Novel freight gliding unmanned aerial vehicle

Abstract

The utility model relates to the field of aircrafts, and particularly discloses a novel freight gliding unmanned aerial vehicle which is characterized in that a fuselage is of a box structure, movable parts of lock catches are mounted on two outer sides of the fuselage, an upper plate cover of the fuselage is provided with fixed parts of the lock catches, and the fixed parts correspond to the movable parts in position; the front end and the rear end of the upper surface of the upper plate cover are each provided with a wing rotating shaft, the two wing rotating shafts are each provided with two wings from top to bottom, and the four wings are oppositely arranged in a staggered mode from top to bottom. The gliding unmanned aerial vehicle is provided with two sets of folding wings, the two sets of wings are located on the same side, in order to reduce the occupied space after folding and avoid position interference after the front set of wings and the rear set of wings are folded, a split type folding wing structure is adopted, meanwhile, structural equipment is convenient to arrange, and an integrated folding structure is only suitable for aircrafts which are small in weight and easy to design.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aircraft, especially relates to a novel freight gliding unmanned plane. BACKGROUND

[0002] In view of the multi-point distribution of emergency material supply and the demand of accurate delivery, the traditional gliding freight unmanned plane has the problems of low precision, low efficiency and high cost in material delivery mode, and the distance of transport aircraft to the delivery point is relatively far, which not only limits the application effect of the unmanned plane in the field of emergency rescue, logistics distribution and the like, but also affects the commercialization process, and the carrying capacity of the traditional unmanned plane is small, and only a small amount of materials can be carried each time, and multiple round trips are needed to complete the large-scale material delivery task. UTILITY MODEL CONTENT

[0003] The utility model provides a novel freight gliding unmanned plane, does not need artificial control after delivery, and the airfoil can be rapidly unfolded, the unmanned plane is converted into flight mode, and is automatically flown to the specified delivery point according to the planned route.

[0004] To solve the above problems, the utility model provides the technical scheme as follows: a novel freight gliding unmanned plane is provided with a fuselage, the fuselage is a box structure, movable parts of a lock catch are installed on the two outer sides of the fuselage, the upper plate cover of the fuselage is provided with fixed parts of the lock catch, and the positions of the fixed parts and the movable parts correspond to each other, the front and rear ends of the upper surface of the upper plate cover are respectively provided with wing rotating shafts, two wing rotating shafts are provided with two wings from top to bottom, and four wings are oppositely and staggeredly arranged from top to bottom.

[0005] The wing rotating shaft includes a wing base, a lower wing mounting joint, an upper wing mounting joint, a torsional spring assembly and a cover plate, the wing base is fixed on the upper plate cover through first screws, the lower wing mounting joint is sleeved on the outer wall of the supporting shaft of the wing base and is fixed with the wing base, one end of the torsional spring assembly is sleeved in the lower wing mounting joint, the other end of the torsional spring assembly is sleeved in the upper wing mounting joint, and the cover plate is fixed on the top of the supporting shaft through second screws.

[0006] The torsional spring assembly includes a torsional spring body and a torsional spring outer cylinder, the torsional spring body is sleeved in the torsional spring outer cylinder, the outer wall of the torsional spring outer cylinder is provided with first and second limiting blocks from top to bottom, the top of the torsional spring body is matched with the upper stop groove in the upper wing mounting joint, the bottom of the torsional spring body is matched with the lower stop groove in the lower wing mounting joint, the first limiting block is matched with the downward extension of the first stop pin, and the second limiting block is matched with the upward extension of the second stop pin.

[0007] Preferably, the wing rotating shaft further comprises a first wing rolling bearing and a second wing rolling bearing; an outer wall of an outer shaft of the first wing rolling bearing is fixed to an inner wall of the lower wing mounting joint, and an inner shaft of the first wing rolling bearing is fixed to a bottom of the torsional spring outer cylinder; an outer wall of an outer shaft of the second wing rolling bearing is fixed to an inner wall of the upper wing mounting joint, and an inner shaft of the second wing rolling bearing is fixed to a top of the torsional spring outer cylinder.

