301, the positioning hole 301 is opened on one side of the front surface of the mounting plate 4, a positioning groove 305 is opened on the front surface of the mounting plate 4 on one side of the positioning hole 301, a positioning spring 303 is fixedly connected to the inner side wall of the positioning groove 305, a positioning block 306 is fixedly connected to one side of the positioning spring 303, and a positioning plate 302 extending to the outside of the mounting plate 4 is fixedly connected to the front surface of the positioning block 306.
Through the cooperation of outside bolt and fixing bolt hole 2, carry out fixed mounting with the adjusting part of mounting panel 4 and aircraft, later stir locating plate 302, make locating piece 306 slide in locating groove 305 and compress positioning spring 303 to suitable position department, insert the locating pin inside locating hole 301 again, and block the hole of predetermineeing to the outside bolt, realize mounting panel 4 and aircraft's adjusting part's location locking, guarantee the two fixed connection fastness, later at the elasticity of positioning spring 303, make locating piece 306 slide and drive locating plate 302 and resume the normal position, compress tightly the positive locating pin of locating hole 301, further improve mounting panel 4 and aircraft's adjusting part's location locking, guarantee its firm stability of installation.
Referring to fig. 1, 3, and 4, the positioning hole 301 has a convex shape in plan view, and one end of the positioning hole 301 communicates with the inside of the fixing bolt hole 2.
By providing the convex positioning hole 301, the positioning pin can be inserted and engaged conveniently.
Referring to fig. 1, 3 and 4, one side of the positioning plate 302 and the front surface of the positioning block 306 are welded together, and the positioning plate 302 forms a sliding structure through the positioning block 306 and the inside of the positioning slot 305.
The positioning block 306 slides inside the positioning slot 305, so that the positioning plate 302 moves more stably.
Referring to fig. 1, 3 and 4, a limiting groove 304 is formed on one side of the front surface of the positioning groove 305, and the length of the limiting groove 304 is greater than the diameter of the cross section of the positioning hole 301.
By providing the longer limiting groove 304, the positioning block 306 has enough moving space, so that the positioning plate 302 can be moved to be completely separated from the positioning hole 301.
Referring to fig. 1, fig. 3 and fig. 5, the mounting structure 1 includes a mounting groove 101, the mounting groove 101 is provided at the top end and the bottom end of one side of the mounting plate 4, and one side of the mounting groove 101 is provided with a locking plate 105 through a hinge fixedly connected with, both sides of the inner wall of the mounting groove 101 are movably connected with a fixing screw 104, and the top end and the bottom end of one side of the compensating blade body 5 are provided with a screw hole 103 matched with the fixing screw 104, one side of the compensating blade body 5 is provided with a clamping groove 106, and the inner side wall of the reserved groove 6 is fixedly connected with a clamping rod 102 matched with the clamping groove 106.
Through inside to reserve groove 6 with compensation blade body 5 card, and make kelly 102 card inside to draw-in groove 106, rotate fixed screw 104 again simultaneously to precession screw hole 103 inside, later make locking plate 105 closed shelter from mounting groove 101, and then realize the firm installation between mounting panel 4 and the compensation blade body 5, and during the dismantlement, rotating fixed screw 104 breaks away from to inside with screw hole 103 completely, later pulling compensation blade body 5, realize dismantling the action, and then be convenient for the installation between mounting panel 4 and the compensation blade body 5 is dismantled, be convenient for maintain the operation.
Referring to fig. 3 and 5, an interference engagement structure is formed between the latch lever 102 and the interior of the latch slot 106, and the latch lever 102 and the latch slot 106 are rectangular.
The rectangular clamping rod 102 is in interference fit with the clamping groove 106, so that the installation stability of the mounting plate 4 and the compensation blade body 5 is ensured.
Referring to fig. 3 and 5, the number of the screw holes 103 and the fixing screws 104 is four, and the screw holes 103 and the fixing screws 104 are symmetrically distributed about a transverse central axis of the prepared groove 6.
Through the cooperation of a plurality of symmetrical screw holes 103 and fixed screw 104, realize that the multiple spot installation between mounting panel 4 and the compensation blade body 5 is fixed, guarantee the firm stability of installation.
Referring to fig. 3 and 5, the cross section of the preformed groove 6 is C-shaped, and a clamping structure is formed between the preformed groove 6 and one side of the compensating blade body 5.
The C-shaped preformed groove 6 and the compensation blade body 5 are clamped at one side, so that the initial installation and fixation of the C-shaped preformed groove and the compensation blade body are realized.
