CN205022854U - Deformable compound aircraft - Google Patents
Deformable compound aircraft Download PDFInfo
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- CN205022854U CN205022854U CN201520664163.XU CN201520664163U CN205022854U CN 205022854 U CN205022854 U CN 205022854U CN 201520664163 U CN201520664163 U CN 201520664163U CN 205022854 U CN205022854 U CN 205022854U
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- screw propeller
- electrical motor
- rotor bar
- wing
- bending
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Abstract
The utility model discloses a deformable compound aircraft, including aircraft nose, fuselage, fin, wing, the place ahead of aircraft nose is equipped with the propulsion screw, rotor mast passes through the connecting piece with the wing and is connected, the streamline curved surface is described for both sides towards the ridge of middle hunch -up to rotor mast's up end, and rotor mast is telescopic rod structure. The utility model discloses the heligyro VTOL not only has, the characteristics of the restriction in place of not taken off and land, fixed -wing aircraft's flying speed and lasting duration also have, bending device makes rotor mast can bend, overturn and rotate to make each screw redirecting and angle wantonly under total controller's control, it is more nimble, convenient to fly.
Description
Technical field
The utility model relates to a kind of aircraft, particularly relates to a kind of deformable composite aircraft.
Background technology
Fixed wing aircraft and heligyro is had at the aircraft that aviation field is common; Fixed wing aircraft mainly produces lift balance airplane weight by wing, and its flying speed is fast, voyage and the cruise time long, but landing distance, require special quality runway, landing is subject to the restriction of geographical environment, thus applies and receives restriction.Heligyro can in narrow and small place vertical takeoff and landing, the restriction of Bu Shou landing site, but rotor efficiency can not show a candle to the wing of fixed wing aircraft, and power consumption is large, and flight resistance is large, thus affects flying speed and cruise duration; And inconvenient when turning to the autogiro of fixed-wing, dumb, can not change of flight track fast.
Utility model content
The purpose of this utility model is to provide a kind of deformable composite aircraft, solves when fixed wing aircraft exists by landing site's restriction and heligyro the defect and flight that flying speed is slow, cruise duration is short and turns to dumb, inconvenient problem.
For achieving the above object, the deformable composite aircraft of one designed by the utility model, comprise head, fuselage and be located at described afterbody empennage and be located at described fuselage below alighting gear and be located at the wing of described fuselage both sides, the front of described head is provided with propelling screws, and the inside of described head or fuselage is provided with master controller; The end of two described wings is respectively equipped with the rotor bar of two ends away from described wing and/or described fuselage; Described rotor bar is connected by attaching parts with described wing; The upper surface of described rotor bar is the ridge shape streamline curved surface arched upward towards centre in both sides, and described rotor bar is Telescopic rod structure; Two described rotor bar described attaching partss be arranged on each rotor bar are divided into left front rotor bar, left back rotor bar, right front rotor bar and right back rotor bar; The end of described left front rotor bar is provided with left front electrical motor and is located at the left front screw propeller on the axle of described left front electrical motor, and the end of described left back rotor bar is provided with left back electrical motor and is located at the left back screw propeller on the axle of described left back electrical motor; The end end of described right front rotor bar is provided with right front electrical motor and is located at the right front screw propeller on the axle of described right front electrical motor, and the end of described right back rotor bar is provided with right back electrical motor and is located at the right back screw propeller on the axle of described right back electrical motor.
Further, described left front screw propeller is identical with the rotation direction of described right back screw propeller, the direction of rotation of described left front screw propeller and described left back screw propeller, right front screw propeller; Described left back screw propeller is identical with the rotation direction of described right front screw propeller.
The beneficial effect of above-mentioned further scheme is: improve the flight stability of aircraft under rotor flying pattern, wind resistance is strong.
