CN118618656B - Barrel-jet unmanned aerial vehicle - Google Patents
Barrel-jet unmanned aerial vehicle Download PDFInfo
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- CN118618656B CN118618656B CN202411095223.0A CN202411095223A CN118618656B CN 118618656 B CN118618656 B CN 118618656B CN 202411095223 A CN202411095223 A CN 202411095223A CN 118618656 B CN118618656 B CN 118618656B
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- 230000006978 adaptation Effects 0.000 claims 1
- 239000011425 bamboo Substances 0.000 claims 1
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- 238000000034 method Methods 0.000 abstract description 11
- 230000008569 process Effects 0.000 abstract description 11
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Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to a barrel-jet unmanned aerial vehicle, which comprises a fuselage, a front wing arranged near the front end of the fuselage, a rear wing arranged near the tail end of the fuselage, and a vertical fin and propeller assembly arranged at the tail end of the fuselage, wherein the front wing, the rear wing, the vertical fin and the propeller assembly can be folded and unfolded by taking the fuselage as the center; the front wing is provided with an aileron, the front wing is provided with a pressing sheet, the machine body is provided with a steering engine and a rocker arm, and the rocker arm is matched with the pressing sheet to clamp the aileron so as to achieve the purpose of controlling the deflection angle of the aileron; therefore, the thickness dimension of the unmanned aerial vehicle in a folded state is reduced; in the process that the unmanned aerial vehicle is unfolded from the folding state to the unfolding state, the left front wing and the right front wing are independently unfolded, so that the acting force required by the unmanned aerial vehicle from the folding state to the unfolding state is reduced.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a barrel-jet unmanned aerial vehicle.
Background
Advantages of the drone include fast reaction capability and simplified deployment process, and is suitable for situations where a large number of drones need to be deployed rapidly, for example, against high-value targets or to perform reconnaissance tasks, the drone is increasingly widely used in modern military wars due to its advantages in terms of combat efficiency and battlefield flexibility, and in order to improve the operability of the drone when in a flight state, the structural design of the drone is increasingly approaching to a real aircraft structure, including the addition of an aileron structure.
The Chinese patent with the publication number of CN109987217A discloses a folding wing unmanned aerial vehicle, wherein the right outer part of the folding wing unmanned aerial vehicle comprises a body (01), a front straight wing, a rear straight wing, a foldable vertical tail arranged at the tail part of the body and a foldable propeller assembly arranged at the rear end of the body, an aileron is arranged on the rear straight wing, and the aileron comprises a left aileron (07) and a right aileron (05); the right aileron (05) is connected with the right rear straight wing (04) through hinge paper, the right aileron (05) can be folded up and down, a first aileron connecting piece (29) is fixed on the right aileron, a right steering engine (32) is fixed on the right rear straight wing (04), and a steering engine arm (31) of the right steering engine is hinged with the first aileron connecting piece; the left aileron (07) is connected with the left rear straight wing (06) through hinge paper, the left aileron (07) can be folded up and down, a second aileron connecting piece is fixed on the left aileron, a left steering engine is fixed on the left rear straight wing (06), and a steering engine arm of the left steering engine is hinged with the second aileron connecting piece; the folding wing unmanned aerial vehicle controls the rudder horn to drive the aileron to deflect through the steering engine, so as to realize the control of the flight state of the unmanned aerial vehicle.
However, although the folding wing unmanned aerial vehicle can realize the deflection control to the aileron, in the actual use process, the inventor finds that the aileron control structure has the defects, specifically:
Steering wheel and steering wheel arm setting of this aileron are on flat wing, and the problem that exists is: on the one hand, the weight of the straight wing is increased, the steering wheel and the steering wheel arm are rotated along with the straight wing in the process of rotating the straight wing from the folding state to the unfolding state, so that the mechanism for driving the straight wing to unfold can unfold the straight wing, the steering wheel and the steering wheel arm together by providing larger acting force, the acting force required by unfolding the straight wing is increased, on the other hand, when the straight wing is in the folding state, a thicker space is required to be provided for simultaneously accommodating the steering wheel on the overlapped left straight wing, the steering wheel Zuo Pingzhi wing and the steering wheel on the right straight wing and the right straight wing in the thickness direction of the unmanned aerial vehicle, and the thickness dimension of the unmanned aerial vehicle is increased.
