CN220465803U - Vertical take-off and landing aircraft - Google Patents

Abstract

The utility model discloses a vertical take-off and landing aircraft, and relates to the technical field of aircrafts. The two sides of the machine body are fixedly provided with supporting arms, the number of the supporting arms is two, the outer sides of the bottoms of the supporting arms are provided with connecting plates, the bottoms of the connecting plates are connected with supporting rods, the front ends and the rear ends of the supporting rods are provided with lifting mechanisms, and the bottoms of the machine body are provided with damping landing gears. The aircraft can vertically take off under the action of the lifting mechanism, the lifting mechanism is four groups, each group of motors drives the helical blades to rotate at the same speed, so that the take-off speed is high, the base is in contact with the ground when the aircraft falls to the ground through the damping landing gear, impact force can be generated on the ground when the aircraft falls, the aircraft is more stable when falling to the ground under the action of the first telescopic rod, the first spring, the second telescopic rod, the second spring and the connecting column, and damage to the main body caused by hard landing is avoided.

Description

Vertical take-off and landing aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a vertical take-off and landing aircraft.

Background

Unmanned aerial vehicles are unmanned aerial vehicles that are operated using a radio remote control device and a self-contained programming device, or are operated autonomously, either entirely or intermittently, by an on-board computer.

The aerial unmanned aerial vehicle also belongs to one of the unmanned aerial vehicles, wherein the aerial unmanned aerial vehicle is usually a vertical take-off and landing technology, the vertical take-off and landing technology reduces or basically gets rid of the dependence on a runway, the aerial unmanned aerial vehicle can be lifted up and land vertically only by a small land, and the vertical take-off and landing aerial vehicle can be roughly divided into a rotor type aerial vehicle, a jet engine thrust steering aerial vehicle, a tilting rotor aerial vehicle, a tailstock propeller power aerial vehicle and a ducted fan power aerial vehicle according to a power mode.

In the prior art, when the aerial unmanned aerial vehicle falls, landing gear is always in direct hard contact with the ground, wherein the landing gear hard landing can generate certain vibration on the aerial unmanned aerial vehicle body, and the aerial unmanned aerial vehicle can be unstable in falling to the ground when serious, so that valuable articles carried on the aerial unmanned aerial vehicle fall to cause loss.

Disclosure of Invention

(one) solving the technical problems

Aiming at the defects of the prior art, the utility model provides a vertical take-off and landing aircraft, which solves the problems that landing gears are always in direct rigid contact with the ground during landing, the landing gears can generate certain vibration on an aerial unmanned aircraft body during the rigid landing, and the aircraft is unstable in landing during serious conditions, so that valuables carried on the aircraft drop, and loss is caused.

(II) technical scheme

In order to achieve the above purpose, the utility model is realized by the following technical scheme: the utility model provides a vertical take-off and landing aircraft, includes the fuselage of aircraft, the both sides fixed mounting of fuselage has the support arm, the quantity of support arm is two sets of, the connecting plate is installed in the outside of support arm bottom, the bottom of connecting plate is connected with the vaulting pole, lift mechanism is installed to the front end and the rear end of vaulting pole, the bottom of fuselage has the shock attenuation undercarriage.

Preferably, the lifting mechanism comprises a motor, a rotating shaft and helical blades, wherein the motor is positioned at the front end and the rear end of the connecting plate, the rotating shaft is connected with the upper end of an output shaft of the motor, and the helical blades are fixedly connected with the surface of the rotating shaft.

Preferably, the damping undercarriage comprises a mounting plate, a connecting ring, a first telescopic rod, a first spring, a second telescopic rod, a second spring, a connecting column, a bolt and a threaded hole, wherein the bottom of the mounting plate is provided with the threaded hole, and the mounting plate is connected with the bottom of the machine body through the bolt.

Preferably, the connecting ring is located the both sides of mounting panel, the one end of connecting ring rotates with the top of first telescopic link to be connected, the bottom of first telescopic link is connected in the inboard of spliced pole, install first spring between the inboard of spliced pole and the bottom of first telescopic link.

Preferably, the second telescopic rod is located at the bottom of two sides of the machine body, the bottom of the second telescopic rod is connected to the top of the connecting column, a second spring is installed between the top of the connecting column and the bottom of the second telescopic rod, and the connecting column is fixedly connected to the top of the base.

Preferably, the front end of the fuselage is provided with a thrust device, the rear end of the fuselage is provided with a horizontal tail, and two sides of the horizontal tail are connected with vertical tails.

