CN204688413U - The left-right asymmetry bulb folder of helicopter tilting frame - Google Patents
The left-right asymmetry bulb folder of helicopter tilting frame Download PDFInfo
- Publication number
- CN204688413U CN204688413U CN201520288004.4U CN201520288004U CN204688413U CN 204688413 U CN204688413 U CN 204688413U CN 201520288004 U CN201520288004 U CN 201520288004U CN 204688413 U CN204688413 U CN 204688413U
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- China
- Prior art keywords
- tilting frame
- bulb
- rotor
- folder
- pull bar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000001105 regulatory effect Effects 0.000 claims abstract description 4
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 4
- 230000000007 visual effect Effects 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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Abstract
The left-right asymmetry bulb folder of a kind of helicopter tilting frame, comprise rotor axle, rotor blade, rotor folder and tilting frame, described tilting frame comprises dish and tilting frame lower wall on the tilting frame that be arranged in parallel, tilting frame coils two ends and be vertically connected with dribbling head and rotor distance pull bar on tilting frame, rotor connects rotor folder bulb apart from the pull bar other end, described tilting frame lower wall two ends respectively connect a bulb folder, the bulb that described bulb folder comprises adjustment screw pull bar and is attached thereto, be characterized in, described adjustment screw pull bar adjustable length, its length is regulated to make the bulb at two ends press from both sides into left and right length dissymmetrical structure, described rotor axle and tilting frame become rotor axle and tilting frame produces an angle being greater than 90 ° from original 90 °, described angle is the change of 0-10 °.The beneficial effects of the utility model are, can allow helicopter hover and flight time keep the vertical and horizontal degree of its fuselage, be beneficial to the accurate location of aviator to front T captions and visible objects, ensure flight safety.
Description
Technical field
The utility model relates to a kind of bulb folder, specifically, relates to the left-right asymmetry bulb folder of a kind of helicopter tilting frame.
Background technology
At present, when hovering and fly, we can find the phenomenon of fuselage to lopsidedness of helicopter to existing helicopter, at this moment aviator will feel that front T captions and visible objects have a leaning angle parallax, and this will make aviator create certain visual angle deviation to the location of visual object and locking.
Summary of the invention
The utility model overcomes the deficiency of above-mentioned prior art, and its object is to provides a kind of helicopter tilting frame left-right asymmetry bulb folder.
Above-mentioned purpose of the present utility model is achieved through the following technical solutions.
The left-right asymmetry bulb folder of a kind of helicopter tilting frame, comprise rotor axle, rotor blade, rotor folder and tilting frame, described tilting frame comprises dish and tilting frame lower wall on the tilting frame that be arranged in parallel, tilting frame coils two ends and be vertically connected with dribbling head and rotor distance pull bar on tilting frame, rotor connects rotor folder bulb apart from the pull bar other end, described tilting frame lower wall two ends respectively connect a bulb folder, the bulb that described bulb folder comprises adjustment screw pull bar and is attached thereto, it is characterized in that, described adjustment screw pull bar adjustable length, its length is regulated to make the bulb at two ends press from both sides into left and right length dissymmetrical structure, described rotor axle and tilting frame become rotor axle and tilting frame produces an angle being greater than 90 ° from original 90 °, described angle is the change of 0-10 °.Preferably, described angle is the change of 5 °.
Lengthen right side on the left of the adjustment screw pull bar of described tilting frame lower wall to shorten, make two adjusting levers be the right short structure of left length.Lengthen left side on the right side of the adjustment screw pull bar of described tilting frame lower wall to shorten, make two adjusting levers be the left short structure of right length.
The bulb of original tilting frame folder is connected on the left of adjusting lever and lengthens, right side is shortened, the previous level position of such tilting frame will become to tilt to the right, like this when the jociey stick of helicopter is in former midway location, the rotor axle of helicopter will have certain inclination angle to the right, and such helicopter its fuselage when hovering and fly would not tilt.
The beneficial effects of the utility model are, helicopter can be allowed when hovering and fly to keep the vertical and horizontal degree of its fuselage, be beneficial to the accurate location of aviator to front T captions and visible objects, visual angle deviation all there will be no to the visible objects in arbitrary orientation simultaneously.
Accompanying drawing explanation
Fig. 1 is the structural representation that the utility model tilting frame bulb presss from both sides when not changing a social system.
Fig. 2 be Fig. 1 structure helicopter hover and flight time fuselage to lopsidedness constitution diagram.
Fig. 3 be the utility model tilting frame bulb folder change system into left and right length asymmetric time structural representation.
Fig. 4 is that helicopter fuselage when hovering and fly of Fig. 3 structure keeps plumbness figure.
Nomenclature in figure: 1, rotor axle; 2, screw pull bar is adjusted; 3, bulb; 4, blade folder rotating shaft; 5, rotor blade; 6, rotor folder; 7, propeller hub; 8, propeller hub axle; 9, tilting frame coils; 10, tilting frame lower wall; 11, rotor folder bulb; 12, rotor is apart from pull bar; 13, dribbling head on tilting frame; 14, pitch control bulb.
Detailed description of the invention
Introduce the utility model specific embodiment in detail below in conjunction with accompanying drawing, for the ease of introducing, the preferred rotor axle 1 of legend is 5 ° with horizontal direction angle and is specifically described.
As shown in Figure 1, Figure 3, the utility model comprises rotor axle 1, rotor blade 5, rotor folder 6 and tilting frame, described tilting frame comprises dish 9 and tilting frame lower wall 10 on the tilting frame that be arranged in parallel, tilting frame coils 9 two ends and to be vertically connected with on tilting frame dribbling 13 and rotor apart from pull bar 12, rotor connects rotor folder bulb 11 apart from pull bar 12 other end, described tilting frame lower wall 10 two ends respectively connect a bulb folder, the bulb 3 that described bulb folder comprises adjustment screw pull bar 2 and is attached thereto.
As shown in Figure 1 and Figure 2, bulb folder in the utility model tilting frame left and right is when without the transformation of the way, namely left and right length is equal, and described rotor axle 1 is all in horizontal direction with tilting frame, and fuselage can to lopsidedness in hovering and when flying for helicopter, cause aviator to produce vision deviation, affect flight safety.
As shown in Figure 3, Figure 4, described adjustment screw pull bar 2 adjustable length, its length is regulated to make the bulb at two ends press from both sides into left and right length dissymmetrical structure, described rotor axle 1 becomes rotor axle 1 with tilting frame from original 90 ° and produces an angle being greater than 90 ° with tilting frame, and described angle is the change of 0-10 °.Preferably, described angle is the change of 5 °, and such helicopter its fuselage when hovering and fly can keep plumbness,
The above; be only the utility model preferably detailed description of the invention; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; be equal to according to the technical solution of the utility model and design thereof and replace or change, all should be encompassed within protection domain of the present utility model.
Claims (4)
1. the left-right asymmetry bulb folder of helicopter tilting frame, comprise rotor axle (1), rotor blade (5), rotor folder (6) and tilting frame, described tilting frame comprises dish (9) and tilting frame lower wall (10) on the tilting frame that be arranged in parallel, tilting frame coils (9) two ends and be vertically connected with dribbling head (13) and rotor distance pull bar (12) on tilting frame, rotor connects rotor folder bulb (11) apart from pull bar (12) other end, described tilting frame lower wall (10) two ends respectively connect a bulb folder, the bulb (3) that described bulb folder comprises adjustment screw pull bar (2) and is attached thereto, it is characterized in that, described adjustment screw pull bar (2) adjustable length, its length is regulated to make the bulb at two ends press from both sides into left and right length dissymmetrical structure, described rotor axle (1) becomes rotor axle (1) with tilting frame from original 90 ° and produces an angle being greater than 90 ° with tilting frame, described angle is the change of 0-10 °.
2. bulb folder according to claim 1, it is characterized in that, described angle is the change of 5 °.
3. bulb folder according to claim 1 and 2, is characterized in that, adjustment screw pull bar (2) left side of described tilting frame lower wall (10) lengthens right side and shortens, and makes two adjusting levers be the right short structure of left length.
4. bulb folder according to claim 1 and 2, is characterized in that, adjustment screw pull bar (2) right side of described tilting frame lower wall (10) lengthens left side and shortens, and makes two adjusting levers be the left short structure of right length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520288004.4U CN204688413U (en) | 2015-05-01 | 2015-05-01 | The left-right asymmetry bulb folder of helicopter tilting frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520288004.4U CN204688413U (en) | 2015-05-01 | 2015-05-01 | The left-right asymmetry bulb folder of helicopter tilting frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204688413U true CN204688413U (en) | 2015-10-07 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520288004.4U Expired - Fee Related CN204688413U (en) | 2015-05-01 | 2015-05-01 | The left-right asymmetry bulb folder of helicopter tilting frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204688413U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923156A (en) * | 2016-06-15 | 2016-09-07 | 江富余 | V-shaped rotor wings of helicopter |
| CN106904055A (en) * | 2017-04-26 | 2017-06-30 | 河南三和航空工业有限公司 | A kind of rotorcycle |
| CN108502157A (en) * | 2018-06-05 | 2018-09-07 | 嘉兴中创航空技术有限公司 | A kind of DCB Specimen unmanned plane of absolute construction |
-
2015
- 2015-05-01 CN CN201520288004.4U patent/CN204688413U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923156A (en) * | 2016-06-15 | 2016-09-07 | 江富余 | V-shaped rotor wings of helicopter |
| CN105923156B (en) * | 2016-06-15 | 2018-05-01 | 江富余 | Helicopter V-type rotor driver |
| CN106904055A (en) * | 2017-04-26 | 2017-06-30 | 河南三和航空工业有限公司 | A kind of rotorcycle |
| WO2018196041A1 (en) * | 2017-04-26 | 2018-11-01 | 河南三和航空工业有限公司 | Hoverbike |
| CN108502157A (en) * | 2018-06-05 | 2018-09-07 | 嘉兴中创航空技术有限公司 | A kind of DCB Specimen unmanned plane of absolute construction |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151007 |