Further, described left front rotor bar is provided with for described left front screw propeller is rotated to the left front apparatus for bending parallel with described propelling screws between described wing with described left front electrical motor; Described left back rotor bar is provided with for described left back screw propeller is rotated to the left back apparatus for bending parallel with described propelling screws between described wing with described left back electrical motor; Described right front rotor bar is provided with for described right front screw propeller is rotated to the right front apparatus for bending parallel with described propelling screws between described wing with described right front electrical motor; Described right back rotor bar is provided with for described right back screw propeller is rotated to the right back apparatus for bending parallel with described propelling screws between described wing with described right back electrical motor.
The beneficial effect of above-mentioned further scheme is: rotate to parallel with propelling screws by left front, left back, right front, right back apparatus for bending by left front, left back, right front, right back screw propeller, now left front, left back, right front, right back screw propeller and propelling screws co-operation, flying speed when making aircraft under fixed-wing offline mode is faster.
Further, the distance between described left front apparatus for bending and described left front electrical motor equals the distance between described right front apparatus for bending and described right front electrical motor; Distance between described left back apparatus for bending and described left back electrical motor equals the distance between described right back apparatus for bending and described right back electrical motor.
The beneficial effect of above-mentioned further scheme is: ensure the flight stability of aircraft under fixed-wing offline mode.
Further, the inside of described left front screw propeller, left back screw propeller, right front screw propeller, right back screw propeller is provided with reinforced rib.
The beneficial effect of above-mentioned further scheme is: prevent screw propeller in flight course from being fractureed, and in the process particularly mutually changed in rotor flying pattern and fixed-wing offline mode, the torsion that left front screw propeller, right front screw propeller are subject to increases.
Further, the line between described left front screw propeller with described right back screw propeller and the intersection point of line between described left back screw propeller with described right front screw propeller overlap with the center of gravity of aircraft.
The beneficial effects of the utility model are: not only have heligyro vertical takeoff and landing, not by the feature of the restriction of landing site, also have the flying speed of fixed wing aircraft and lasting flying power; Apparatus for bending makes the bending of rotor bar energy, upset and rotation, thus makes each screw propeller can change arbitrarily direction and angle under the control of master controller, and flight more flexibly, conveniently.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model under fixed-wing offline mode.
Fig. 2 is the structural representation of the utility model under rotor flying pattern.
Fig. 3 is the structural representation of rotor bar of the present utility model.
Fig. 4 is the cross section view of rotor bar of the present utility model.
In figure 1, head; 2, fuselage; 3, empennage; 4, wing; 5, propelling screws; 6, rotor bar; 61, left front rotor bar; 611, left front electrical motor; 612, left front screw propeller; 613, left front apparatus for bending; 62, left back rotor bar; 621, left back electrical motor; 622, left back screw propeller; 623, left back apparatus for bending; 63, right front rotor bar; 631, right front electrical motor; 632, right front screw propeller; 633, right front apparatus for bending; 64, right back rotor bar; 641, right back electrical motor; 642, right back screw propeller; 643, right back apparatus for bending.
Detailed description of the invention
Be described principle of the present utility model and feature below in conjunction with accompanying drawing, example, only for explaining the utility model, is not intended to limit scope of the present utility model.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, a kind of deformable composite aircraft, comprise head 1, fuselage 2 and be located at fuselage 2 afterbody empennage 3 and be located at fuselage 2 below alighting gear and be located at the wing 4 of fuselage 2 both sides, the front of head 1 is provided with propelling screws 5, and the inside of head 1 or fuselage 2 is provided with master controller; The end of two wings 4 is respectively equipped with the rotor bar 6 of two ends away from wing 4 and/or fuselage 2; Rotor bar 6 is connected by attaching parts with wing 4; The upper surface of rotor bar 6 is the ridge shape streamline curved surface arched upward towards centre in both sides, and rotor bar 6 is Telescopic rod structure; Two rotor bar 6 attaching partss be arranged on every root rotor bar 6 are divided into left front rotor bar 61, left back rotor bar 62, right front rotor bar 63 and right back rotor bar 64; The end of left front rotor bar 61 is provided with left front electrical motor 611 and the left front screw propeller 612 be located on the axle of left front electrical motor 611, and the end of left back rotor bar 62 is provided with left back electrical motor 621 and the left back screw propeller 622 be located on the axle of left back electrical motor 621; The end end of right front rotor bar 63 is provided with right front electrical motor 631 and the right front screw propeller 632 be located on the axle of right front electrical motor 631, and the end of right back rotor bar 64 is provided with right back electrical motor 641 and the right back screw propeller 642 be located on the axle of right back electrical motor 641.