Therefore, in view of the above-mentioned shortcomings, there is a need to design a barrel-jet unmanned aerial vehicle for reducing the thickness of the unmanned aerial vehicle in a folded state, and the effort required by the unmanned aerial vehicle from the folded state to the unfolded state.
Disclosure of Invention
The invention aims at: aiming at the defects of the control mechanism of the aileron of the unmanned aerial vehicle in the practical use process, the cylindrical shooting type unmanned aerial vehicle is provided for reducing the thickness dimension of the unmanned aerial vehicle in the folding state, and the unmanned aerial vehicle is required acting force from the folding state to the unfolding state.
In order to achieve the above object, the present invention provides the following technical solutions:
The barrel-jet unmanned aerial vehicle comprises a fuselage, a front wing, a rear wing, a vertical tail and a propeller assembly, wherein the front wing is arranged near the front end of the fuselage, the rear wing is arranged near the tail end of the fuselage, the vertical tail and the propeller assembly are arranged at the tail end of the fuselage, and the front wing, the rear wing, the vertical tail and the propeller assembly can be folded and unfolded by taking the fuselage as the center;
the front wing comprises a left front wing and a right front wing, a left aileron is rotatably arranged on the left front wing, a left pressing piece is arranged between the left front wing and the left aileron, the left pressing piece has elasticity, one end of the left pressing piece is fixedly connected with the left front wing, the other end of the left pressing piece is abutted with the left aileron, a left steering engine is arranged on the machine body, a left rocker arm is arranged on the left steering engine, one end of the left rocker arm is rotatably connected with the left steering engine, the other end of the left rocker arm is abutted with the left aileron, and the left pressing piece and the left rocker arm form clamping on the left aileron;
the rotatable right aileron that is provided with on the right front wing, right front wing with be provided with right preforming between the right aileron, right preforming has elasticity, right preforming one end with right front wing fixed connection, the other end with right aileron butt, be provided with right steering wheel on the fuselage, be provided with right rocking arm on the steering wheel, right rocking arm one end with right steering wheel rotates to be connected, the other end with right aileron butt, right preforming with right rocking arm cooperation is right the aileron forms the centre gripping.
As a preferential technical scheme of the application, the machine body is provided with a groove which is used for accommodating the left steering engine and the right steering engine.
As a preferred technical scheme of the application, the left front wing is located above the right front wing, a left concave platform is arranged at a position on the left aileron, which is contacted with the left rocker arm, a right boss is arranged at a position on the right aileron, which is contacted with the right rocker arm, and a surface of the left concave platform, which is contacted with the left rocker arm, and a surface of the right boss, which is contacted with the right rocker arm, are on the same horizontal plane.
As a preferential technical scheme of the application, the periphery of the left concave table is provided with a left concave table inclined plane which is inclined inwards from top to bottom, the periphery of the right boss is provided with a right boss inclined plane which is inclined outwards from top to bottom, and the left concave table inclined plane is matched with the right boss inclined plane.
As a preferred technical solution of the present application, the front wing and the rear wing are both mounted below the fuselage, the left front wing and the right front wing can be folded toward the tail of the fuselage with the fuselage as a center, the rear wing includes a left rear wing and a right rear wing, and the left rear wing and the right rear wing can be folded toward the head of the fuselage with the fuselage as a center.
