CN114228989B - Amphibious water surface life preserver based on box wing aerodynamic layout - Google Patents

Abstract

The present invention provides an amphibious water surface life preserver based on box-type wing aerodynamic layout, which is a box-type wing aerodynamic layout, including: front wing, rear wing, left front and rear wing connection section, right front and rear wing connection section, first power The rotor, the second power rotor, the third power rotor and the fourth power rotor; the front wing and the rear wing are horizontally arranged in parallel; the height of the front wing is lower than the height of the rear wing. The amphibious water surface lifesaving device based on box-type wing aerodynamic layout provided by the present invention has the following advantages: (1) The aircraft has an ergonomic life-saving shape through the box-type wing layout, and has three functions of unmanned aerial vehicle, unmanned ship and life buoy , through air flight and water surface cruising, it can quickly and actively reach the searched and rescued object to carry out rescue, and has the function of autonomous lifesaving. (2) It makes up for the inaccurate and random defects of the existing UAV rescue method, improves rescue efficiency, and maximizes the survival rate of the rescued.

Description

Amphibious water surface life preserver based on box wing aerodynamic layout

technical field

The invention belongs to the technical field of water surface lifesaving, and in particular relates to an amphibious water surface lifesaving device based on box-type wing aerodynamic layout.

Background technique

Flood disaster is a kind of natural disaster that occurs frequently and seriously at present, and the direct economic loss of flood disaster accounts for about 60% of the total direct economic loss of various natural disasters. Flood disasters are generally characterized by high frequency of occurrence, wide range of influence, and heavy economic losses.

However, although casualties and economic losses caused by floods often occur every year, safety rescue equipment for flood disasters is still relatively lacking. Existing rescue equipment mainly includes: lifeboats, life rafts, hovercraft, rubber boats, assault boats, etc. Most of these equipment have the disadvantages of large volume and weight, inconvenient storage and transportation, and difficult daily maintenance. In addition, fuel-powered equipment, such as lifeboats, assault boats, etc., need to take warm-up measures when they are turned on in low-temperature environments; hovercrafts are slow towing, so the number of vehicles that can reach the disaster area in a short period of time is limited, and the cost of use is high; life rafts, Rubber boats have poor wind and wave resistance, are easily overturned under the influence of wind and waves, and have insufficient power, so the rescue distance is also relatively short. The most important thing is that these rescue equipment require professional rescuers to drive to the side of the trapped person at risk, and then rescue them. In the case of very turbulent water flow, not only may the rescue operation fail, but it may also endanger the safety of the rescuers. .

In recent years, there has been a rescue method of throwing life buoys by drones, which has solved the above problems to a certain extent, but this method simply uses the transportation function of drones, and the accuracy of throwing is poor.

Contents of the invention

Aiming at the defects existing in the prior art, the present invention provides an amphibious water surface life preserver based on box wing aerodynamic layout, which can effectively solve the above problems.

The technical scheme that the present invention adopts is as follows:

The present invention provides an amphibious water surface lifesaving device based on box-type wing aerodynamic layout. The shape of the amphibious water surface lifesaving device based on box-type wing aerodynamic layout is box-type wing aerodynamic layout, including: front wing (1), Rear wing (2), left front and rear wing connection section (3), right front and rear wing connection section (4), first power rotor (5), second power rotor (6), third power rotor (7) and The fourth power rotor (8);

The front wing (1), the left front and rear wing connection section (3), the rear wing (2) and the right front and rear wing connection section (4) are connected end to end to form a closed ring structure; The front wing (1) and the rear wing (2) are horizontally arranged in parallel; the height of the front wing (1) is lower than the height of the rear wing (2);

On the upper airfoil surface of the nose of the front wing (1), the first power rotor (5) is fixedly installed; on the upper airfoil surface of the left wing tip position of the front wing (1), fixed The second power rotor (6) is installed; on the upper airfoil surface of the right wing tip position of the front wing (1), the third power rotor (7) is fixedly installed; on the rear wing (2) ) on the airfoil surface of the tail position, the fourth power rotor (8) is fixedly installed; wherein, the first power rotor (5), the second power rotor (6), the third power rotor (7) is arranged in parallel with the fourth power rotor (8).

Preferably, the airfoils of the front wing (1) and the rear wing (2) are the same, which are symmetrical airfoils; the chord length of the airfoil is defined as c, and the leading edge of the airfoil is a semicircular arc with a radius of R, and the airfoil The trailing edge of the shape is a semi-circular arc with a radius of r, then: R/c=0.2～0.4, r/c=0.05～0.1; the defined wingspan is L, and L/c=4～7.

Preferably, the center of the semicircle arc of the leading edge of the airfoil and the center of the semicircle arc of the trailing edge of the airfoil are on a horizontal line, the upper endpoint (A1) of the semicircle arc of the leading edge of the airfoil, and the semicircle of the trailing edge of the airfoil The upper end point (A2) is connected by the upper airfoil straight line (F1); the lower end point (B1) of the airfoil leading edge semicircle arc and the lower end point (B2) of the airfoil trailing edge semicircle arc are connected by the lower airfoil straight line (F2) to connect.

