CN215475718U

CN215475718U - Ice knife type landing gear-free high-aspect-ratio solar unmanned aerial vehicle landing auxiliary device

Info

Publication number: CN215475718U
Application number: CN202121599908.0U
Authority: CN
Inventors: 刘平; 徐尚儒; 朱奕潼; 吴世城; 郭瑾; 赵志强; 张新宇; 李满嫄
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2021-07-14
Filing date: 2021-07-14
Publication date: 2022-01-11
Anticipated expiration: 2031-07-14

Abstract

The utility model relates to the technical field of unmanned aerial vehicle models, in particular to an ice skate type landing-gear-free high-aspect-ratio solar unmanned aerial vehicle landing assisting device which comprises a reinforcing wing assistant, wherein a rivet I is arranged at the bottom of the right side of the reinforcing wing assistant surface. The detachable locking and positioning skid is arranged, portability is improved, the position of the outer supporting rod can be adjusted by the limiting chute through the adjusting screw nut according to the angle during landing, and through the matching of the parts, the air resistance of the unmanned aerial vehicle in the flight process is reduced, so that the ice skate type landing auxiliary device of the solar unmanned aerial vehicle without the landing gear and the large aspect ratio has the advantage of small flight resistance.

Description

Ice knife type landing gear-free high-aspect-ratio solar unmanned aerial vehicle landing auxiliary device

Technical Field

The utility model relates to the technical field of unmanned aerial vehicle models, in particular to an ice skate type landing-gear-free high-aspect-ratio solar unmanned aerial vehicle landing auxiliary device.

Background

With the continuous development and progress of unmanned aerial vehicles and model planes, the model planes are widely applied to the fields of aerial photography, agriculture, plant protection, self-shooting, express transportation and the like, the use of the flight model planes is greatly expanded, meanwhile, the solar aircraft receives wide attention as a novel unmanned aerial vehicle, and the solar aircraft has the characteristics of overlong flight time, lasting air space, ultrahigh flight, wide operation and the like, and has the advantages of flexibility in deployment, good economy and the like.

At present, the undercarriage is all installed to high aspect ratio solar energy unmanned aerial vehicle and model aeroplane and model ship, general undercarriage all is the outside of direct mount at the aircraft, and unmanned aerial vehicle's volume has been increased, weight, lead to unmanned aerial vehicle's portability greatly reduced, undercarriage weight has occupied the space of other electronic equipment greatly simultaneously, belong to unnecessary weight in the flight task, and solar energy unmanned aerial vehicle flight cycle is long, the energy of consumption aircraft that its undercarriage can be very big and increase flight resistance, consequently, need a descending auxiliary device to solve the problem urgently.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide an ice skate type landing assisting device of a solar unmanned aerial vehicle without an undercarriage and with a large aspect ratio, which has the advantage of small flight resistance, and solves the problems that the existing solar unmanned aerial vehicle with the large aspect ratio and an aeromodelling are provided with the undercarriage, the undercarriage is directly arranged on the outer side of the airplane, the size and the weight of the unmanned aerial vehicle are increased, the portability of the unmanned aerial vehicle is greatly reduced, the weight of the undercarriage greatly occupies the space of other electronic equipment, redundant weight is generated in a flight task, the flight period of the solar unmanned aerial vehicle is long, and the undercarriage can greatly consume the energy of the airplane and increase the flight resistance.

In order to achieve the purpose, the utility model provides the following technical scheme: an ice-skate blade type landing-gear-free high-aspect-ratio solar unmanned aerial vehicle landing auxiliary device comprises a reinforcing wing assistant, the bottom of the right side of the strengthening wing correcting surface is provided with a first rivet, the surface of the first rivet is rotationally connected with a locking and positioning skid, the front surface of the locking and positioning skid is provided with a limiting sliding chute, the inner cavity of the limiting sliding chute is connected with a limiting fixer in a sliding way, the bottom of the assistant surface of the reinforcing wing is provided with a second rivet, the surface of the second rivet is rotatably connected with a rotary lock head, an inner supporting rod is fixedly connected with one side of the rotary lock head, an outer supporting rod is sleeved on the surface of one end of the inner supporting rod, which is far away from the rotary lock head, one end of the outer supporting rod is fixedly connected with the limiting fixer, the surface of the inner supporting rod is sleeved with a spring, one end of the spring is fixedly connected with the outer supporting rod, and the end, far away from the outer supporting rod, of the spring is fixedly connected with the rotary lock head.

Preferably, the front surface of the reinforcing wing assistant is provided with a slotted hole, and the slotted hole is circular.

Preferably, the left side of the bottom of the reinforcing wing assistor is provided with a positioning groove, and the surface of the positioning groove is smooth.

Preferably, the right side of the bottom of the reinforcing wing assistor is provided with a groove, and the cross sectional area of the groove is smaller than that of the reinforcing wing assistor.