Compared with the prior art, the invention has the beneficial effects that:
1. In the scheme of the application, the steering engine is arranged on the plane body, when the cylindrical unmanned aerial vehicle is in a folded state, the left front wing and the right front wing of the cylindrical unmanned aerial vehicle are folded to be parallel to the plane body, and as the steering engine is not arranged on the left front wing and the right front wing, the left front wing and the right front wing can be attached to each other more closely in the thickness direction of the unmanned aerial vehicle when being folded together, so that the thickness dimension of the unmanned aerial vehicle in the folded state is thinned; in the process that the unmanned aerial vehicle is unfolded from the folding state to the unfolding state, the left front wing and the right front wing are independently unfolded, so that the acting force required by the unmanned aerial vehicle from the folding state to the unfolding state is reduced; after the front wing is unfolded, the left rocker arm and the left pressing sheet are matched to clamp the left aileron, when the angle of the left aileron needs to be adjusted, the left steering engine drives the left rocker arm to apply acting force to the left aileron, the left aileron changes the angle, meanwhile, the left pressing sheet elastically deforms, when the angle of the aileron needs to be adjusted again, the left steering engine drives the left rocker arm to be far away from the left aileron, under the action of the recovery deformation of the left pressing sheet, the left aileron changes the angle, the adjustment of the angle of the right aileron is realized in the same way, and the flight attitude of the unmanned aerial vehicle is controlled by changing the angles of the left aileron and the right aileron;
2. Because the left front wing and the right front wing are at the difference in height of unmanned aerial vehicle thickness direction, lead to left side rocking arm and right rocking arm length difference great, further influence the control to left aileron and right aileron, set up the face that left concave station and left rocking arm contacted and the face that right boss and right rocking arm contacted on same horizontal plane, so set up for the same length can be accomplished to left rocking arm and right rocking arm's length, make the control to left aileron and right aileron more balanced, be favorable to the control to unmanned aerial vehicle flight gesture.
Drawings
Fig. 1 is a schematic structural view of one embodiment of a barrel-jet unmanned aerial vehicle according to the present application;
FIG. 2 is a schematic view of a partial structure of one embodiment of a barrel-jet unmanned aerial vehicle according to the present application;
FIG. 3 is a schematic view of a partially split structure of one embodiment of a barrel-jet unmanned aerial vehicle according to the present application;
FIG. 4 is a schematic view of an embodiment of a deployment process of a barrel-jet unmanned aerial vehicle according to the present application;
FIG. 5 is an enlarged view of portion A of FIG. 1;
The figures indicate: 1-fuselage, 2-front wing, 3-rear wing, 4-vertical tail, 5-propeller assembly, 11-groove, 21-left front wing, 22-right front wing, 211-left aileron, 212-left preform, 213-left steering engine, 214-left rocker arm, 221-right aileron, 222-right preform, 223-right steering engine, 224-right rocker arm, 2111-left concave platform, 2112-left concave platform inclined plane, 2211-right convex platform, 2212-right convex platform inclined plane, 31-left rear wing, 32-right rear wing.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It will be apparent that the described embodiments are some, but not all, embodiments of the invention.
Thus, the following detailed description of the embodiments of the invention is not intended to limit the scope of the invention, as claimed, but is merely representative of some embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that, under the condition of no conflict, the embodiments of the present invention and the features and technical solutions in the embodiments may be combined with each other.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present invention, it should be noted that, the terms "upper", "lower", and the like indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, or an azimuth or a positional relationship conventionally put in use of the inventive product, or an azimuth or a positional relationship conventionally understood by those skilled in the art, such terms are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element to be referred must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Embodiment one: as shown in reference to figures 1 to 5,
The barrel-jet unmanned aerial vehicle provided by the embodiment comprises a body 1, a front wing 2 arranged near the front end of the body 1, a rear wing 3 arranged near the tail end of the body 1, a vertical tail 4 arranged at the tail of the body 1 and a propeller assembly 5, wherein the front wing 2, the rear wing 3, the vertical tail 4 and the propeller assembly 5 can be folded and unfolded by taking the body 1 as the center;
The front wing 2 comprises a left front wing 21 and a right front wing 22, a left aileron 211 is rotatably arranged on the left front wing 21, a left pressing sheet 212 is arranged between the left front wing 21 and the left aileron 211, the left pressing sheet 212 has elasticity, one end of the left pressing sheet 212 is fixedly connected with the left front wing 21, the other end of the left pressing sheet 212 is abutted to the left aileron 211, a left steering engine 213 is arranged on the machine body 1, a left rocker arm 214 is arranged on the left steering engine 213, one end of the left rocker arm 214 is rotatably connected with the left steering engine 213, the other end of the left rocker arm 214 is abutted to the left aileron 211, and the left pressing sheet 212 and the left rocker arm 214 form clamping on the left aileron 211;
The rotatable right aileron 221 that is provided with on the right front wing 22, right front wing 22 with be provided with right preforming 222 between the right aileron 221, right preforming 222 has elasticity, right preforming 222 one end with right front wing 22 fixed connection, the other end with right aileron 221 butt, be provided with right steering engine 223 on the fuselage 1, be provided with right rocking arm 224 on the right steering engine 223, right rocking arm 224 one end with right steering engine 223 rotates to be connected, the other end with right aileron 221 butt, right preforming 222 with right rocking arm 224 cooperation is right aileron 221 forms the centre gripping.
In this embodiment, the steering engine is disposed on the fuselage 1, when the barrel-jet unmanned aerial vehicle is in a folded state, the left front wing 21 and the right front wing 22 of the barrel-jet unmanned aerial vehicle are folded to be parallel to the fuselage 1, and as the steering engine is not disposed on the left front wing 21 and the right front wing 22, when the left front wing 21 and the right front wing 22 are folded together, the left front wing 21 and the right front wing 22 can be attached closer in the thickness direction of the unmanned aerial vehicle, so that the thickness dimension of the unmanned aerial vehicle in the folded state is reduced; in the process that the unmanned aerial vehicle is unfolded from the folding state to the unfolding state, the left front wing 21 and the right front wing 22 are independently unfolded, so that the acting force required by the unmanned aerial vehicle from the folding state to the unfolding state is reduced; after the front wing 2 is unfolded, the left rocker arm 214 and the left pressing sheet 212 are matched to clamp the left aileron 211, when the angle of the left aileron 211 needs to be adjusted, the left steering engine 213 drives the left rocker arm 214 to apply acting force to the left aileron 211, the left aileron 211 changes the angle, meanwhile, the left pressing sheet 212 elastically deforms, when the angle of the aileron needs to be adjusted again, the left steering engine 213 drives the left rocker arm 214 to be far away from the left aileron 211, under the action of the recovery deformation of the left pressing sheet 212, the left aileron 211 changes the angle, the adjustment of the angle of the right aileron 221 is realized in the same way, and the flying gesture of the unmanned aerial vehicle is controlled by changing the angles of the left aileron 211 and the right aileron 221.
As a preferred embodiment, further, on the basis of the above manner, a groove 11 is provided on the body 1, and the groove 11 is used for accommodating the left steering engine 213 and the right steering engine 223.
The arrangement of the groove 11 approaches the positions of the left steering engine 213 and the right steering engine 223 to the fuselage 1, so that the thickness dimension of the unmanned aerial vehicle is further reduced when the left front wing 21 and the right front wing 22 are in a folded state.
In a preferred embodiment, in addition to the above-described embodiment, the left front wing 21 is located above the right front wing 22, a left concave portion 2111 is provided at a position of the left flap 211 contacting the left rocker arm 214, a right convex portion 2211 is provided at a position of the right flap 221 contacting the right rocker arm 224, and a surface of the left concave portion 2111 contacting the left rocker arm 214 is on the same level as a surface of the right convex portion 2211 contacting the right rocker arm 224.
Because the height difference of the left front wing 21 and the right front wing 22 in the thickness direction of the unmanned aerial vehicle causes the length difference of the left rocker arm 214 and the right rocker arm 224 to be larger, the control of the left aileron 211 and the right aileron 221 is further influenced, the contact surface of the left concave table 2111 and the left rocker arm 214 and the contact surface of the right boss 2211 and the right rocker arm 224 are arranged on the same horizontal plane, and the arrangement is such that the lengths of the left rocker arm 214 and the right rocker arm 224 can be the same, so that the control of the left aileron 211 and the right aileron 221 is more balanced, and the control of the flight attitude of the unmanned aerial vehicle is facilitated.
As a preferred embodiment, further on the above manner, a left concave table inclined surface 2112 is provided at the periphery of the left concave table 2111, the left concave table inclined surface 2112 is inclined inwards from top to bottom, a right boss inclined surface 2212 is provided at the periphery of the right boss 2211, the right boss inclined surface 2212 is inclined outwards from top to bottom, and the left concave table inclined surface 2112 is adapted to the right boss inclined surface 2212.
The arrangement of the left concave platform inclined plane 2112 and the right boss inclined plane 2212 ensures that the left front wing 21 and the right front wing 22 can be effectively unfolded, and when the left concave platform inclined plane 2112 contacts with the right boss inclined plane 2212 in the unfolding process of the left front wing 21 and the right front wing 22, the left concave platform inclined plane 2112 and the right boss inclined plane 2212 relatively slide in the unfolding direction, so that the left concave platform 2111 can cross the right boss 2211, the unfolding of the left front wing 21 and the left aileron 211 is realized, and the unfolding of the right front wing 22 and the right aileron 221 is synchronously realized.
In a preferred embodiment, in addition to the above embodiments, the front wing 2 and the rear wing 3 are both mounted below the fuselage 1, the left front wing 21 and the right front wing 22 are foldable toward the tail of the fuselage 1 with the fuselage 1 as a center, the rear wing 3 includes a left rear wing 31 and a right rear wing 32, and the left rear wing 31 and the right rear wing 32 are foldable toward the head of the fuselage 1 with the fuselage 1 as a center.
By adopting the folding mode, the moment direction when the front wing 2 is unfolded and the moment direction when the rear wing 3 is unfolded are just opposite to each other when the fuselage 1 is unfolded, so that the unfolding processes of the front wing 2 and the rear wing 3 of the unmanned aerial vehicle are more balanced, and the stability of the unmanned aerial vehicle in the launching process is improved.
The above embodiments are only for illustrating the present invention and not for limiting the technical solutions described in the present invention, and although the present invention has been described in detail in the present specification with reference to the above embodiments, the present invention is not limited to the above specific embodiments, and thus any modifications or equivalent substitutions are made to the present invention; all technical solutions and modifications thereof that do not depart from the spirit and scope of the invention are intended to be included in the scope of the appended claims.