[0008] Preferably, the outer convex part of the upper wing mounting joint is provided with a first fixing hole, a first stop pin is passed through the wing and the first fixing hole, and the wing is fixed to the upper wing mounting joint; the outer convex part of the lower wing mounting joint is provided with a second fixing hole, a second stop pin is passed through the wing and the second fixing hole, and the wing is fixed to the lower wing mounting joint.

[0009] Preferably, the fuselage front and rear can be assembled with the fairing and the tail vertebra of the rear extension end.

[0010] The beneficial effects of the prior art are that, by using the above scheme, the wing folding mechanism of the gliding unmanned aerial vehicle adopts a split type configuration, which is different from the traditional integrated wing folding mechanism, the upper and lower folding wings can be adjusted according to the height requirement of the folding wing, the gliding unmanned aerial vehicle has two groups of folding wings, and the two groups of wings are located on the same side; in order to reduce the occupied space after folding, the folding wings are folded to the middle at the same time, in order to avoid the position interference of the front and rear two groups of wings after folding, the split type folding wing configuration is adopted, and the split type folding wing mechanism is suitable for large weight aircraft, and is convenient for arranging structural equipment, and the integrated folding structure is only suitable for small weight and simple designed aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0011] In order to more clearly illustrate the technical scheme in the embodiments or the prior art, the drawings needed to be used in the following embodiment or prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the utility model, and other drawings can be obtained by those skilled in the art without creative labor.

[0012] Fig. 1 It is a whole structure wing folding schematic view of the utility model;

[0013] Fig. 2 It is a whole structure wing folding schematic view of the utility model;

[0014] Fig. 3 It is a wing rotating shaft structure schematic view of the utility model;

[0015] According to the above diagram: 1. Fuselage; 2. Upper plate cover; 3. Fairing; 4. Tail cone; 5. Vertical tail; 6. Wing; 7. Wing shaft; 8. Supplies; 9. Wing base; 10. First screw; 11. Second stop pin; 12. Lower wing mounting joint; 13. First wing rolling bearing; 14. Torsion spring body; 15. Torsion spring outer tube; 16. Upper wing mounting joint; 17. Cover; 18. Second screw; 19. Second wing rolling bearing; 20. First stop pin. DETAILED DESCRIPTION

[0016] To facilitate understanding of the present invention, the present invention is described in more detail below with reference to the accompanying drawings and specific embodiments. The accompanying drawings illustrate preferred embodiments of the present invention. However, the present invention can be implemented in many different forms and is not limited to the embodiments described in this specification. Rather, these embodiments are provided to provide a more thorough and comprehensive understanding of the disclosure of the present invention.

[0017] It should be noted that when an element is referred to as being "fixed to" another element, it may be directly attached to the other element or there may be an intermediate element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be an intermediate element. The terms "fixed," "integrally formed," "left," "right," and similar expressions used in this specification are for illustrative purposes only. In the drawings, elements with similar structures are indicated by the same reference numerals.

[0018] Unless otherwise defined, all technical and scientific terms used in this specification have the same meanings as those commonly understood by those skilled in the art in the art of the present invention. The terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present invention.

[0019] like Figs. 1-3 As shown, an embodiment 1 of the present invention: a new cargo gliding drone, the fuselage 1 is a box structure, the movable parts of the lock are installed on the two outer sides of the fuselage 1, the upper cover 2 of the fuselage 1 is provided with a fixed part of the lock, and the position of the fixed part corresponds to the position of the movable part; wing shafts 7 are respectively provided at the front and rear ends of the upper surface of the upper cover 2, and two of the wing shafts 7 are provided with two wings 6 from top to bottom, and the four wings 6 are relatively staggered from top to bottom.

[0020] It is to be noted that the gliding cargo unmanned aerial vehicle is composed of a fuselage box, a fuselage 1 upper plate cover 2, a nose fairing 3, a tail spine 4, a vertical tail 5, a wing 6, a wing rotating shaft 7 and goods 8. The fuselage 1 is a rectangular box, and the wing 6 and on-board equipment are placed inside; the fuselage 1 upper plate cover 2 is connected with two front and rear wing rotating shafts 7, and can be fixed and separated with the fuselage 1 box; the nose fairing 3 and the tail spine 4 are attached parts, and can be respectively installed at the front and rear of the fuselage 1 box; the vertical tail 5 can be installed on the tail spine 4; the wing 6 is four pieces, and is respectively connected with the front and rear wing rotating shafts 7 and folded and placed in the fuselage 1 box; the goods 8 are supply goods, and can be placed in the fuselage 1 box after the fuselage 1 upper plate cover 2 is opened and turned over.

[0021] Before the gliding unmanned aerial vehicle is unfolded, it is a box with a length of 2650 mm, a height of 600 mm and a width of 600 mm, wherein the wing 6 is divided into front and rear serial wings 6, and the wing 6 can be folded through the rotating shaft. In the task preparation stage, the two groups of wings 6 are folded and placed in the box together with on-board equipment. The main equipment of the aircraft is placed through the integrated wing rotating shaft 7 position, that is, the whole aircraft realizes the minimization of the unmanned aerial vehicle storage space through the structure, space and overall arrangement design, realizes the rapid transfer and delivery, in the task execution stage, the lock buckle of the upper cover plate 17 of the fuselage 1 box is unlocked, the upper cover plate 17 is turned over together with the wing 6 and the rotating shaft, and is fixed on the fuselage 1 box through the lock buckle again, the on-board equipment is connected and powered on, that is, the delivery preparation is completed. After delivery, the folded wing 6 is automatically unfolded, the gliding attitude is established, and the aircraft is silently flown to the target area.

[0022] The maximum design weight of the gliding unmanned aerial vehicle is 1000 kg, the maximum payload is 850 kg, a battle group of 1 day of battle material equipment can be transported and delivered, the maximum material volume is 0.95 cubic meters, the wing span is 4.342 meters, the total wing 6 length is 8.684 meters, the mature low-cost flight control computer and data link equipment are configured, the unmanned aerial vehicle navigation and flight control are realized through the automatic driving system, the positioning system, the inertial navigation unit integrated in the flight control computer, the ranging equipment, the air speed tube and the like; at the same time, low-cost photoelectric equipment is arranged at the nose or the belly, flight information, control instructions and real-time images are transmitted through the data link equipment; the ground control station changes the route and delivery site according to the front situation.

[0023] The gliding unmanned plane can be launched by fixed-wing aircraft hoisting or gravity air drop, traction continuous launching, or launched by helicopter through hoisting or pushing. The minimum launch height is 450 meters, and the maximum launch height is 8000 meters. After air drop, the wings 6 are extended to the position by the instruction opening mechanism. The position is located by the positioning system. The remote control instruction is received through the measurement and control link. The instruction is sent by the flight control computer to control the rudder to deflect the rudder surface, so as to realize the attitude control and route control of the unmanned plane. The glide ratio can be kept at 9:1. The autonomous gliding range is 100 kilometers when the maximum height is air dropped, and the stall speed is 120 kilometers / hour.

[0024] Since there is no power system, the unmanned plane can keep silent gliding to the specified position, reduce the exposure probability, and the single machine cost is controlled within 100,000 yuan. At the same time, the unmanned plane can be compatible with the power mode, and the unmanned plane is driven by the electric motor and the propeller to realize the roadbed take-off and landing function, has the full stall landing ability and zero vertical impact ability, ensures the integrity of the goods and the reusability, and at the same time, can keep a low war consumption ratio. Compared with the traditional air drop system, the modified gliding unmanned plane can save 50% of the cost.

[0025] In the embodiment 2, the wing rotating shaft 7 comprises a wing base 9, a lower wing mounting joint 12, an upper wing mounting joint 16, a torsional spring assembly and a cover plate 17; the wing base 9 is fixed on the upper plate cover 2 through a first screw 10; the lower wing mounting joint 12 is sleeved on the outer wall of the supporting shaft of the wing base 9 and fixed with the wing base 9; one end of the torsional spring assembly is sleeved in the lower wing mounting joint 12, and the other end of the torsional spring assembly is sleeved in the upper wing mounting joint 16; and the cover plate 17 is fixed on the top of the supporting shaft through a second screw 18.

[0026] The torsional spring assembly comprises a torsional spring body 14 and a torsional spring outer cylinder 15; the torsional spring body 14 is sleeved in the torsional spring outer cylinder 15; the outer wall of the torsional spring outer cylinder 15 is provided with a first limiting block and a second limiting block from top to bottom; the top of the torsional spring body 14 is matched with an upper stop groove in the upper wing mounting joint 16; the bottom of the torsional spring body 14 is matched with a lower stop groove in the lower wing mounting joint 12; the first limiting block is matched with the downward extension part of the first stop pin 20, and the second limiting block is matched with the upward extension part of the second stop pin 11.

[0027] The wing 6 rotation shaft 7 further comprises a first wing rolling bearing 13 and a second wing rolling bearing 19; the outer wall of the outer shaft of the first wing rolling bearing 13 is fixed with the inner wall of the lower wing mounting joint 12, and the inner shaft of the first wing rolling bearing 13 is fixed with the bottom of the torsion spring outer cylinder 15; the outer wall of the outer shaft of the second wing rolling bearing 19 is fixed with the inner wall of the upper wing mounting joint 16, and the inner shaft of the second wing rolling bearing 19 is fixed with the top of the torsion spring outer cylinder 15.

[0028] The outer convex part of the upper wing mounting joint 16 is provided with a first fixing hole, the wing 6 is fixed on the upper wing mounting joint 16 by penetrating the wing 6 and the first fixing hole through the first stop pin 20; the outer convex part of the lower wing mounting joint 12 is provided with a second fixing hole, the wing 6 is fixed on the lower wing mounting joint 12 by penetrating the wing 6 and the second fixing hole through the second stop pin 11.

[0029] It should be noted that the main use process of the gliding cargo unmanned aerial vehicle is as follows: open the upper cover plate 17 of the fuselage 1 box body, see the attached figure (1), turn over the upper cover plate 17 and place it on the ground on one side, at this time, the four folded fixed wing surfaces with ailerons are fixed on the wing rotation shaft 7 of the upper plate cover, put the materials 8 into the box body, assemble the upper cover plate 2 and the wing 6 on one side of the box body, assemble the front fairing 3 and the rear extension section tail fin 4 and vertical tail 5, and the gliding unmanned aerial vehicle is ready for delivery; after the gliding unmanned aerial vehicle reaches the specified delivery area, the delivery is carried out, the wing 6 is unfolded to the flight state automatically through the wing folding locking mechanism and the mechanism system, after the wing 6 folding state is released, the torsion spring releases the torque in the mechanism system, drives the wing 6 mounting joint upper rotating bearing to rotate around the wing rotation shaft 7, and the wing 6 is unfolded; when the wing 6 mounting joint upper stop pin moves to the position of the torsion spring outer cylinder 15 block, the wing 6 is locked and stopped, the wing 6 is unfolded to the specified position, and the gliding unmanned aerial vehicle is glided to the specified area through the on-board equipment. The above process can be completed by two people. After the cargo gliding unmanned aerial vehicle completes the task, the unmanned aerial vehicle is collected according to the above reverse order.

[0030] The wing 6 folding assembly installation process of the gliding cargo unmanned aerial vehicle is as follows:

[0031] 1) The wing base 9 is installed with the first screw 10 fixed to the upper cover plate 17 of the fuselage 1 box body,

[0032] 2) The first wing rolling bearing 13 is sleeved on the support shaft of the wing base 9, and the inner wall of the first wing rolling bearing 13 is fixedly installed on the bearing mounting seat of the outer wall of the support shaft of the wing base 9 through interference fit,

[0033] 3) The lower wing mounting joint 12 is sleeved on the outer wall of the support shaft of the wing base 9, and the outer wall of the first wing rolling bearing 13 is fixedly installed on the inner wall of the lower wing mounting joint 12 through interference fit,

[0034] 4) The second stop pin 11 is installed in the mounting hole of the lower wing mounting joint 12 and extends the pin body;

[0035] 5) The lower straight wall of the torsion spring body 14 contacts the upper stop groove in the upper wing mounting joint 16 to achieve rotation limiting, and the upper straight wall of the torsion spring body 14 contacts the lower stop groove in the lower wing mounting joint 12 to achieve rotation limiting,

[0036] 6) The first limiting block of the torsion spring outer cylinder 15 is consistent with the designed position swing of the second stop pin 11, and the second limiting block of the torsion spring outer cylinder 15 is consistent with the designed position swing of the first stop pin 20,

[0037] 7) The torsion spring outer cylinder 15 is welded and fixed with the flange plate of the wing base 9,

[0038] 8) The inner wall of the first wing rolling bearing 13 is fixed and installed on the outer wall mounting seat of the wing base 9 through interference fit,

[0039] 9) The outer wall of the second wing rolling bearing 19 is fixed and installed on the inner wall of the upper wing mounting joint 16 through interference fit,

[0040] 10) The first stop pin 20 is installed in the mounting hole of the upper wing mounting joint 16 and extends the pin body;

[0041] 11) The second screw 18 is installed through the cover plate 17 to fix the cover plate 17 on the mounting hole of the support shaft of the wing base 9, and the wing 6 folding assembly is fixed, see the attached Fig. 3 .

[0042] It should be noted that the above technical features continue to be combined with each other to form various embodiments not listed above, which are considered to be within the scope of the description of the utility model; and for ordinary skilled persons in the art, the above description can be improved or changed, and all these improvements and changes should belong to the protection scope of the appended claims of the utility model.

Claims

1. A new type of cargo gliding drone, characterized by: The fuselage is a box structure, and the movable parts of the locks are installed on the two outer sides of the fuselage. The upper plate cover of the fuselage is provided with a fixed part of the lock, and the fixed part corresponds to the position of the movable part; wing shafts are respectively provided at the front and rear ends of the upper surface of the upper plate cover, and two wing shafts are each provided with two wings from top to bottom, and the four wings are relatively staggered from top to bottom.

2. The novel cargo gliding drone according to claim 1, characterized in that: The wing rotating shaft includes a wing base, a lower wing mounting joint, an upper wing mounting joint, a torsion spring assembly and a cover plate; the wing base is fixed to the upper plate cover by a first screw; the lower wing mounting joint is sleeved on the outer wall of the support shaft of the wing base and is fixed to the wing base; one end of the torsion spring assembly is sleeved in the lower wing mounting joint, and the other end of the torsion spring assembly is sleeved in the upper wing mounting joint; the cover plate is fixed to the top of the support shaft by a second screw.

3. The novel cargo gliding drone according to claim 2, characterized in that: The torsion spring assembly includes a torsion spring body and a torsion spring outer tube; the torsion spring body is sleeved inside the torsion spring outer tube, and the outer wall of the torsion spring outer tube is provided with a first limit block and a second limit block from top to bottom; the top of the torsion spring body cooperates with the upper stop groove in the upper wing mounting joint; the bottom of the torsion spring body cooperates with the lower stop groove in the lower wing mounting joint; the first limit block cooperates with the downward extension of the first stop pin, and the second limit block cooperates with the upward extension of the second stop pin.

4. The novel cargo gliding drone according to claim 3, characterized in that: The wing shaft also includes a first wing rolling bearing and a second wing rolling bearing; the outer wall of the outer shaft of the first wing rolling bearing is fixed to the inner wall of the lower wing mounting joint, and the inner shaft of the first wing rolling bearing is fixed to the bottom of the torsion spring outer tube; the outer wall of the outer shaft of the second wing rolling bearing is fixed to the inner wall of the upper wing mounting joint, and the inner shaft of the second wing rolling bearing is fixed to the top of the torsion spring outer tube.

5. The novel cargo gliding UAV according to claim 2, characterized in that: The outer protrusion of the upper wing mounting joint is provided with a first fixing hole, and a first stop pin passes through the wing and the first fixing hole to fix the wing on the upper wing mounting joint; the outer protrusion of the lower wing mounting joint is provided with a second fixing hole, and a second stop pin passes through the wing and the second fixing hole to fix the wing on the lower wing mounting joint.

6. The novel cargo gliding drone according to claim 1, characterized in that: The front and rear of the fuselage can be assembled with a front fairing and a tail cone and a vertical tail at the rear extended end.

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