CN213921452U

CN213921452U - Collapsible section of thick bamboo penetrates formula unmanned aerial vehicle

Info

Publication number: CN213921452U
Application number: CN202023017348.1U
Authority: CN
Inventors: 林玉祥; 刘艳军; 罗竑; 梁斌; 吴海杰
Original assignee: Universal Star Suzhou Co ltd
Current assignee: Universal Star Suzhou Co ltd
Priority date: 2020-12-15
Filing date: 2020-12-15
Publication date: 2021-08-10
Anticipated expiration: 2030-12-15

Abstract

The utility model relates to a general aviation field, concretely relates to collapsible section of thick bamboo penetrates formula unmanned aerial vehicle. The aircraft comprises an aircraft body, wings, empennages and a propulsion power system, wherein the head of the aircraft body is provided with an airspeed head used for testing the flight speed, the wings are horizontally arranged on the aircraft body through the bilateral symmetry of a wing rotating mechanism, the empennages are inverted V-shaped empennages and are arranged on the side edge of the tail part of the aircraft body through the bilateral symmetry of the empennage rotating mechanism respectively, the propulsion power system is arranged at the tail end of the aircraft body, the propulsion power system comprises a propulsion motor, a propeller hub and a propeller, the propeller hub is used for installing the propeller, and the propeller hub is provided with a propeller blocking mechanism. The utility model discloses a wing rotary mechanism, fin rotary mechanism and propeller hub realize the folding and but quick assembly disassembly of wing, fin and screw. Effectively reduces the occupied space of the whole machine and is convenient for storage and transportation.

Description

Collapsible section of thick bamboo penetrates formula unmanned aerial vehicle

Technical Field

The utility model relates to a general aviation field, concretely relates to collapsible section of thick bamboo penetrates formula unmanned aerial vehicle.

Background

The cylinder-shooting type unmanned aerial vehicle is folded through folding mechanism parts, the space size is effectively reduced, a shooting mode of cylinder shooting is adopted, and the cylinder-shooting type unmanned aerial vehicle has the characteristics of low cost, high cost ratio, small size and the like. And the flexibility and the regional adaptability of the cylinder-shooting type unmanned aerial vehicle system attract a large number of domestic and foreign experts to carry out deep research on the cylinder-shooting type unmanned aerial vehicle system.

Present cylinder-shooting type unmanned aerial vehicle adopts tandem wing overall arrangement around mostly, needs great thickness after two sets of wings are folded, can take up the effective loading space of fuselage for the spatial structure of fuselage designs the degree of difficulty greatly increased. The design of two sets of wings can lead to the focus of fuselage more back than conventional unmanned aerial vehicle for each item equipment's in the fuselage arranges the degree of difficulty greatly increased.

SUMMERY OF THE UTILITY MODEL

The utility model provides a technical problem provide a collapsible and quick assembly disassembly's a section of thick bamboo penetrates formula unmanned aerial vehicle.

The utility model provides a technical scheme that its technical problem adopted is:

a foldable cylinder-shooting unmanned aerial vehicle comprises a fuselage, wings, empennages and a propulsion power system, wherein airspeed tubes used for testing flight speed are arranged at the head of the fuselage, the wings are horizontally arranged on the fuselage in a bilateral symmetry mode through wing rotating mechanisms, the empennages are inverted V-shaped empennages and comprise left and right empennages which are respectively arranged on the side edges of the tail part of the fuselage in a bilateral symmetry mode through the empennage rotating mechanisms, the propulsion power system is arranged at the tail end of the fuselage, the propulsion power system comprises a propulsion motor, a propeller hub and propellers, the propeller hub is used for mounting the propellers, and propeller blocking mechanisms are arranged on the propeller hub; the aircraft is characterized in that a seeker and a fighting part are integrated on the front section inside the aircraft body, a flight control system, a data chain, a power battery and a parachute are integrated on the middle section inside the aircraft body, and the tail section inside the aircraft body is used for installing the propulsion motor and the electric controller.

Furthermore, ailerons are symmetrically arranged on the rear edge of the wing, and empennage control surfaces are symmetrically arranged on the rear edge of the empennage.

Further, the wing rotating mechanism drives the wing to rotate by 90 degrees and is parallel or vertical to the fuselage.

Further, the tail wing rotating mechanism drives the tail wing to rotate by 90 degrees and is parallel or vertical to the fuselage.

Preferably, the fuselage is a lifting body fuselage.

Preferably, the wing is a high lift airfoil wing.

The utility model has the advantages that:

the foldable and fast detachable wing, the empennage and the propeller are realized through the wing rotating mechanism, the empennage rotating mechanism and the propeller hub. The wings adopt a mode that the whole wings rotate, so that the space of the fuselage can be occupied as little as possible, and the loading space of the fuselage is greatly increased. The fin adopts the tail of falling the V, keeps better aircraft appearance after rotatory back and fuselage laminating, has reduced unmanned aerial vehicle's storage space, the transportation of being convenient for. The whole aircraft only has one wing rotating mechanism and two tail wing rotating structures, the rotating mechanisms are mutually independent, the structure is simple, and the weight is light. The wings adopt high lift wing shapes, the fuselage adopts the shape of the body of the lift body, and the pneumatic efficiency of the whole aircraft is higher. The center of gravity of the machine body is relatively close to the front, so that the arrangement difficulty of various devices in the machine body can be greatly reduced.

Drawings

FIG. 1 is a view showing an expanded form of the present invention;

FIG. 2 is a partial perspective view of the aft portion of the fuselage of FIG. 1;

FIG. 3 is a schematic diagram of the structure labeled 7 in FIG. 1;

FIG. 4 is a view of the folded configuration of FIG. 1;

labeled as:

1. fuselage, 2, airspeed head, 3, wing rotary mechanism, 4, wing, 401, aileron, 5, tail rotary mechanism, 6, tail, 601, tail rudder face, 7, propulsion power system, 701, propeller hub, 702, screw, 7011 screw blocking mechanism.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

A foldable cylinder-shooting unmanned aerial vehicle is shown in figures 1-3 and comprises a body 1, wings 4, a tail wing 6 and a propulsion power system 7, wherein the head of the body 1 is provided with an airspeed head 2 for testing flight speed, the wings 4 are horizontally arranged on the body 1 in a bilateral symmetry mode through a wing rotating mechanism 3, the tail wing 6 is an inverted V-shaped tail wing and comprises a left tail wing and a right tail wing which are respectively arranged on the side edge of the tail part of the body 1 in a bilateral symmetry mode through a tail wing rotating mechanism 5, the propulsion power system 7 is arranged at the tail end of the body 1, the propulsion power system 7 comprises a propulsion motor, a propeller hub 701 and a propeller 702, the propeller hub 701 is used for mounting the propeller 702, and the propeller hub 701; the integrated seeker of the inside anterior segment of fuselage 1 and warhead, integrated flight control system, data chain, power battery and parachute in inside middle section, inside tail section is used for installing propulsion motor and electricity to transfer.

As shown in fig. 1, the rear edge of the wing 4 is symmetrically provided with ailerons 401, and the rear edge of the tail 6 is symmetrically provided with tail control surfaces 601. The ailerons 401 are used for roll control of the drone and the empennage control surface 601 is used for pitch and course control of the drone.

With reference to fig. 1 and 4, the utility model discloses an unmanned aerial vehicle folding angle and principle as follows:

the wing rotating mechanism 3 drives the wing 4 to rotate by 90 degrees and keep parallel or vertical to the fuselage 2, the wing 4 is unfolded by rotating by 90 degrees through the wing rotating mechanism 3 and keeps vertical to the fuselage 2, and the wing 4 is retracted by rotating by 90 degrees through the wing rotating mechanism 3 and keeps parallel to the fuselage 2.

The tail wing rotating mechanism 5 drives the tail wing 6 to rotate by 90 degrees and keep parallel or vertical to the machine body 2, the tail wing 6 is unfolded by rotating by 90 degrees through the tail wing rotating mechanism 5 and keeps vertical to the machine body 2 to form an inverted V-shaped tail wing, and the tail wing 6 is retracted by rotating by 90 degrees through the tail wing rotating mechanism 5 and keeps parallel to the machine body 2. Because the inverted V-shaped tail wing design is adopted, when the tail wing 6 and the wing 4 are retracted, the tail wing 6 is kept horizontal with the side edge of the fuselage 2, and the wing 4 is kept horizontal with the upper surface of the fuselage 2, so that the thickness of the whole aircraft is effectively reduced, and the difficulty in designing the space structure of the fuselage is reduced.

The propeller 702 is deployed and retracted around the hub 701, attached to the fuselage 1 when retracted, and a hub drag mechanism 7011 is used to prevent the propeller 701 from being deployed too far beyond the central axis of the fuselage 1.

The utility model discloses in, fuselage 1 adopts the lift body fuselage, and wing 4 adopts high lift wing section wing. Fuselage 1, wing 4 and fin 6 all adopt glass fiber composite for unmanned aerial vehicle has and satisfies the wave-transparent requirement under the less structural weight condition. Hub 701 adopts the 7075 aviation aluminum alloy of mark number, satisfies sufficient use intensity to make this mechanism weight lighter, be favorable to reducing unmanned aerial vehicle's weight.

The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims

1. The utility model provides a collapsible section of thick bamboo penetrates formula unmanned aerial vehicle which characterized in that: the aircraft comprises a fuselage (1), wings (4), a tail wing (6) and a propulsion power system (7), wherein the head of the fuselage (1) is provided with an airspeed head (2) for testing flight speed, the wings (4) are horizontally arranged on the fuselage (1) through wing rotating mechanisms (3) in a bilateral symmetry manner, the tail wing (6) is an inverted V-shaped tail wing and comprises a left tail wing and a right tail wing, the left tail wing and the right tail wing are respectively arranged on the side edge of the tail part of the fuselage (1) in a bilateral symmetry manner through a tail wing rotating mechanism (5), the propulsion power system (7) is arranged at the tail end of the fuselage (1), the propulsion power system (7) comprises a propulsion motor, a propeller hub (701) and a propeller (702), the propeller hub (701) is used for installing the propeller (702), and a propeller blocking mechanism (7011) is arranged on the propeller hub (701); the aircraft is characterized in that a seeker and a fighting part are integrated on the front section inside the aircraft body (1), a flight control system, a data chain, a power battery and a parachute are integrated on the middle section inside the aircraft body, and the tail section inside the aircraft body is used for installing the propulsion motor and the electric controller.

2. The foldable tube-shooting unmanned aerial vehicle of claim 1, wherein: ailerons (401) are symmetrically arranged on the rear edge of the wing (4), and empennage control surfaces (601) are symmetrically arranged on the rear edge of the empennage (6).

3. A foldable barrel-shooting drone according to claim 2, characterized in that: the wing rotating mechanism (3) drives the wing (4) to rotate 90 degrees and is parallel or vertical to the fuselage.

4. A foldable barrel-shooting drone according to claim 2, characterized in that: the empennage rotating mechanism (5) drives the empennage (6) to rotate 90 degrees and keep parallel or perpendicular to the fuselage.

5. A foldable tube-fire drone according to any of claims 1 to 4, characterised in that: the machine body (1) is a lifting body machine body.

6. The foldable tube-shooting unmanned aerial vehicle of claim 5, wherein: the wings (4) are high-lift airfoil-shaped wings.