(III) beneficial effects

The utility model provides a vertical take-off and landing aircraft. The beneficial effects are as follows:

the aircraft can vertically take off under the action of the lifting mechanism, the lifting mechanism is four groups, each group of motors drives the helical blades to rotate at the same speed, so that the take-off speed is high, the base is in contact with the ground when the aircraft falls to the ground through the damping landing gear, impact force can be generated on the ground when the aircraft falls, the aircraft is more stable when falling to the ground under the action of the first telescopic rod, the first spring, the second telescopic rod, the second spring and the connecting column, and damage to the main body caused by hard landing is avoided.

Drawings

FIG. 1 is a schematic diagram of the overall structure of the present utility model;

FIG. 2 is a schematic view of a shock absorbing landing gear of the present utility model;

fig. 3 is a schematic view of the structure of the threaded hole of the present utility model.

In the figure: 1. a body; 2. a support arm; 3. a connecting plate; 4. a brace rod; 5. a lift mechanism; 51. a motor; 52. a rotating shaft; 53. a helical blade; 6. damping landing gear; 61. a mounting plate; 62. a connecting ring; 63. a first telescopic rod; 64. a first spring; 65. a second telescopic rod; 66. a second spring; 67. a connecting column; 68. a bolt; 69. a threaded hole; 610. a base; 7. a thrust device; 8. a horizontal tail; 9. and a vertical tail.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-3, the present utility model provides a technical solution: the utility model provides a vertical take-off and landing aircraft, includes fuselage 1 of aircraft, the both sides fixed mounting of fuselage 1 has support arm 2, the quantity of support arm 2 is two sets of, connecting plate 3 is installed in the outside of support arm 2 bottom, the bottom of connecting plate 3 is connected with vaulting pole 4, lift mechanism 5 is installed to the front end and the rear end of vaulting pole 4, the bottom of fuselage 1 has shock attenuation undercarriage 6. The aircraft can vertically take off under the action of the lifting mechanism 5, the lifting mechanism 5 is four groups, each group of motors 51 drives the helical blades 53 to rotate at the same speed, so that the take-off speed is high, the base 610 contacts with the ground when the aircraft falls to the ground through the damping landing gear 6, impact force can be generated on the ground when the aircraft falls, and the aircraft is more stable when falling to the ground under the action of the first telescopic rod 63, the first spring 64, the second telescopic rod 65, the second spring 66 and the connecting column 67, so that the damage to the main body caused by hard landing is avoided.

Referring to fig. 1-3, the present utility model provides a technical solution: the lifting mechanism 5 comprises a motor 51, a rotating shaft 52 and a helical blade 53, wherein the motor 51 is positioned at the front end and the rear end of the connecting plate 3, the rotating shaft 52 is connected with the upper end of an output shaft of the motor 51, and the helical blade 53 is fixedly connected with the surface of the rotating shaft 52. The motor 51 drives the rotation shaft 52 to rotate, so that the spiral blades 53 rotate, the motor 51, the rotation shaft 52 and the spiral blades 53 are four groups, and the spiral blades 53 rotate at the same speed, so that the whole body is vertically lifted.

Referring to fig. 1-3, the present utility model provides a technical solution: the damping undercarriage 6 comprises a mounting plate 61, a connecting ring 62, a first telescopic rod 63, a first spring 64, a second telescopic rod 65, a second spring 66, a connecting column 67, a bolt 68 and a threaded hole 69, wherein the bottom of the mounting plate 61 is provided with the threaded hole 69, and the mounting plate 61 is connected with the bottom of the machine body 1 through the bolt 68. The bolts 68 mount the mounting plate 61 to the bottom of the fuselage 1 to facilitate removal of the shock absorbing landing gear 6 when maintenance is required.

Referring to fig. 1-3, the present utility model provides a technical solution: the connecting rings 62 are located at two sides of the mounting plate 61, one end of each connecting ring 62 is rotatably connected with the top of the corresponding first telescopic rod 63, the bottom of each first telescopic rod 63 is connected to the inner side of the corresponding connecting column 67, and a first spring 64 is installed between the inner side of the corresponding connecting column 67 and the bottom of the corresponding first telescopic rod 63. The bottom at first telescopic link 63 is established to this first spring 64 cover, and first spring 64 compresses between spliced pole 67 and first telescopic link 63 when making the aircraft descend under the effect of first spring 64 to make the aircraft descend and have certain buffering, more stable when descending to the main part.

Referring to fig. 1-3, the present utility model provides a technical solution: the second telescopic rods 65 are located at the bottoms of two sides of the machine body 1, the bottoms of the second telescopic rods 65 are connected to the tops of the connecting columns 67, second springs 66 are installed between the tops of the connecting columns 67 and the bottoms of the second telescopic rods 65, and the connecting columns 67 are fixedly connected to the tops of the bases 610. The second spring 66 is sleeved at the lower end of the second telescopic rod 65, and is matched with the first spring 64, so that the vibration of the aircraft is greatly reduced when the aircraft descends, and the damage to the main body caused by hard landing is avoided.

Referring to fig. 1-3, the present utility model provides a technical solution: the front end of the machine body 1 is provided with a thrust device 7, the rear end of the machine body 1 is provided with a horizontal tail 8, and two sides of the horizontal tail 8 are connected with vertical tails 9. The main body is moved forward by the thrust device 7, and the tail airflow is regulated and stabilized under the action of the horizontal tail 8 and the vertical tail 9, so that the aircraft is more stable in flight.

When the motor 51 works, the rotating shaft 52 is rotated, the spiral blades 53 rotate at the same speed, so that the aircraft vertically takes off, the descending speed of the aircraft is controlled during landing, when the base 610 contacts the ground, the first spring 64 and the second spring 66 compress between the connecting post 67 and the first telescopic rod 63 and the second telescopic rod 65, so that the impact force of the main body on the ground is reduced, the vibration amplitude of the aircraft is reduced, the aircraft lands softly, and the main body cannot be damaged.

In summary, this vertical take-off and landing aircraft has solved when dropping, often the undercarriage all is direct with ground rigid contact, and wherein the undercarriage hard landing can produce certain vibrations to unmanned aerial vehicle body of taking photo by plane, can make the aircraft unstable on the ground when serious to carry valuables on the messenger's aircraft and drop, cause the problem of loss.

It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, 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, method, article, or apparatus.

Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims (6)

1. Vertical take-off and landing aircraft comprising a fuselage (1) of the aircraft, characterized in that: the two sides of the machine body (1) are fixedly provided with support arms (2), the number of the support arms (2) is two, the outer sides of the bottoms of the support arms (2) are provided with connecting plates (3), the bottoms of the connecting plates (3) are connected with supporting rods (4), the front ends and the rear ends of the supporting rods (4) are provided with lifting mechanisms (5), and the bottoms of the machine body (1) are provided with damping landing gears (6).

2. A vertical takeoff and landing aircraft according to claim 1, wherein: the lifting mechanism (5) comprises a motor (51), a rotating shaft (52) and a helical blade (53), wherein the motor (51) is positioned at the front end and the rear end of the connecting plate (3), the rotating shaft (52) is connected with the upper end of an output shaft of the motor (51), and the helical blade (53) is fixedly connected to the surface of the rotating shaft (52).

3. A vertical takeoff and landing aircraft according to claim 1, wherein: the damping undercarriage (6) comprises a mounting plate (61), a connecting ring (62), a first telescopic rod (63), a first spring (64), a second telescopic rod (65), a second spring (66), a connecting column (67), bolts (68), threaded holes (69) and a base (610), wherein the bottom of the mounting plate (61) is provided with the threaded holes (69), and the mounting plate (61) is connected with the bottom of the machine body (1) through the bolts (68).

4. A vertical takeoff and landing aircraft according to claim 3, wherein: the connecting rings (62) are located on two sides of the mounting plate (61), one end of each connecting ring (62) is rotatably connected with the top of each first telescopic rod (63), the bottom of each first telescopic rod (63) is connected to the inner side of each connecting column (67), and a first spring (64) is installed between the inner side of each connecting column (67) and the bottom of each first telescopic rod (63).

5. A vertical takeoff and landing aircraft according to claim 3, wherein: the second telescopic rods (65) are located at the bottoms of two sides of the machine body (1), the bottoms of the second telescopic rods (65) are connected to the tops of the connecting columns (67), second springs (66) are installed between the tops of the connecting columns (67) and the bottoms of the second telescopic rods (65), and the connecting columns (67) are fixedly connected to the tops of the bases (610).

6. A vertical takeoff and landing aircraft according to claim 1, wherein: the front end of the machine body (1) is provided with a thrust device (7), the rear end of the machine body (1) is provided with a horizontal tail wing (8), and two sides of the horizontal tail wing (8) are connected with vertical tail wings (9).