The specific implementation process comprises the following steps: through inside to reserve groove 6 with compensation blade body 5 card, and make kelly 102 card inside to draw-in groove 106, rotate fixed screw 104 again simultaneously to precession screw hole 103 inside, later make locking plate 105 closed shelter from mounting groove 101, and then realize the firm installation between mounting panel 4 and the compensation blade body 5, and during the dismantlement, rotating fixed screw 104 breaks away from to inside with screw hole 103 completely, later pulling compensation blade body 5, realize dismantling the action, and then be convenient for the installation between mounting panel 4 and the compensation blade body 5 is dismantled, be convenient for maintain the operation.
Afterwards, through the cooperation of external bolt and fixing bolt hole 2, carry out fixed mounting with the adjusting part of mounting panel 4 and aircraft, later stir locating plate 302, make locating piece 306 slide in constant head tank 305 and compress positioning spring 303 to suitable position department, insert the locating pin inside locating hole 301 again, and block the hole of predetermineeing to the external bolt, realize mounting panel 4 and aircraft's adjusting part's location locking, guarantee the two fixed connection fastness, later at the elasticity of positioning spring 303, make locating piece 306 slide and drive locating plate 302 and resume the normal position, compress tightly the positive locating pin of locating hole 301, further improve mounting panel 4 and aircraft's adjusting part's location locking, guarantee its firm stability of installation.
The foregoing shows and describes the basic principles and principal features of the invention, together with the advantages thereof. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments, and the above embodiments and descriptions are only illustrative of the principles of the present invention, and that various changes and modifications may be made without departing from the spirit and scope of the present invention, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. An accurate compensation blade of an aircraft, characterized in that: the mounting structure comprises a mounting plate (4), wherein a fixing bolt hole (2) is formed in one side of the mounting plate (4), a positioning structure (3) is movably connected to one front side of the mounting plate (4), a preformed groove (6) is formed in the other side of the mounting plate (4), one side of the preformed groove (6) is movably connected with a compensation blade body (5) in a extending mode, and mounting structures (1) are movably connected to the inner portions of the mounting plate (4) above and below the preformed groove (6);
location structure (3) are including locating hole (301), set up in the positive one side of mounting panel (4) locating hole (301), locating groove (305) have openly been seted up in mounting panel (4) of locating hole (301) one side, the inside wall fixedly connected with positioning spring (303) of locating groove (305), one side fixedly connected with locating piece (306) of positioning spring (303), locating piece (306) openly fixedly connected with extends to outside locating plate (302) of mounting panel (4).
2. The precision compensated blade for an aircraft of claim 1, wherein: the positioning hole (301) is convex in shape in plan view, and one end of the positioning hole (301) is communicated with the inside of the fixing bolt hole (2).
3. The precision compensating blade for an aircraft of claim 1, wherein: one side of the positioning plate (302) and the front surface of the positioning block (306) are in a welding integrated structure, and the positioning plate (302) forms a sliding structure through the positioning block (306) and the positioning groove (305).
4. The precision compensated blade for an aircraft of claim 1, wherein: a limiting groove (304) is formed in one side of the front face of the positioning groove (305), and the length of the limiting groove (304) is larger than the diameter of the cross section of the positioning hole (301).
5. The precision compensated blade for an aircraft of claim 1, wherein: mounting structure (1) includes mounting groove (101), the top and the bottom in mounting panel (4) one side are seted up to mounting groove (101), and one side of mounting groove (101) is through hinge fixedly connected with locking plate (105), the both sides swing joint of mounting groove (101) inner wall has set screw (104), and the top and the bottom of compensating blade body (5) one side set up with set screw (104) matched with screw hole (103), draw-in groove (106) have been seted up to one side of compensating blade body (5), and reserve groove (6) inside wall fixedly connected with and draw-in groove (106) matched with kelly (102).
6. The precision compensated blade for an aircraft of claim 5, wherein: an interference clamping structure is formed between the clamping rod (102) and the inside of the clamping groove (106), and the clamping rod (102) and the clamping groove (106) are rectangular.
7. The precision compensated blade for an aircraft of claim 5, wherein: the number of the screw holes (103) and the number of the fixing screws (104) are four, and the screw holes (103) and the fixing screws (104) are symmetrically distributed around the transverse central axis of the preformed groove (6).
8. The precision compensated blade for an aircraft of claim 1, wherein: the cross section of the preformed groove (6) is C-shaped, and a clamping structure is formed between the preformed groove (6) and one side of the compensation blade body (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221396845.3U CN217805240U (en) | 2022-06-06 | 2022-06-06 | Precise compensation blade of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221396845.3U CN217805240U (en) | 2022-06-06 | 2022-06-06 | Precise compensation blade of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217805240U true CN217805240U (en) | 2022-11-15 |
Family
ID=83989998
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221396845.3U Active CN217805240U (en) | 2022-06-06 | 2022-06-06 | Precise compensation blade of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217805240U (en) |
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2022
- 2022-06-06 CN CN202221396845.3U patent/CN217805240U/en active Active
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