Left front screw propeller 612 is identical with the rotation direction of right back screw propeller 642, the direction of rotation of left front screw propeller 612 and left back screw propeller 622, right front screw propeller 632; Left back screw propeller 622 is identical with the rotation direction of right front screw propeller 632.
Left front rotor bar 61 is provided with for left front screw propeller 612 is rotated to the left front apparatus for bending 613 parallel with propelling screws 5 between wing 4 with left front electrical motor 611; Left back rotor bar 62 is provided with for left back screw propeller 622 is rotated to the left back apparatus for bending 623 parallel with propelling screws 5 between wing 4 with left back electrical motor 621; Right front rotor bar 63 is provided with for right front screw propeller 632 is rotated to the right front apparatus for bending 633 parallel with propelling screws 5 between wing 4 with right front electrical motor 631; Right back rotor bar 64 is provided with for right back screw propeller 642 is rotated to the right back apparatus for bending 643 parallel with propelling screws 5 between wing 4 with right back electrical motor 641; Left front apparatus for bending 613, left back apparatus for bending 623, right front apparatus for bending 633, right back apparatus for bending 643 are connected with master controller.
Distance between left front apparatus for bending 613 and left front electrical motor 611 equals the distance between right front apparatus for bending 633 and right front electrical motor 631; Distance between left back apparatus for bending 623 and left back electrical motor 621 equals the distance between right back apparatus for bending 643 and right back electrical motor 641.
The inside of left front screw propeller 612, left back screw propeller 622, right front screw propeller 632, right back screw propeller 642 is provided with reinforced rib.Line between left front screw propeller 612 with right back screw propeller 642 and the intersection point of line between left back screw propeller 622 with right front screw propeller 632 overlap with the center of gravity of aircraft.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (6)
1. a deformable composite aircraft, comprise head (1), fuselage (2) and be located at described fuselage (2) afterbody empennage (3) and be located at described fuselage (2) below alighting gear and be located at the wing (4) of described fuselage (2) both sides, it is characterized in that: the front of described head (1) is provided with propelling screws (5), and the inside of described head (1) or fuselage (2) is provided with master controller; The end of two described wings (4) is respectively equipped with the rotor bar (6) of two ends away from described wing (4) and/or described fuselage (2); Described rotor bar (6) is connected by attaching parts with described wing (4); The upper surface of described rotor bar (6) is the ridge shape streamline curved surface arched upward towards centre in both sides, and described rotor bar (6) is Telescopic rod structure; The described attaching parts that two described rotor bars (6) are arranged on each described rotor bar (6) is divided into left front rotor bar (61), left back rotor bar (62), right front rotor bar (63) and right back rotor bar (64); The end of described left front rotor bar (61) is provided with left front electrical motor (611) and is located at the left front screw propeller (612) on the axle of described left front electrical motor (611), and the end of described left back rotor bar (62) is provided with left back electrical motor (621) and is located at the left back screw propeller (622) on the axle of described left back electrical motor (621); The end end of described right front rotor bar (63) is provided with right front electrical motor (631) and is located at the right front screw propeller (632) on the axle of described right front electrical motor (631), and the end of described right back rotor bar (64) is provided with right back electrical motor (641) and is located at the right back screw propeller (642) on the axle of described right back electrical motor (641).
2. the deformable composite aircraft of one according to claim 1, it is characterized in that: described left front screw propeller (612) is identical with the rotation direction of described right back screw propeller (642), the direction of rotation of described left front screw propeller (612) and described left back screw propeller (622), right front screw propeller (632); Described left back screw propeller (622) is identical with the rotation direction of described right front screw propeller (632).