Claims (4)
1. A section of thick bamboo penetrating formula unmanned aerial vehicle, its characterized in that: the wing structure comprises a fuselage, a front wing arranged near the front end of the fuselage, a rear wing arranged near the tail end of the fuselage, a vertical fin and a propeller assembly arranged at the tail end of the fuselage, wherein the front wing, the rear wing, the vertical fin and the propeller assembly can be folded and unfolded by taking the fuselage as the center;
the front wing comprises a left front wing and a right front wing, a left aileron is rotatably arranged on the left front wing, a left pressing piece is arranged between the left front wing and the left aileron, the left pressing piece has elasticity, one end of the left pressing piece is fixedly connected with the left front wing, the other end of the left pressing piece is abutted with the left aileron, a left steering engine is arranged on the machine body, a left rocker arm is arranged on the left steering engine, one end of the left rocker arm is rotatably connected with the left steering engine, the other end of the left rocker arm is abutted with the left aileron, and the left pressing piece and the left rocker arm form clamping on the left aileron;
the right front wing is rotatably provided with a right aileron, a right pressing sheet is arranged between the right front wing and the right aileron and is elastic, one end of the right pressing sheet is fixedly connected with the right front wing, the other end of the right pressing sheet is abutted to the right aileron, the machine body is provided with a right steering engine, the right steering engine is provided with a right rocker arm, one end of the right rocker arm is rotatably connected with the right steering engine, the other end of the right rocker arm is abutted to the right aileron, and the right pressing sheet is matched with the right rocker arm to clamp the right aileron;
The left front wing is located above the right front wing, a left concave table is arranged at the position, in contact with the left rocker arm, of the left aileron, a right boss is arranged at the position, in contact with the right rocker arm, of the right aileron, and the surface, in contact with the left rocker arm, of the left concave table is on the same horizontal plane as the surface, in contact with the right boss and the right rocker arm, of the left concave table.
2. A barrel-fire unmanned aerial vehicle as claimed in claim 1, wherein: the machine body is provided with a groove, and the groove is used for accommodating the left steering engine and the right steering engine.
3. A barrel-fire unmanned aerial vehicle as claimed in claim 2, wherein: the periphery of left concave station is provided with left concave station inclined plane, left concave station inclined plane is from top to bottom inwards inclined, the periphery of right boss is provided with right boss inclined plane, right boss inclined plane is from top to bottom outwards inclined, left concave station inclined plane with right boss inclined plane adaptation.
4. A barrel-fire unmanned aerial vehicle as claimed in claim 3, wherein: the front wing and the rear wing are both arranged below the fuselage, the left front wing and the right front wing can be folded towards the tail direction of the fuselage by taking the fuselage as the center, the rear wing comprises a left rear wing and a right rear wing, and the left rear wing and the right rear wing can be folded towards the head direction of the fuselage by taking the fuselage as the center.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411095223.0A CN118618656B (en) | 2024-08-12 | 2024-08-12 | Barrel-jet unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411095223.0A CN118618656B (en) | 2024-08-12 | 2024-08-12 | Barrel-jet unmanned aerial vehicle |
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| CN118618656A CN118618656A (en) | 2024-09-10 |
| CN118618656B true CN118618656B (en) | 2024-10-29 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151275A (en) * | 2009-09-09 | 2015-12-16 | 威罗门飞行公司 | Elevon control system |
| CN113120222A (en) * | 2021-05-24 | 2021-07-16 | 中国人民解放军国防科技大学 | Foldable wing structure |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204433058U (en) * | 2015-01-22 | 2015-07-01 | 曹启武 | The full landform in low latitude collapsible scouting operation one unmanned plane |
| CN108688793B (en) * | 2018-07-27 | 2023-11-24 | 中国工程物理研究院总体工程研究所 | Folding and unfolding mechanism for wings of barrel-type launching unmanned aerial vehicle |
| CN109987217A (en) * | 2019-04-29 | 2019-07-09 | 北京驰宇空天技术发展有限公司 | Folding wings unmanned plane and its launching technique |
| CN212685894U (en) * | 2020-04-28 | 2021-03-12 | 北京航天嘉诚精密科技发展有限公司 | Guide slot type fin folding mechanism |
| CN113353238A (en) * | 2021-06-24 | 2021-09-07 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing folding mechanism and unmanned aerial vehicle |
| CN114148506B (en) * | 2021-12-06 | 2023-10-13 | 浙江大学 | Foldable variant unmanned aerial vehicle and control method thereof |
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- 2024-08-12 CN CN202411095223.0A patent/CN118618656B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151275A (en) * | 2009-09-09 | 2015-12-16 | 威罗门飞行公司 | Elevon control system |
| CN113120222A (en) * | 2021-05-24 | 2021-07-16 | 中国人民解放军国防科技大学 | Foldable wing structure |
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