CN205202635U - Fin subassembly and have its hovercar for hovercar - Google Patents
Fin subassembly and have its hovercar for hovercar Download PDFInfo
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- CN205202635U CN205202635U CN201521014464.4U CN201521014464U CN205202635U CN 205202635 U CN205202635 U CN 205202635U CN 201521014464 U CN201521014464 U CN 201521014464U CN 205202635 U CN205202635 U CN 205202635U
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Abstract
The utility model discloses a fin subassembly and have its hovercar for hovercar. The fin subassembly sets up for the hovercar on the tail, the fin subassembly includes: the vertical fin, it is connected with the tail, and the perpendicular to the tail sets up, the horizontal tail subassembly, it includes course left side horizontal tail and course right side horizontal tail, course left side horizontal tail and course right side horizontal tail respectively with the tail is connected, wherein, at oneself in the projection of aircraft nose to tail direction, the vertical fin with form two contained angles that the number of degrees are the same respectively between course left side horizontal tail and the course right side horizontal tail, just the contained angle is greater than 90 degrees. The utility model discloses a fin subassembly is in the projection from aircraft nose to tail direction for the hovercar, forms two contained angles that the number of degrees are the same respectively between vertical fin and course left side horizontal tail and the course right side horizontal tail, and the contained angle is greater than 90 degrees, is in promptly the utility model discloses turning over under the well horizontal tail, forming the type of falling Y with the vertical fin, the horizontal tail can play certain course and increase steady effect, reduces the vertical fin size.
Description
Technical Field
The utility model relates to a hovercar technical field especially relates to a fin subassembly and have its hovercar for hovercar.
Background
The flying automobile needs to give consideration to the performances of air flight and road surface driving, which has great difference to the design requirements of the tail wing. The traditional airplane tail mainly plays a role in controlling direction and lifting, and maintains the stability of airplane control, and the functions are redundant in the process of driving on a road surface. The rear wheel of the traditional front-wheel drive automobile mainly has the functions of keeping the stability and the safety of the automobile and supporting the automobile, and the functions are also redundant in the air flight process.
At present, in the design of various tail wings of aerocars, tail wheels and tail wings are separated or a double-vertical-tail H-shaped structure is mostly adopted. The tail wheel and the tail wing are separated from each other, so that the system reliability is improved to a certain extent, the number of parts is increased, the comprehensive utilization of the structure cannot be realized, and although the double vertical tail H-shaped structure realizes the comprehensive utilization of the structure to a certain extent, the stress directions of the horizontal tail and the tail wheel are vertical, the horizontal tail moment is increased, and the structural strength is low under the road running state.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
SUMMERY OF THE UTILITY MODEL
It is an object of the present invention to provide a tail assembly for a flying vehicle which overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.
In order to achieve the above object, the utility model provides an empennage assembly for hovercar, hovercar includes aircraft nose and tail, the empennage assembly sets up on the tail, the empennage assembly includes: the vertical fin is connected with the machine tail and is arranged perpendicular to the machine tail; the horizontal tail assembly comprises a course left horizontal tail and a course right horizontal tail, and the course left horizontal tail and the course right horizontal tail are respectively connected with the tail; in the projection from the machine head to the machine tail, two included angles with the same degree are formed between the vertical tail and the left horizontal tail and between the vertical tail and the right horizontal tail respectively, and the included angles are larger than 90 degrees.
Preferably, the tip of the other end of the horizontal tail navigating to the left, which is opposite to the end connected with the tail, is a left tail wheel fairing, and the tip of the other end of the horizontal tail navigating to the right, which is opposite to the end connected with the tail, is a right tail wheel fairing.
Preferably, the tail assembly further comprises two tail wheels, one of which is disposed within the left tail wheel fairing and the other of which is disposed within the right tail wheel fairing.
Preferably, the hovercar further comprises a propeller, the propeller is arranged at the end part of the tail of the hovercar; the propeller comprises three propeller blades, wherein any one propeller blade is taken as a first propeller blade, the other propeller blade is taken as a second propeller blade, and the remaining propeller blade is taken as a third propeller blade; when the first propeller blade is superposed with the projection of any one of the empennage, the course left horizontal tail or the course right horizontal tail in the direction from the machine head to the machine tail, the second propeller blade and the third propeller blade are respectively superposed with the other two projections of the empennage, the course left horizontal tail or the course right horizontal tail which are not superposed with the projection of the first propeller blade; and in the projection in the direction, the tail wing corresponds to one propeller blade, the course left horizontal tail corresponds to one propeller blade, and the course right horizontal tail corresponds to one propeller blade.
Preferably, the three propeller blades have a dimension in the projection of the nose-to-tail direction that is smaller than the dimensions of the tail, the left heading tail and the right heading tail in the projection direction.
Preferably, the included angle is 120 degrees.
The utility model also provides a hovercar, hovercar includes as above the fin subassembly for the hovercar.
The utility model discloses an fin subassembly is forming the contained angle that two degrees are the same between vertical fin and the horizontal tail of left side of course and the horizontal tail of right side of course respectively in the projection from aircraft nose to tail direction for the hovercar, and the contained angle is greater than 90 degrees, is in promptly the utility model discloses well horizontal tail is inverted down, forms the type of falling Y with vertical fin, and the horizontal tail can play certain course and increase steady effect, reduces the vertical fin size.
Drawings
Fig. 1 is a schematic structural view of a tail assembly for a flying vehicle according to an embodiment of the present invention.
Fig. 2 is a schematic view of the structure of the tail section of the fin assembly for a flying vehicle shown in fig. 1.
Reference numerals:
| 1 | machine head | 6 | Left tail wheel fairing |
| 2 | Tail | 7 | Right tail wheel fairing |
| 3 | Vertical fin | 8 | Tail wheel |
| 4 | Horizontal tail of aeronautical left | 9 | Propeller |
| 5 | Horizontal tail for sailing to right |
Detailed Description
In order to make the purpose, technical solution and advantages of the present invention clearer, the following will combine the drawings in the embodiments of the present invention to perform more detailed description on the technical solution in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not 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 therefore, should not be considered as limiting the scope of the invention.
Fig. 1 is a schematic structural view of a tail assembly for a flying vehicle according to an embodiment of the present invention. Fig. 2 is a schematic view of the structure of the tail section of the fin assembly for a flying vehicle shown in fig. 1.
The aerocar comprises a nose 1 and a tail 2.
In the fin assembly for a flying vehicle shown in fig. 1, the fin assembly is provided on a tail 2, and the fin assembly includes a vertical fin 3 and a horizontal fin assembly. In the embodiment, the vertical tail 3 is connected with the machine tail 2 and is arranged perpendicular to the machine tail 2; the horizontal tail assembly comprises a course left horizontal tail 4 and a course right horizontal tail 5, and the course left horizontal tail 4 and the course right horizontal tail 5 are respectively connected with the tail 2; in the projection from the machine head to the machine tail direction, two included angles with the same degree are formed between the vertical tail 3 and the left horizontal tail 4 and between the vertical tail and the right horizontal tail 5 respectively, and the included angles are larger than 90 degrees.
In the embodiment, the tip of the other end of the course left horizontal tail 4 opposite to the end connected with the tail 2 is a left tail wheel fairing 6, and the tip of the other end of the course right horizontal tail 5 opposite to the end connected with the tail 2 is a right tail wheel fairing 7.
In this embodiment the tail assembly further comprises two tail wheels 8, one of which is arranged in the left tail wheel fairing 6 and the other in the right tail wheel fairing 7.
In the embodiment, the aerocar further comprises a propeller 9, wherein the propeller 9 is arranged at the end part of the tail of the aerocar; the propeller 9 comprises three propeller blades, wherein any one propeller blade is taken as a first propeller blade, the other propeller blade is taken as a second propeller blade, and the remaining one propeller blade is taken as a third propeller blade; when the first propeller blade is superposed with the projection of any one of the tail wing, the course left horizontal tail or the course right horizontal tail in the direction from the machine head to the machine tail, the second propeller blade and the third propeller blade are respectively superposed with the other two projections of the tail wing, the course left horizontal tail or the course right horizontal tail which are not superposed with the projection of the first propeller blade; and in the projection in the direction, the tail wing corresponds to one propeller blade, the course left horizontal tail corresponds to one propeller blade, and the course right horizontal tail corresponds to one propeller blade.
In the embodiment, the size of the projection of the three propeller blades in the direction from the machine head to the machine tail is smaller than the size of the tail wing, the left horizontal tail of the heading direction and the right horizontal tail of the heading direction in the projection direction.
In this embodiment, the included angle greater than 90 degrees is 120 degrees.