3. the deformable composite aircraft of one according to claim 1, is characterized in that: described left front rotor bar (61) is provided with for described left front screw propeller (612) is rotated to the left front apparatus for bending (613) parallel with described propelling screws (5) between described wing (4) with described left front electrical motor (611); Described left back rotor bar (62) is provided with for described left back screw propeller (622) is rotated to the left back apparatus for bending (623) parallel with described propelling screws (5) between described wing (4) with described left back electrical motor (621); Described right front rotor bar (63) is provided with for described right front screw propeller (632) is rotated to the right front apparatus for bending (633) parallel with described propelling screws (5) between described wing (4) with described right front electrical motor (631); Described right back rotor bar (64) is provided with for described right back screw propeller (642) is rotated to the right back apparatus for bending (643) parallel with described propelling screws (5) between described wing (4) with described right back electrical motor (641).
4. the deformable composite aircraft of one according to claim 3, is characterized in that: the distance between described left front apparatus for bending (613) and described left front electrical motor (611) equals the distance between described right front apparatus for bending (633) and described right front electrical motor (631); Distance between described left back apparatus for bending (623) and described left back electrical motor (621) equals the distance between described right back apparatus for bending (643) and described right back electrical motor (641).
5. the deformable composite aircraft of one according to claim 1, is characterized in that: the inside of described left front screw propeller (612), left back screw propeller (622), right front screw propeller (632), right back screw propeller (642) is provided with reinforced rib.
6. the deformable composite aircraft of one according to claim 1, is characterized in that: the line between described left front screw propeller (612) with described right back screw propeller (642) and the intersection point of line between described left back screw propeller (622) with described right front screw propeller (632) overlap with the center of gravity of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520664163.XU CN205022854U (en) | 2015-08-28 | 2015-08-28 | Deformable compound aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520664163.XU CN205022854U (en) | 2015-08-28 | 2015-08-28 | Deformable compound aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205022854U true CN205022854U (en) | 2016-02-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520664163.XU Active CN205022854U (en) | 2015-08-28 | 2015-08-28 | Deformable compound aircraft |
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| CN (1) | CN205022854U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516079A (en) * | 2016-10-28 | 2017-03-22 | 北京电子工程总体研究所（航天科工防御技术研究开发中心） | Assembly type aircraft based on micro electromechanical system |
| CN106672264A (en) * | 2016-12-13 | 2017-05-17 | 清华大学 | Deformable nose cone used for air vehicle and air vehicle comprising same |
| CN108438204A (en) * | 2018-05-21 | 2018-08-24 | 中宇航通（北京）科技有限公司 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
| CN112660368A (en) * | 2019-10-15 | 2021-04-16 | 上海峰飞航空科技有限公司 | Control method and system for flight resistance of vertical take-off and landing unmanned aerial vehicle |
-
2015
- 2015-08-28 CN CN201520664163.XU patent/CN205022854U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516079A (en) * | 2016-10-28 | 2017-03-22 | 北京电子工程总体研究所（航天科工防御技术研究开发中心） | Assembly type aircraft based on micro electromechanical system |
| CN106516079B (en) * | 2016-10-28 | 2019-06-14 | 北京电子工程总体研究所（航天科工防御技术研究开发中心） | A kind of combined type aircraft based on MEMS |
| CN106672264A (en) * | 2016-12-13 | 2017-05-17 | 清华大学 | Deformable nose cone used for air vehicle and air vehicle comprising same |
| CN106672264B (en) * | 2016-12-13 | 2018-12-11 | 清华大学 | For the deformation nose cone of aircraft and with its aircraft |
| CN108438204A (en) * | 2018-05-21 | 2018-08-24 | 中宇航通（北京）科技有限公司 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
| CN112660368A (en) * | 2019-10-15 | 2021-04-16 | 上海峰飞航空科技有限公司 | Control method and system for flight resistance of vertical take-off and landing unmanned aerial vehicle |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |