CN112407242B - A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin - Google Patents
A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin Download PDFInfo
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- CN112407242B CN112407242B CN202011238127.9A CN202011238127A CN112407242B CN 112407242 B CN112407242 B CN 112407242B CN 202011238127 A CN202011238127 A CN 202011238127A CN 112407242 B CN112407242 B CN 112407242B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
Abstract
The invention provides a joint integral type root rib for an unmanned aerial vehicle empennage and an unmanned aerial vehicle, wherein the joint integral type root rib is integrated with a front joint 2, a rear joint 3 and a rear beam joint 4 into a whole, the number of parts is reduced by 60%, the weight is light by 20%, the assembly time is reduced by 50%, and the manufacturing and assembly cost is reduced by 25%; the integral root rib of the joint has a simple structure, and the front joint is of a vertical lug structure so as to bear course load; the rear joint is of a double lug inserting plate vertical lug structure so as to bear shearing force and bending moment generated by pneumatic load of the tail wing; the web plate and the turned-over edge of the root rib form a box-shaped structure which is used for bearing the torque of the pneumatic load of the tail wing, the utilization rate of the structure is high, and the force transmission route is good; the front joint of the integral type root rib is positioned at the front edge of the root rib, so that a large space is reserved behind a main beam of the tail wing of the unmanned aerial vehicle while the rigidity and the strength of the tail wing of the unmanned aerial vehicle are good, and the type selection of an aero-engine and the installation of related equipment are facilitated.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicle facilities, in particular to an integral joint root rib for an unmanned aerial vehicle empennage and an unmanned aerial vehicle.
Background
The unmanned aerial vehicle empennage root rib and empennage joint are mostly in a riveted or screwed connection mode, when the unmanned aerial vehicle empennage root rib and empennage joint are assembled, the number of parts is large, the assembly time is long, assembly errors are easy to generate, an assembly fixture is required for positioning, the manufacturing cost is high, and force transmission is indirect; and, under thin wing section's space, be subject to the space, structural design is comparatively complicated, the dismouting difficulty, and structure weight is big, and the utilization ratio of structure is low.
Disclosure of Invention
The present invention is directed to solving one of the problems set forth above.
The invention mainly aims to provide a joint integral type root rib for an unmanned aerial vehicle empennage.
Another object of the present invention is to provide an unmanned aerial vehicle.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
one aspect of the present invention provides a joint integral type root rib for an unmanned aerial vehicle empennage, comprising: root rib 1, preceding joint 2, back joint 3 and back beam joint 4, root rib 1 preceding joint 2 back joint 3 with back beam joint 4 integrated into one piece, wherein:
the front joint 2 is positioned at the front edge 101 of the root rib 1;
the rear joint 3 is positioned on the front surface of the web plate 102 of the root rib 1, when the integral joint root rib is riveted with the unmanned aerial vehicle empennage, the rear joint 3 corresponds to the main beam of the unmanned aerial vehicle empennage, and the front surface of the web plate 102 is the surface of the web plate 102 opposite to the unmanned aerial vehicle body when the integral joint root rib is riveted with the unmanned aerial vehicle body;
the back beam connects 4 to be located the back of the web 102 of root rib 1, just is in connect integral root rib with during the riveting of unmanned aerial vehicle fin, the back beam connect 4 with the position of the girder of unmanned aerial vehicle fin corresponds, the back of web 102 does connect integral root rib with during the riveting of unmanned aerial vehicle fin the web 102 with the one side that the unmanned aerial vehicle fin is relative.
Optionally, the front joint 2 is of a stud structure, and a tab surface of the front joint 2 is parallel to a surface of the web 102 of the root rib 1 to bear a heading load.
Optionally, the rear joint 3 is a double-lug-inserting-lug vertical lug structure, and the lug surface of the rear joint 3 is perpendicular to the surface of the web plate 102 of the root rib 1 so as to bear the bending moment generated by the aerodynamic load of the empennage of the unmanned aerial vehicle.
Optionally, the back beam joint 4 is a channel beam structure, and a channel bottom surface of the channel beam structure is perpendicular to the surface of the web 102 of the root rib 1; alternatively, the first and second electrodes may be,
the back beam joint 4 is of an i-shaped structure, and the vertical part of the i-shaped structure is perpendicular to the surface of the web plate 102 of the root rib 1.