Adopt the utility model discloses an fin subassembly for hovercar has following advantage:
1. in the projection from the machine head to the machine tail direction, two included angles with the same degree are respectively formed between the vertical tail and the left horizontal tail and between the vertical tail and the right horizontal tail, and the included angle is larger than 90 degrees, namely, the horizontal tail is inverted downwards and forms an inverted Y shape with the vertical tail, the horizontal tail can play a certain course stabilizing role, and the size of the vertical tail is reduced;
2. the inverted Y-shaped tail wing can completely shield the outline of the propeller at the tail end of the aerocar, so that the safety of ground running is improved;
3. the tail wheel is arranged at the tip of the lower reverse horizontal tail wing, so that the number of parts is reduced, the function synthesis and weight reduction are realized, the material and weight of the aerocar are reduced, and the cost is reduced;
4. the lower reverse horizontal tail and the tail wheel form an included angle in the stress direction, the force borne by the tail wheel in the driving process of the aerocar on the road surface can be axially transmitted to the aerocar body along the lower reverse horizontal tail, the root moment of the lower reverse horizontal tail is reduced, and the structural strength is higher.
The utility model also provides a hovercar, hovercar includes as above the fin subassembly for the hovercar.
Finally, it should be pointed out that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (7)
1. A fin assembly for a flying automobile, the flying automobile comprising a nose (1) and a tail (2), characterized in that the fin assembly is provided on the tail (2), the fin assembly comprising:
the vertical fin (3) is connected with the machine tail (2) and is perpendicular to the machine tail (2);
the horizontal tail assembly comprises a course left horizontal tail (4) and a course right horizontal tail (5), and the course left horizontal tail (4) and the course right horizontal tail (5) are respectively connected with the tail (2); wherein,
in the projection from the machine head to the machine tail direction, two included angles with the same degree are formed between the vertical tail (3) and the course left horizontal tail (4) and between the vertical tail and the course right horizontal tail (5), and the included angles are larger than 90 degrees.
2. A tail assembly for a flying vehicle according to claim 1, wherein the tip of the other end of the left-hand horizontal tail (4) opposite to the end connected to the tail (2) is a left-wheel fairing (6), and the tip of the other end of the right-hand horizontal tail (5) opposite to the end connected to the tail (2) is a right-wheel fairing (7).
3. A tail assembly for a flying vehicle according to claim 2, wherein the tail assembly further comprises two tail wheels (8), one of which is disposed within the left tail wheel fairing (6) and the other of which is disposed within the right tail wheel fairing (7).
4. A tail assembly as claimed in claim 2, wherein the flying vehicle further comprises a propeller (9), the propeller (9) being provided at the end of the tail of the flying vehicle; the propeller (9) comprises three propeller blades, wherein any one propeller blade is taken as a first propeller blade, the other propeller blade is taken as a second propeller blade, and the remaining one propeller blade is taken as a third propeller blade; when the first propeller blade is superposed with the projection of any one of the empennage, the course left horizontal tail or the course right horizontal tail in the direction from the machine head to the machine tail, the second propeller blade and the third propeller blade are respectively superposed with the other two projections of the empennage, the course left horizontal tail or the course right horizontal tail which are not superposed with the projection of the first propeller blade; and in the projection in the direction, the tail wing corresponds to one propeller blade, the course left horizontal tail corresponds to one propeller blade, and the course right horizontal tail corresponds to one propeller blade.
5. A tail assembly as claimed in claim 4, wherein the three propeller blades have a dimension in projection in the nose to tail direction which is less than the dimensions of the tail, left and right heading tails in the projection direction.
6. A tail assembly for a flying vehicle according to claim 1 wherein said included angle is 120 degrees.
7. A flying car comprising a tail assembly as claimed in any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521014464.4U CN205202635U (en) | 2015-12-09 | 2015-12-09 | Fin subassembly and have its hovercar for hovercar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521014464.4U CN205202635U (en) | 2015-12-09 | 2015-12-09 | Fin subassembly and have its hovercar for hovercar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205202635U true CN205202635U (en) | 2016-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521014464.4U Active CN205202635U (en) | 2015-12-09 | 2015-12-09 | Fin subassembly and have its hovercar for hovercar |
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| Country | Link |
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| CN (1) | CN205202635U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107273638A (en) * | 2017-07-06 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fuselage based on horizontal tail load and empennage connecting hinge point load distribution method |
-
2015
- 2015-12-09 CN CN201521014464.4U patent/CN205202635U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107273638A (en) * | 2017-07-06 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fuselage based on horizontal tail load and empennage connecting hinge point load distribution method |
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| C14 | Grant of patent or utility model | ||
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| TR01 | Transfer of patent right |
Effective date of registration: 20201027 Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002 Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA |