CN217706249U - Novel unmanned aerial vehicle capable of being stored in portable mode and taking off in catapult mode - Google Patents

Abstract

The utility model discloses a novel unmanned aerial vehicle that can portablely accomodate and can launch and take off relates to unmanned aerial vehicle's technical field, the utility model discloses to provide the solution of optimizing more in this problem of unmanned aerial vehicle folding to adapt to more and carry and launch canister transmission. The utility model comprises a body, a foldable wing, a foldable empennage and a foldable propeller, wherein the upper surface of the body is provided with a concave platform, the root part of the wing is rotatably arranged in the concave platform, and the wing is accommodated in the concave platform when being folded; the empennage is connected with the machine body through a rotating structure; the empennage is attached to two sides of the fuselage when folded and is in an inverted V shape when unfolded; the blades of the propeller are hinged and can be turned over towards the axial direction of the propeller, and the machine body is provided with a containing groove for containing the blades of the propeller.

Description

Novel unmanned aerial vehicle capable of being stored in portable mode and catapult-launching

Technical Field

The utility model relates to an unmanned aerial vehicle's technical field, concretely relates to novel unmanned aerial vehicle that can portably accomodate and catapult take-off.

Background

Launching of fixed wing drones takes many forms, such as takeoff via a runway, takeoff using a catapult mechanism, or takeoff using a launch canister. The launching of the launching tube has the advantages of miniaturization, integration, high-density launching and the like, and the launching can be carried out by utilizing initiating explosive devices, pneumatics and other modes. But the manner of launching with a launch canister requires that the aircraft must be foldable. At present, unmanned aerial vehicle's beta structure scheme among the prior art has very big optimization space in addition, because unmanned aerial vehicle can be folded the degree more big, the launching tube just can be done the less, all be profitable to launching tube and unmanned aerial vehicle's transportation. To this problem, the utility model provides a new solution.

SUMMERY OF THE UTILITY MODEL

The utility model provides a novel unmanned aerial vehicle capable of being stored in a portable mode and taking off in a catapult mode, which comprises a body, a foldable wing, a foldable empennage and a foldable propeller, wherein a concave platform is arranged on the upper surface of the body, the root of the wing is rotatably arranged in the concave platform, and the wing is stored in the concave platform when being folded; the empennage is connected with the machine body through a rotating structure; the empennage is attached to two sides of the fuselage when folded and is in an inverted V shape when unfolded; the propeller is hinged and can be turned over towards the axial direction of the propeller, and the machine body is provided with a containing groove for containing the propeller.

The utility model discloses a further set up to: the tail of the fuselage is in a contracted arrangement to reduce the width.

The utility model discloses a further set up to: the empennage comprises a wing root and a full rudder, the wing root is connected with the fuselage through the rotating structure, and a driving structure used for controlling the rotation of the full rudder is arranged on the empennage.

The utility model discloses a further set up to: the rotating structure comprises a flange plate, a mandrel, a sleeve and a torsional spring, the flange plate is fixedly connected with the mandrel, the sleeve is sleeved on the mandrel, and the torsional spring is sleeved on the sleeve, and two ends of the torsional spring are respectively fixedly connected with the flange plate and the sleeve; and the two ends of the flange plate and the sleeve which deviate from each other are respectively connected with the wing root and the machine body.

The utility model discloses a further set up to: the mandrel is obliquely arranged in the machine body, and the surface of the flange plate, which is attached to the wing root, is also obliquely arranged.

The utility model discloses a further set up to: the driving structure comprises a steering engine, a connecting arm and a rotating shaft; the wing root is provided with a mounting groove, and the steering engine and the connecting arm are both arranged in the mounting groove; the rotating shaft is fixedly connected with the full rudder and extends into the mounting groove; the rocker arm of the steering engine is fixedly connected with one end of the connecting arm, and the other end of the connecting arm is fixedly connected with one end of the rotating shaft.

The utility model discloses a further set up to: the wings are telescopic wings.

The utility model discloses a further set up to: the wing comprises an inner wing and an outer wing, wherein the outer wing is sleeved outside the inner wing and can slide relative to the inner wing; the wing is internally provided with a telescopic opposite-inserting wing beam, and two ends of the wing beam are fixedly connected with two ends of the outer wing and the inner wing which deviate from each other respectively; an extension spring is further arranged in the opposite insertion wing beam, and two ends of the extension spring are fixedly connected with two ends of the opposite insertion wing beam respectively; and a limiting rope is further arranged in the wing, and two ends of the limiting rope are respectively fixedly connected with two ends of the outer wing and two ends of the inner wing which deviate from each other.

The utility model discloses a further set up to: the wing lock is provided with an unlocking convex part and a limiting convex part which extend out of the inner wing; the wing lock is movably arranged and can be pressed into the inner wing by external force; the limiting convex part is triangular, the unlocking convex part is rectangular, and a bayonet matched with the limiting convex part is required to be arranged on the outer wing; when the outer wing retracts, the wing lock is limited in that the outer wing is pressed into the inner wing, the wing lock resets when the limiting protruding part is opposite to the bayonet, and the limiting protruding part is clamped into the bayonet so as to limit the extension of the outer wing; when the wing rotates for 90 degrees and is unfolded, the unlocking protrusion is abutted against the fuselage and enables the wing lock to be pressed into the inner wing.

The utility model has the advantages that:

after whole unmanned aerial vehicle is folding, not only reduced the size, through the reasonable transformation of fuselage, reduced the arch of external profile or irregular shape for whole unmanned aerial vehicle can be accomodate by a square rectangle box, portable. In addition, the shape of the launching tube is more regular, so that the launching tube can be better matched with a square launching tube, and the size of the launching tube can be smaller.

Drawings

Fig. 1 is a three-dimensional structure diagram of the folding state of the unmanned aerial vehicle in the present invention;

fig. 2 is a left side view of the folded state of the unmanned aerial vehicle of the present invention;

fig. 3 is a top view of the folded state of the unmanned aerial vehicle of the present invention;

fig. 4 is a three-dimensional structure diagram of the unmanned aerial vehicle in the deployed state;

FIG. 5 is an enlarged view of a portion of FIG. 4 at A;

fig. 6 is a left side view of the unmanned aerial vehicle in the deployed state;

fig. 7 is a schematic view of a rotating structure of the middle rear wing of the present invention;

fig. 8 is a schematic view of a driving structure of the full rudder according to the present invention;

fig. 9 is a schematic structural diagram of a middle telescopic wing of the present invention;

FIG. 10 is an enlarged view of a portion of FIG. 9 at A;

fig. 11 is a partial enlarged view at B in fig. 9;

fig. 12 is a schematic structural view of a wing lock according to a preferred embodiment of the present invention.

Reference numerals are as follows: 1. a body; 11. a storage groove; 12. a concave platform; 2. an airfoil; 21. an inner wing; 22. an outer wing; 23. oppositely inserting wing beams; 24. an extension spring, 25, a limit rope; 26. a wing lock; 261. an unlocking protrusion; 262. a limit protrusion part; 3. a tail wing; 31. a wing root; 32. steering the whole rudder; 33. mounting grooves; 4. a propeller; 5. a rotating structure; 51. a flange plate; 52. a sleeve; 53. a mandrel; 54. a torsion spring; 6. a drive structure; 61. a steering engine; 62. a connecting arm; 63. a rotating shaft.

Detailed Description

Preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention, and are not intended to limit the scope of the present invention.

Referring to fig. 1-8, the utility model provides a novel unmanned aerial vehicle that can portably accomodate and can launch and take off, including fuselage 1, be provided with wing 2, fin 3 and screw 4 on the fuselage 1.

The upper surface of fuselage 1 is provided with concave station 12, and the root of two wings 2 all rotates to be set up in concave station 12. The two wings 2 can be folded towards the tail direction, and when the two wings 2 are folded, the two wings are overlapped and accommodated in the concave platform 12. The depth of the recessed platform 12 is consistent with the thickness of the two wings 2, so that the two wings 2 do not protrude upwards from the recessed platform 12 after being folded. Regarding the unfolding and folding structure of the wing 2, which belongs to the prior art, reference may be made to patent No. CN103693188A or other technical solutions, and in the prior art, there is an example of applying a fixed-wing aircraft to launch a launch canister, so the detailed structure is not described in detail.

On this basis, the wing 2 of the present application can also be set as a telescopic wing 2 (a registered wing). After the wings 2 are unfolded, a larger area of the wings 2 can be obtained, so that more lift force can be obtained, and the airplane can obtain more excellent flight performance; and the wing 2 is retracted without affecting the folding. A preferred wing 2 telescoping solution is described here:

referring in detail to fig. 9-11, the wing 2 may be divided into an inner wing 21 and an outer wing, the inner wing 21 being provided with aileron control surfaces and the outer wing being non-aileron control surfaces. The inner wing 21 and the outer wing are both hollow, the outer wing is sleeved outside the inner wing 21, and the inner wing 21 and the outer wing can slide relatively. Three telescopic opposite insertion wing spars 23 are arranged inside the wing 2. This pair of insertion spars 23 can be understood as telescopic rods, but it also has a supporting effect on the wing 2, with its two ends fixedly connected to the two ends respectively facing away from the outer wing and the inner wing 21. In addition, extension springs 24 are further provided in the opposite insertion wing beams 23, and both ends of the extension springs 24 are fixedly connected to both ends of the opposite insertion wing beams 23, respectively. When the opposite insertion wing beam 23 is in a retracted state, the extension spring 24 is in a compressed state, so that in an unconstrained state, the outer wing extends under the action of the extension spring 24 to deploy the whole wing 2. Almost double area of the wing 2 can be obtained after the wing is unfolded, and the space utilization rate is high. In order to limit the expansion range of the wing 2, a limiting rope 25 is further arranged in the wing 2, and two ends of the limiting rope 25 are fixedly connected with two ends of the outer wing and two ends of the inner wing, which are deviated from the outer wing and the inner wing 21 respectively, so that the extending distance of the outer wing is limited.

With regard to the relative locking of the outer wing and the inner wing 21, a wing lock 26 is provided in the inner wing 21. The wing lock 26 is provided with an unlocking protrusion 261 and a stopper protrusion 262, both protruding from the inner wing 21 to the outside of the inner wing 21. However, the wing lock 26 is movably installed and can be pressed into the inner wing 21 by an external force. For example, a spring connected to the wing lock 26 is provided in the inner wing 21, or one end of the limit protrusion 262 is hinged in the inner wing 21 and is provided with the torsion spring 54, or the wing lock 26 itself is made of spring steel and is configured as shown in fig. 12, as long as the wing lock 26 can be pressed into the inner wing 21 and can be reset, and the related technical solutions are many and conventional and are not specifically shown in the drawings. The stopper protrusion 262 is triangular, and the unlocking protrusion 261 is rectangular. The outer wing is required to be provided with a bayonet matched with the limit protrusion 262. When the outer wing retracts, the wing lock 26 is limited by the outer wing pressed into the inner wing 21, when the limiting protruding part 262 faces the bayonet, the wing lock 26 resets, the limiting protruding part 262 is clamped into the bayonet, the outer wing is limited from extending out, and locking is achieved. Specifically, the unlocking process is that, when the wing 2 is rotated by 90 ° and deployed, the unlocking protrusion 261 of the wing lock 26 interferes with the body 1 and causes the wing lock 26 to be pressed into the inner wing 21. The outer wing is now unconstrained and the entire wing 2 is extended open by the extension spring 24.

The empennage 3 is arranged at the tail part of the fuselage 1. The two empennages 3 are symmetrically arranged, and the empennages 3 are inverted V-shaped in the unfolded state; the tail wings 3 are attached to both sides of the body 1 in a folded state. In order not to let two fin 3 influence whole unmanned aerial vehicle's maximum width value, so the afterbody of fuselage 1 is the shrink setting, has also reduced the width of fuselage 1 afterbody promptly, just can not influence whole unmanned aerial vehicle's width after two fin 3 are folding like this.

The specific structure of the empennage 3 is as follows: the tail 3 comprises a wing root 31 and a full rudder 32. The wing root 31 is connected to the fuselage 1 via the swivel 5. The tail fin 3 is also provided with a driving structure 6 for controlling the rotation of the whole rudder 32, so that the flight attitude of the airplane can be controlled.

Turning to fig. 7 in detail, the rotating structure 5 comprises a flange 51, a spindle 53, a sleeve 52 and a torsion spring 54. The flange 51 is connected to the wing root 31 by bolts, and the core shaft 53 is welded perpendicularly to the center of the other side surface of the flange 51. The sleeve 52 is sleeved on the mandrel 53, a flange is integrally arranged at one end of the sleeve 52, which is far away from the flange plate 51, three through holes are formed in the flange, and the through holes are used for being connected with the machine body 1 through bolts. On the side of the sleeve 52 facing away from the flange 51, a nut is provided which is screwed onto the spindle 53 and thus prevents the sleeve 52 from being removed from the spindle 53. The torsion spring 54 is sleeved outside the sleeve 52, and two ends of the torsion spring 54 are respectively fixedly connected with the flange 51 and the sleeve 52 in a welding manner. When the tail fin 3 is mounted on the fuselage 1, the mandrel 53 is inclined and the surface of the fin base 31 that abuts the flange 51 is also inclined, so that when the tail fin 3 is rotated about the mandrel 53, it can assume an inverted "V" shape in the deployed state and can abut the fuselage 1 in the folded state. When the rear wing 3 is attached to the body 1, the torsion spring 54 is in a twisted state. So unmanned aerial vehicle launches the back from launching tube, fin 3 can be opened automatically.

The driving structure 6 comprises a steering engine 61, a connecting arm 62 and a rotating shaft 63. The wing root 31 is provided with a mounting groove 33, and the steering engine 61 and the connecting arm 62 are both arranged in the mounting groove 33. The rotating shaft 63 is fixedly connected with the full rudder 32 and extends into the mounting slot 33, so that the full rudder 32 can rotate around the rotating shaft 63 and the wing root 31 relatively. The steering engine 61 is fixed in the mounting groove 33 through a bolt, and a rocker arm of the steering engine 61 is fixedly connected with one end of the connecting arm 62. The other end of the connecting arm 62 is fixedly connected with one end of the rotating shaft 63. When the steering engine 61 acts, the full rudder 32 can be driven to rotate, and the attitude of the airplane is controlled.

The structure of the tail fin 3 reduces the volume required by the arrangement of an elevator and a rudder in the past, also reduces the structural quantity, and is more convenient to fold and store.

Referring to fig. 5 in detail, the motor driving the propeller 4 is installed at the extreme end of the rear portion of the body 1, and the propeller 4 is directly installed on the output shaft of the motor. The propeller 4 is foldable, the blades being hingedly arranged and being foldable towards the axial direction of the propeller 4. Such propeller 4-related technology can be referred to patent publication No. CN108202864A, which discloses a propeller 4 whose blades can be turned. A receiving groove 11 for receiving blades of the propeller 4 is provided at a rear portion of the body 1. When the propeller 4 is in a folded state, the blades are all located in the accommodating groove 11, so that the outer contour of the unmanned aerial vehicle is not affected, and the folding of the wing 2 and the empennage 3 is not affected. When unmanned aerial vehicle transmission and screw 4 rotatory back, can make the paddle keep the state of expanding under the effect of centrifugal force.

To sum up, whole unmanned aerial vehicle is folding, has not only reduced the size, through the reasonable transformation of fuselage 1, has reduced the arch of external profile or irregularly shaped for whole unmanned aerial vehicle can be accomodate by the rectangle box of a square, portable. In addition, the launching tube can be better matched with the launching tube due to the more regular shape, and the size of the launching tube can be smaller.

While the invention has been described with reference to a preferred embodiment, various modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention, and particularly, various features shown in the various embodiments may be combined in any combination as long as there is no structural conflict. The present invention is not intended to be limited to the particular embodiments disclosed herein, but rather to include all embodiments falling within the scope of the appended claims.

In the description of the present invention, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like, which indicate directions or positional relationships, are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Furthermore, it should be noted that, in the description of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; 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 meaning of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The terms "comprises," "comprising," or any other similar term are intended to cover a non-exclusive inclusion, such that a process, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, article, or apparatus.

So far, the technical solution of the present invention has been described with reference to the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, a person skilled in the art can make equivalent changes or substitutions to the related technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

Claims (9)

1. The utility model provides a novel unmanned aerial vehicle that can portablely accomodate and can launch and take off, includes fuselage (1), folding wing (2), folding fin (3) and folding screw (4), its characterized in that:

a concave platform (12) is arranged on the upper surface of the fuselage (1), the root of the wing (2) is rotatably arranged in the concave platform (12), and the wing (2) is accommodated in the concave platform (12) when being folded;

the empennage (3) is connected with the fuselage (1) through a rotating structure (5);

the empennage (3) is attached to two sides of the fuselage (1) when folded and is inverted V-shaped when unfolded;

the propeller (4) is hinged and can be turned over towards the axial direction of the propeller (4), and the machine body (1) is provided with a containing groove (11) for containing the propeller (4).

2. The novel unmanned aerial vehicle capable of being portably stored and catapulted for takeoff according to claim 1, wherein: the tail part of the machine body (1) is arranged in a contracting mode to reduce the width.

3. The novel portably stowable and catapultable drone of claim 1, further comprising: the empennage (3) comprises a wing root (31) and a full rudder (32), wherein the wing root (31) passes through the rotating structure (5) and the fuselage (1) are connected, and the empennage (3) is provided with a rotating driving structure (6) for controlling the full rudder (32).

4. The novel portably stowable and catapultable drone of claim 3, further comprising: the rotating structure (5) comprises a flange (51), a mandrel (53), a sleeve (52) and a torsion spring (54), the flange (51) is fixedly connected with the mandrel (53), the sleeve (52) is sleeved on the mandrel (53), the torsion spring (54) is sleeved on the sleeve (52), and two ends of the torsion spring are fixedly connected with the flange (51) and the sleeve (52) respectively; the two ends of the flange plate (51) and the sleeve (52) which are deviated from each other are respectively connected with the wing root (31) and the machine body (1).

5. The novel unmanned aerial vehicle capable of being portably stored and catapulted for takeoff according to claim 4, wherein: the mandrel (53) is arranged in the fuselage (1) in an inclined manner, and the surface of the wing root (31) which is attached to the flange (51) is also arranged in an inclined manner.

6. The novel portably stowable and catapultable drone of claim 3, further comprising: the driving structure (6) comprises a steering engine (61), a connecting arm (62) and a rotating shaft (63); a mounting groove (33) is formed in the wing root (31), and the steering engine (61) and the connecting arm (62) are both arranged in the mounting groove (33); the rotating shaft (63) is fixedly connected with the full rudder (32) and extends into the mounting groove (33); the rocker arm of the steering engine (61) is fixedly connected with one end of the connecting arm (62), and the other end of the connecting arm (62) is fixedly connected with one end of the rotating shaft (63).

7. The novel unmanned aerial vehicle capable of being portably stored and catapulted for takeoff according to claim 1, wherein: the wings (2) are telescopic wings (2).

8. The novel portably stowable and ejectable takeoff unmanned aerial vehicle of claim 7, wherein: the wing (2) comprises an inner wing and an outer wing (22), the outer wing (22) is sleeved outside the inner wing and can slide relative to the inner wing;

a telescopic opposite-insertion wing beam (23) is arranged in the wing (2), and two ends of the telescopic opposite-insertion wing beam are fixedly connected with two ends of the outer wing (22) and the inner wing which deviate from each other respectively;

an extension spring is further arranged in the oppositely inserted wing beam (23), and two ends of the extension spring are fixedly connected with two ends of the oppositely inserted wing beam (23) respectively;

and a limiting rope is further arranged in the wing (2), and two ends of the limiting rope are respectively fixedly connected with two ends of the outer wing (22) and two ends of the inner wing which deviate from each other.

9. The novel portably stowable and catapultable take-off drone of claim 8, wherein: a wing lock (26) is arranged in the inner wing, and the wing lock (26) is provided with an unlocking convex part (261) and a limiting convex part (262) which extend out of the inner wing;

the wing lock (26) is movably arranged and can be pressed into the inner wing by external force;

the limiting convex part (262) is triangular, the unlocking convex part (261) is rectangular, and a bayonet matched with the limiting convex part (262) needs to be arranged on the outer wing (22);

when the outer wing (22) retracts, the wing lock (26) is limited by the outer wing (22) being pressed into the inner wing, the limiting projection (262) is opposite to the bayonet, then the wing lock (26) is reset, the limiting projection (262) is clamped into the bayonet, and then the outer wing (22) is limited from extending;

when the wing (2) rotates for 90 degrees and is unfolded, the unlocking protrusion (261) collides with the fuselage (1) and enables the wing lock (26) to be pressed into the inner wing.

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