Optionally, the root rib 1 is of a double-flanged structure, a flange 103 on one side of the root rib 1 extends outwards from the front surface of the web plate 102, a front box-shaped structure is formed by the flange 103 on the front surface of the web plate 102, the front edge 101 of the root rib 1 and a rear wall 107 of the root rib 1, a flange 104 on the other side of the root rib 1 extends outwards from the back surface of the web plate 102, and a back box-shaped structure is formed on the back surface of the web plate 102 to bear the torque of the aerodynamic load of the empennage of the unmanned aerial vehicle.
Optionally, the front tab 2 is located at an end 105 of the leading edge 101 of the root rib 1.
Optionally, the rear joint 3 is located at a first position on the front surface of the web 102 of the root rib 1, and the rear beam joint 4 is located at a second position on the rear surface of the web 102 of the root rib 1, where the first position corresponds to the second position; the distance between the first location and the end 105 of the leading edge 101 is 1/3 the chord length of the web 102 and the distance between the second location and the end 105 of the leading edge 101 is 1/3 the chord length of the web 102.
Optionally, the web 102 of the root rib 1 is provided with lightening holes 106.
Optionally, the integral root rib of the joint for the empennage of the unmanned aerial vehicle provided by the invention further comprises: a bushing 5; wherein:
the bush 5 includes a plurality of, a plurality of the bush 5 respectively with the bolt hole of front joint 2 with the bolt hole of rear joint 3 adopts interference fit to fix.
Another aspect of the present invention provides an unmanned aerial vehicle, including: fuselage 20, empennage 30 and as described above the integral root rib 10 of the joint for the empennage of an unmanned aerial vehicle, wherein:
the front joint 2 and the rear joint 3 of the joint integral type root rib 10 of the unmanned aerial vehicle empennage are respectively and fixedly connected with the fuselage 20;
the rear beam joint 4 of the joint integral type root rib 10 of the unmanned aerial vehicle empennage is fixedly connected with the main beam of the empennage 30.
According to the technical scheme provided by the invention, the invention provides the joint integral type root rib for the tail wing of the unmanned aerial vehicle and the unmanned aerial vehicle, and the joint integral type root rib has the following beneficial effects:
(1) the joint integral type root rib fusion root rib 1, the front joint 2, the rear joint 3 and the rear beam joint 4 are integrated, the number of parts is reduced by 60%, the weight is light by 20%, the assembly time is reduced by 50%, and the manufacturing and assembly cost is reduced by 25%;
(2) the joint integral type root rib is simple in structure, the front joint is of a vertical lug structure, and the lug plane is parallel to the web surface of the joint integral type root rib so as to bear course load; the rear joint is of a double lug inserting plate vertical lug structure so as to bear shearing force and bending moment generated by pneumatic load of the tail wing; the web plate and the flanging of the root rib form a box-shaped structure for bearing the torque generated by the pneumatic load of the tail wing, the utilization rate of the structure is high, and the force transmission route is good;
(3) the front joint of the integral type root rib is positioned at the front edge of the root rib, so that a large space is reserved behind a main beam of the tail wing of the unmanned aerial vehicle while the rigidity and the strength of the tail wing of the unmanned aerial vehicle are good, and the type selection of an aero-engine and the installation of related equipment are facilitated.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
Fig. 1 is a schematic view of the internal structure of a joint integral root rib for an unmanned aerial vehicle empennage provided by the embodiment of the invention;
fig. 2 is a schematic view of the internal structure of another integral joint root rib for the tail wing of the unmanned aerial vehicle, provided by the embodiment of the invention;
fig. 3 is a partial cross-sectional view of a joint integral root rib for an unmanned aerial vehicle empennage provided by an embodiment of the present invention;
fig. 4 is a schematic structural diagram of the unmanned aerial vehicle provided in the embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention are clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or quantity or location.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
Example 1
Embodiments of the present invention will be described in further detail with reference to fig. 1 to 4.
Referring to fig. 1 to 3, an embodiment of the present invention provides a joint integral root rib for an unmanned aerial vehicle empennage, including: root rib 1, preceding joint 2, back joint 3 and back beam joint 4, root rib 1, preceding joint 2, back joint 3 and back beam joint 4 integrated into one piece, wherein:
the front tab 2 is located at the leading edge 101 of the root rib 1;
the rear joint 3 is positioned on the front surface of the web plate 102 of the root rib 1, when the integral joint root rib is riveted with the unmanned aerial vehicle empennage, the rear joint 3 corresponds to the main beam of the unmanned aerial vehicle empennage, and the front surface of the web plate 102 is the surface of the web plate 102 opposite to the unmanned aerial vehicle body when the integral joint root rib is riveted with the unmanned aerial vehicle body;
the back roof beam connects 4 to be located the back of the web 102 of root rib 1, and when connecting integral root rib and unmanned aerial vehicle fin riveting, the back roof beam connects 4 to correspond with the position of the girder of unmanned aerial vehicle fin, and the back of web 102 is the one side that web 102 is relative with the unmanned aerial vehicle fin when connecting integral root rib and unmanned aerial vehicle fin riveting.
In this embodiment, root rib 1, preceding joint 2, back joint 3 and back beam joint 4 are the aluminum alloy all-in-one and add the manufacturing, can reach the quantity of part and reduce 60%, light in weight 20%, and the assemble duration reduces 50%, makes and assembly cost reduces 25%'s effect.
In the existing root rib assembly, generally, the front joint 2 is arranged at the rear wall (107) of the root rib (see fig. 1 and 2), and in the embodiment, the front joint 2 is arranged at the front edge 101 of the root rib, so that the space of the front edge of the root rib is well utilized, the rigidity and the strength of the tail wing of the unmanned aerial vehicle can be ensured to be good, meanwhile, a large space is reserved behind the main beam of the tail wing of the unmanned aerial vehicle, and the type selection of an aero-engine and the installation of related equipment are facilitated. As an alternative to the present embodiment, the front joint 2 may be located at the end 105 of the leading edge 101 of the root rib 1, thereby leaving as much space behind the main beam of the empennage of the drone as possible.
As an alternative to the embodiment of the present invention, referring to fig. 1 to 2, the front joint 2 is a stud structure, and the tab surface of the front joint 2 is parallel to the surface of the web 102 of the root rib 1 to bear the heading load.
As an alternative implementation manner of the embodiment of the present invention, referring to fig. 1 to 3, the rear joint 3 is a double-insertion-lug-tab stud structure, and the surface of the lug of the rear joint 3 is perpendicular to the surface of the web plate 102 of the root rib 1, so as to bear the shearing force and bending moment generated by the aerodynamic load of the empennage of the unmanned aerial vehicle.
As an alternative embodiment of the present invention, referring to fig. 1 to 2, the root rib 1 is a double-flanged structure, one side flange 103 of the root rib 1 extends outwards from the front surface of the web 102 to form a front box-shaped structure with the front surface of the web 102, the front edge 101 of the root rib 1 and the root rib rear wall 107 of the root rib 1, and the other side flange 104 of the root rib 1 extends outwards from the back surface of the web 102 to form a back box-shaped structure on the back surface of the web 102 to bear the torque of the aerodynamic load of the empennage of the unmanned aerial vehicle.
In the embodiment, the joint integral type root rib is simple in structure, the front joint is of a vertical lug structure, and the lug plane is parallel to the web surface of the joint integral type root rib and is used for bearing course load; the rear joint is of a double lug inserting piece vertical lug structure and is used for bearing shearing force and bending moment generated by pneumatic load of the empennage; the web plate and the flanging of the root rib form a box-shaped structure for bearing the torque of the pneumatic load of the tail wing, so that the effects of high utilization rate of the structure and good force transmission route are achieved.
In this embodiment, connect 3 fuselage riveting with unmanned aerial vehicle through this preceding joint 2 and back to this will connect integral root rib and unmanned aerial vehicle's fuselage fixed Assembly.
As an alternative embodiment of the present invention, the back beam joint 4 is a channel beam structure (see fig. 2), and the channel bottom surface of the channel beam structure is arranged perpendicular to the surface of the web 102 of the root rib 1; alternatively, the rear beam joint 4 is an i-shaped structure (not shown in the drawings), and a vertical portion of the i-shaped structure is arranged perpendicular to the surface of the web 102 of the root rib 1. This alternative is only an alternative to the back beam joint 4 provided in the present embodiment, and the present embodiment is not limited to this. The rear beam joint 4 is riveted with a main beam of the tail wing, so that the joint integral type root rib is fixedly assembled with the tail wing of the unmanned aerial vehicle.
As an alternative embodiment of the present invention, the rear joint 3 is located at a first position on the front surface of the web 102 of the root rib 1, the rear beam joint 4 is located at a second position on the rear surface of the web 102 of the root rib 1, and the first position corresponds to the second position; the distance between the first location and the end 105 of the leading edge 101 is 1/3 the chord length of the web 102 and the distance between the second location and the end 105 of the leading edge 101 is 1/3 the chord length of the web 102. This alternative embodiment is merely a preferred embodiment, and the first position and the second position may be disposed at other positions of the web 102, which is not limited by the present invention. In practical application, when the integral joint type root rib provided by the invention is fixedly installed on the empennage of the unmanned aerial vehicle, the rear beam joint 4 is riveted with the main beam of the empennage of the unmanned aerial vehicle, and the first position and the second position correspond to the positions of the main beam of the empennage of the unmanned aerial vehicle.
As an alternative to the embodiment of the present invention, referring to fig. 1 to 3, the web 102 of the root rib 1 is provided with lightening holes 106. The weight of the root rib can be reduced by providing the lightening hole 106. In addition, this lightening hole 106 can also be regarded as crossing the line hole, and the cable between unmanned aerial vehicle fin and the unmanned aerial vehicle fuselage can pass through this lightening hole 106.
As an optional implementation manner of the embodiment of the present invention, the integral root rib of a joint for an unmanned aerial vehicle empennage provided by the embodiment of the present invention further includes: a bushing 5; wherein: the bush 5 includes a plurality of, and a plurality of bushes 5 adopt interference fit to fix with the bolt hole of front joint 2 and the bolt hole of rear joint 3 respectively. The size of the bush 5 matches the size of the bolt holes on the front and rear joints 2, 3. Specifically, as shown in fig. 1 and 2, the front connector 2 has a spiral hole, and a bushing 5 can be fitted into the spiral hole of the front connector 2 for interference fit. As shown in fig. 3, the rear joint 2 is a double-lug-insertion-piece vertical lug structure, each lug is provided with 2 spiral holes, the rear joint has 4 spiral holes, and 4 bushings 5 are required to be fixed with the rear joint in an interference fit manner.
In addition, this embodiment still provides an unmanned aerial vehicle. Referring to fig. 4, the unmanned aerial vehicle provided in the embodiment of the present invention includes: fuselage 20, empennage 30 and as described above the integral root rib 10 of the joint for the empennage of an unmanned aerial vehicle, wherein: the front joint 2 and the rear joint 3 of the joint integral type root rib 10 of the unmanned aerial vehicle empennage are respectively and fixedly connected with the fuselage 20; the rear beam joint 4 of the joint integral type root rib 10 of the unmanned aerial vehicle empennage is fixedly connected with the main beam of the empennage 30.
As an optional implementation manner in this embodiment, the other side flanging 104 of the root rib 1 is further riveted with the tail joint cover, the tail leading edge and the tail rudder angle box, so as to further fixedly assemble the joint integral root rib 10 of the unmanned aerial vehicle tail with the tail 30.
The invention provides a joint integral type root rib for an unmanned aerial vehicle empennage and an unmanned aerial vehicle, which have the following beneficial effects:
(1) the joint integral type root rib fusion root rib 1, the front joint 2, the rear joint 3 and the rear beam joint 4 are integrated, the number of parts is reduced by 60%, the weight is light by 20%, the assembly time is reduced by 50%, and the manufacturing and assembly cost is reduced by 25%;
(2) the joint integral type root rib is simple in structure, the front joint is of a vertical lug structure, and the lug plane is parallel to the web surface of the joint integral type root rib so as to bear course load; the rear joint is of a double lug inserting plate vertical lug structure so as to bear shearing force and bending moment generated by pneumatic load of the tail wing; the web plate and the flanging of the root rib form a box-shaped structure for bearing the torque generated by the pneumatic load of the tail wing, the utilization rate of the structure is high, and the force transmission route is good;
(3) the front joint of the integral type root rib is positioned at the front edge of the root rib, so that a large space is reserved behind a main beam of the tail wing of the unmanned aerial vehicle while the rigidity and the strength of the tail wing of the unmanned aerial vehicle are good, and the type selection of an aero-engine and the installation of related equipment are facilitated.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (9)
1. A connect integral root rib for unmanned aerial vehicle fin, its characterized in that includes: root rib (1), front joint (2), rear joint (3) and back beam joint (4), root rib (1) front joint (2) rear joint (3) and back beam joint (4) integrated into one piece, wherein:
the front joint (2) is positioned at the front edge (101) of the root rib (1);
the rear joint (3) is located on the front face of a web plate (102) of the root rib (1), when the integral joint root rib is riveted with an unmanned aerial vehicle empennage, the rear joint (3) corresponds to the main beam of the unmanned aerial vehicle empennage, and the front face of the web plate (102) is the face, opposite to the unmanned aerial vehicle body, of the web plate (102) when the integral joint root rib is riveted with the unmanned aerial vehicle body;
the rear beam joint (4) is located on the back of a web plate (102) of the root rib (1), when the integral joint root rib is riveted with the unmanned aerial vehicle empennage, the rear beam joint (4) corresponds to the main beam of the unmanned aerial vehicle empennage, and the back of the web plate (102) is the surface of the web plate (102) opposite to the unmanned aerial vehicle empennage when the integral joint root rib is riveted with the unmanned aerial vehicle empennage;
the rear beam joint (4) is of a groove-shaped beam structure, and the groove-shaped bottom surface of the groove-shaped beam structure is perpendicular to the surface of the web plate (102) of the root rib (1); alternatively, the first and second electrodes may be,
the rear beam joint (4) is of an I-shaped structure, and the vertical part of the I-shaped structure is perpendicular to the surface of the web plate (102) of the root rib (1).
2. The joint integral root rib of claim 1, wherein:
the front joint (2) is of a vertical lug structure, and the lug surface of the front joint (2) is parallel to the surface of the web plate (102) of the root rib (1) so as to bear course load.
3. The joint integral root rib of claim 1, wherein:
the rear joint (3) is of a double-lug-inserting-piece vertical lug structure, and the lug surface of the rear joint (3) is perpendicular to the surface of a web plate (102) of the root rib (1) so as to bear shearing force and bending moment generated by pneumatic load of the tail wing of the unmanned aerial vehicle.
4. The joint integral root rib of claim 1, wherein:
root rib (1) are two turn-ups structure, one side turn-ups (103) of root rib (1) are followed the front of web (102) is outwards extended, with the front of web (102), the leading edge (101) of root rib (1) and root rib back wall (107) of root rib (1) form positive box type structure, another side turn-ups (104) of root rib (1) are followed the back of web (102) is outwards extended the back of web (102) forms back box type structure to bear the moment of torsion of the aerodynamic load of unmanned aerial vehicle fin.
5. The joint integral root rib of claim 1 or 2, wherein:
the front joint (2) is located at an end (105) of a leading edge (101) of the root rib (1).
6. A joint integral root rib as claimed in claim 1 or 3, wherein:
the rear joint (3) is located at a first position on the front surface of the web (102) of the root rib (1), the rear beam joint (4) is located at a second position on the back surface of the web (102) of the root rib (1), and the first position corresponds to the second position; the first location is spaced from the end (105) of the leading edge (101) by 1/3 a chord length of the web (102), and the second location is spaced from the end (105) of the leading edge (101) by 1/3 a chord length of the web (102).
7. The joint integral root rib of claim 1, wherein:
lightening holes (106) are arranged on the web (102) of the root rib (1).
8. The joint integral root rib of claim 1, wherein: further comprising: a bushing (5); wherein:
the bush (5) comprises a plurality of bushes (5), and the bushes (5) are fixed with the bolt holes of the front joint (2) and the bolt holes of the rear joint (3) in an interference fit mode respectively.
9. An unmanned aerial vehicle, its characterized in that: the method comprises the following steps: fuselage (20), empennage (30) and joint integral root rib (10) for an unmanned aerial vehicle empennage according to any of claims 1 to 8, wherein:
the front joint (2) and the rear joint (3) of the joint integral type root rib (10) of the unmanned aerial vehicle empennage are respectively and fixedly connected with the fuselage (20);
the rear beam joint (4) of the joint integral type root rib (10) of the unmanned aerial vehicle empennage is fixedly connected with the main beam of the empennage (30).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011238127.9A CN112407242B (en) | 2020-11-09 | 2020-11-09 | A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011238127.9A CN112407242B (en) | 2020-11-09 | 2020-11-09 | A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin |
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| CN112407242B true CN112407242B (en) | 2021-07-20 |
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Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6497600B1 (en) * | 1999-10-05 | 2002-12-24 | Alejandro Velasco Levy | Automatic pilot system for model aircraft |
| ES2346834B1 (en) * | 2007-04-30 | 2011-08-17 | Airbus Operations, S.L. | RIB STRUCTURE FOR TORSION DRAWERS OF A WING OR A STABILIZER OF AN AIRCRAFT. |
| CN108100230A (en) * | 2017-12-01 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter horizontal tail wing box |
| CN208715479U (en) * | 2018-08-02 | 2019-04-09 | 中国科学院工程热物理研究所 | Modularization supersonic speed unmanned plane |
| CN208915424U (en) * | 2018-08-23 | 2019-05-31 | 西安三翼航空科技有限公司 | A kind of detachable empennage bindiny mechanism |
| CN209535435U (en) * | 2018-12-06 | 2019-10-25 | 天和无人机科技溧阳有限公司 | Miniature fixed wing aircraft |
| CN109823514B (en) * | 2019-02-02 | 2021-01-12 | 北京航空航天大学 | Quick detachable fin structure of adjustable installation angle |
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2020
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