Preferably, the front surface of the reinforcing wing assistor is provided with three through holes, the front surface of the reinforcing wing assistor is positioned at the top of the through holes and is provided with two through grooves.

Preferably, one side of the locking and positioning skid is provided with an arc-shaped surface, and the surface of the arc-shaped surface is smooth.

Compared with the prior art, the utility model has the following beneficial effects:

1. the utility model improves the portability by arranging the detachable locking and positioning skid, the position of the outer supporting rod can be adjusted by the limiting chute through the adjusting screw nut according to the angle when the landing is carried out, and the air resistance borne by the unmanned aerial vehicle in the flight process is reduced by matching the components, so that the landing auxiliary device of the ice skate type solar unmanned aerial vehicle without the undercarriage and the large aspect ratio has the advantage of small flight resistance, in the actual use process, the locking and positioning skid is integrally arranged into a semi-arc ice skate shape and is made of polyvinyl chloride, a rivet structure can be matched, the head of the reinforcing wing rib rotates in a small amplitude, the positioning chute is arranged in the middle part, the position can be adjusted according to the angle when the landing by matching with the outer supporting rod, and the problem that the existing large aspect ratio solar unmanned aerial vehicle and an aeromodelling are provided with the undercarriage, and the undercarriage is generally directly arranged on the outer side of the aircraft is solved, and increased unmanned aerial vehicle's volume, weight leads to unmanned aerial vehicle's portability to descend greatly to and undercarriage weight has taken up other electronic equipment's space greatly, belongs to unnecessary weight in the flight task, and solar energy unmanned aerial vehicle flight cycle is long, the problem of the energy of its undercarriage very big consumption aircraft and increase flight resistance.

2. According to the utility model, through the arrangement of the slotted holes, a user can conveniently confirm the installation direction of the reinforcing wing assist, the user can conveniently install the reinforcing wing assist, the weight of the whole reinforcing wing assist can be reduced through the arrangement of the positioning grooves, the resistance of the unmanned aerial vehicle during flying is reduced, the whole weight of the reinforcing wing assist can be reduced through the arrangement of the grooves, the bearing of the unmanned aerial vehicle during flying is reduced, the ventilation effect can be realized through the arrangement of the through holes, the airflow circulation around the reinforcing wing assist is convenient, the supporting effect can be realized by matching with the locking positioning skids through the arrangement of the arc-shaped surfaces, and the sliding friction force of the locking positioning skids can be reduced through the arc-shaped surfaces.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is an enlarged view of a portion of FIG. 1;

FIG. 3 is a schematic perspective view of a reinforced rib structure according to the present invention.

In the figure: 1. reinforcing wing aids; 2. riveting one; 3. locking and positioning the skid; 4. a limiting chute; 5. a limiting fixer; 6. a second rivet; 7. rotating the lock head; 8. an inner support bar; 9. an outer support bar; 10. a spring; 11. a slot; 12. positioning a groove; 13. a groove; 14. a through hole; 15. a through groove; 16. an arc-shaped surface.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in figures 1 to 3: the utility model provides an ice-blade landing assisting device for a high-aspect-ratio solar unmanned aerial vehicle without an undercarriage, which comprises a reinforcing wing assistant 1, wherein the front surface of the reinforcing wing assistant 1 is provided with a groove hole 11, the shape of the groove hole 11 is circular, the mounting direction of the reinforcing wing assistant 1 can be conveniently confirmed by a user through the arrangement of the groove hole 11, the reinforcing wing assistant 1 can be conveniently mounted by the user, the left side of the bottom of the reinforcing wing assistant 1 is provided with a positioning groove 12, the surface of the positioning groove 12 is smooth, the integral weight of the reinforcing wing assistant 1 can be reduced through the arrangement of the positioning groove 12, the resistance of the unmanned aerial vehicle during flying is reduced, the right side of the bottom of the reinforcing wing assistant 1 is provided with a groove 13, the cross-sectional area of the groove 13 is smaller than that of the reinforcing wing assistant 1, the integral weight of the reinforcing wing assistant 1 can be reduced through the arrangement of the groove 13, the bearing of the unmanned aerial vehicle during flying is reduced, and the through hole 14 is formed in the front surface of the reinforcing wing assistant 1, the number of the through holes 14 is three, the front surface of the reinforcing wing assistant 1 and the top of the through hole 14 are provided with through grooves 15, the number of the through grooves 15 is two, the ventilation effect can be achieved through the matching use of the through holes 14 and the through grooves 15, the circulation of air flow around the reinforcing wing assistant 1 is convenient, the bottom of the right side of the front surface of the reinforcing wing assistant 1 is provided with a first rivet 2, the surface of the first rivet 2 is rotatably connected with a locking and positioning skid 3, one side of the locking and positioning skid 3 is provided with an arc surface 16, the surface of the arc surface 16 is smooth, through the arrangement of the arc surface 16, the sliding friction force of the locking and positioning skid 3 can be reduced by the arc surface 16, the front surface of the locking and positioning skid 3 is provided with a limiting chute 4, the inner cavity of the limiting chute 4 is slidably connected with a limiting fixer 5, the bottom of the front surface of the reinforcing wing assistant 1 is provided with a second rivet 6, the surface of the second rivet 6 is rotatably connected with a rotary lock head 7, an inner supporting rod 8 is fixedly connected to one side of the rotary lock head 7, an outer supporting rod 9 is sleeved on the surface of one end, far away from the rotary lock head 7, of the inner supporting rod 8, one end of the outer supporting rod 9 is fixedly connected with the limiting fixer 5, a spring 10 is sleeved on the surface of the inner supporting rod 8, one end of the spring 10 is fixedly connected with the outer supporting rod 9, and one end, far away from the outer supporting rod 9, of the spring 10 is fixedly connected with the rotary lock head 7.

The working principle is as follows: when the utility model is used, a user installs the reinforcing wing assistant 1 on an unmanned aerial vehicle, the locking and positioning skid 3 supports the unmanned aerial vehicle, the outer supporting rod 9 is made of carbon fiber resin composite square tubes, the inner part of the outer supporting rod is hollow, the lower part of the outer supporting rod is connected with the locking and positioning skid 3 through screw nuts, the inner supporting rod 8 is made of carbon fiber resin composite round rods, the inner supporting rod is inserted in the hollow part of the outer supporting rod 9 and can move up and down in the hollow part, the spring 10 is arranged between the rotary lock head 7 and the outer supporting rod 9 and mainly plays a role of buffering, the reinforcing wing assistant 1 is made of carbon fiber and is mainly fixed on a beam of a wing to play a main fixing role, the rotary lock head 7 is a key part for connecting the inner supporting rod 8 and the reinforcing wing assistant 1, the locking and positioning skid 3 is detachable, the portability is improved, the limiting chute 4 can adjust the position of the outer supporting rod 9 according to the descending angle through adjusting the screw nuts, through the cooperation of above-mentioned part use, reduce the air resistance that unmanned aerial vehicle received at the flight in-process.

It is noted that, herein, relational terms such as first and second, and the like may be 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. Also, 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 invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments 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

1. Ice sword formula does not have big aspect ratio solar energy unmanned aerial vehicle of undercarriage descending auxiliary device helps (1), its characterized in that including strengthening the wing: a first rivet (2) is arranged at the bottom of the right side of the front surface of the reinforcing wing assistant (1), a locking and positioning skid (3) is rotatably connected to the surface of the first rivet (2), a limiting sliding chute (4) is formed in the front surface of the locking and positioning skid (3), a limiting fixer (5) is slidably connected to the inner cavity of the limiting sliding chute (4), a second rivet (6) is arranged at the bottom of the front surface of the reinforcing wing assistant (1), a rotating lock head (7) is rotatably connected to the surface of the second rivet (6), an inner support rod (8) is fixedly connected to one side of the rotating lock head (7), an outer support rod (9) is sleeved on the surface of one end, far away from the rotating lock head (7), of the inner support rod (8), one end of the outer support rod (9) is fixedly connected with the limiting fixer (5), and a spring (10) is sleeved on the surface of the inner support rod (8), one end of the spring (10) is fixedly connected with the outer supporting rod (9), and the end, far away from the outer supporting rod (9), of the spring (10) is fixedly connected with the rotary lock head (7).

2. The ice skate blade type landing aid for solar unmanned aerial vehicle without undercarriage and with high aspect ratio according to claim 1, wherein: the front surface of the reinforcing wing assistor (1) is provided with a slotted hole (11), and the slotted hole (11) is circular.

3. The ice skate blade type landing aid for solar unmanned aerial vehicle without undercarriage and with high aspect ratio according to claim 1, wherein: the left side of the bottom of the reinforcing wing assistor (1) is provided with a positioning groove (12), and the surface of the positioning groove (12) is smooth.

4. The ice skate blade type landing aid for solar unmanned aerial vehicle without undercarriage and with high aspect ratio according to claim 1, wherein: the right side of the bottom of the reinforcing wing assistor (1) is provided with a groove (13), and the cross sectional area of the groove (13) is smaller than that of the reinforcing wing assistor (1).

5. The ice skate blade type landing aid for solar unmanned aerial vehicle without undercarriage and with high aspect ratio according to claim 1, wherein: the front surface of the reinforcing wing assistor (1) is provided with three through holes (14), the top of the reinforcing wing assistor (1), which is located at the top of the through holes (14), is provided with two through grooves (15).

6. The ice skate blade type landing aid for solar unmanned aerial vehicle without undercarriage and with high aspect ratio according to claim 1, wherein: one side of the locking and positioning skid (3) is provided with an arc-shaped surface (16), and the surface of the arc-shaped surface (16) is smooth.