Preferably, the shape of the amphibious surface lifeguard based on the aerodynamic layout of the box wing is mirror-symmetrical about the central axis of the fuselage;

Front wing sweep angle _θ1 is the included angle between the leading edge of the front wing and the vertical line of the central axis of the fuselage;

The rear wing sweep angle _θ2 is the angle between the leading edge of the rear wing and the vertical line of the central axis of the fuselage;

Then there is: front wing sweep angle θ ₁ = rear wing sweep angle θ ₂ .

Preferably, the front wing (1) includes integrally formed left front wing (H1), right front wing (H2) and front wing connecting transition section (H3);

The connecting transition section (H3) of the front wing is a circular arc with a central angle of θ ₃ , and the left end point of the connecting transition section (H3) of the front wing extends outwards from the linear left front wing (H1), so The right end point of the front wing connection transition section (H3) extends outwards to a straight line of the right front wing portion (H2);

The rear wing (2) has the same shape as the front wing (1).

Preferably, the central angle θ ₃ =2θ ₁ .

Preferably, the height difference between the front wing (1) and the rear wing (2) is h, h/c=0.7˜1.2.

Preferably, the connecting section of the left front and rear wings (3) and the connecting section of the right front and rear wings (4) are thin plates with a thickness d; d/c=0.2～0.3;

The angle between the left front and rear wing connecting section (3) and the horizontal direction is the same as the angle between the right front and rear wing connecting section (4) and the horizontal direction, both being β.

Preferably, β=30-60°.

Preferably, the total length of the fuselage is defined as Z, Z/c=5～7;

The distance from the first powered rotor (5) to the front end of the lifeguard is x ₁ , x ₁ /Z=0.05～0.07;

The distance from the second powered rotor (6) to the front end of the life preserver is the same as the distance from the third powered rotor (7) to the front end of the life preserver, both are x ₂ , x ₂ /Z=0.35～0.37;

The distance from the second power rotor (6) to the left tip of the front wing (1) is the same as the distance from the third power rotor (7) to the right wing tip of the front wing (1), Both are y, y/c=0.35～0.45;

The distance between the fourth power rotor (8) and the front end of the lifeguard is x ₃ , and x ₃ /Z=0.93-0.95.

The amphibious water surface life preserver based on box wing aerodynamic layout provided by the present invention has the following advantages:

(1) The aircraft has an ergonomic life-saving shape through the box-shaped wing layout, and has three functions of drone, unmanned ship, and lifebuoy. With self-rescue function.

(2) It makes up for the inaccurate and random defects of the existing UAV rescue method, improves rescue efficiency, and maximizes the survival rate of the rescued.

Description of drawings

Fig. 1 is the top view of the amphibious type water surface lifesaving device based on the aerodynamic layout of the box wing provided by the present invention;

Fig. 2 is the front view of the amphibious water surface lifesaving device based on box-type wing aerodynamic layout provided by the present invention;

Fig. 3 is a side view of the amphibious water surface lifeguard based on the aerodynamic layout of the box wing provided by the present invention.

Detailed ways

In order to make the technical problems, technical solutions and beneficial effects solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

The invention provides an amphibious water surface life preserver based on the aerodynamic layout of box wings, which integrates a drone and a life buoy, greatly improving the speed, safety and economy of rescue under flood disaster conditions.

The present invention provides an amphibious water surface life preserver based on box-type wing aerodynamic layout, which has the following characteristics: 1) adopts box-type wing aerodynamic layout, which can effectively improve the aerodynamic efficiency of the aircraft compared with conventional layouts. Compared with the conventional layout, the box wing layout has the advantages of small wing size, light structure weight, high stiffness, high lift coefficient, good stability and maneuverability, etc. 2) The wing of the box wing is closed, which is similar in shape to the lifebuoy, and has the natural advantages of the lifebuoy.

Specifically, the present invention provides an air/surface amphibious intelligent surface lifesaving device based on the aerodynamic layout of the box wing. Through the layout design and power configuration of the lifesaving device, its aerodynamic characteristics, maneuverability and stability are studied, and the solution is evaluated. Feasibility, finally give the design scheme and verification model. After the invention has achieved results, the life preserver is used in emergency rescue and disaster relief in time to ensure the safety of people's lives and property.

Referring to Fig. 1-Fig. 3, the present invention provides an amphibious water surface lifesaving device based on box-type wing aerodynamic layout, the shape of the amphibious water surface lifesaving device based on box-type wing aerodynamic layout is box-type wing aerodynamic layout, Including: front wing 1, rear wing 2, left front and rear wing connection section 3, right front and rear wing connection section 4, first power rotor 5, second power rotor 6, third power rotor 7 and fourth power rotor 8;

The front wing 1, the left front and rear wing connection section 3, the rear wing 2 and the right front and rear wing connection section 4 are connected end to end to form a closed ring structure; the front wing 1 and the rear wing 2 horizontally arranged in parallel; the height of the front wing 1 is lower than the height of the rear wing 2;

On the upper airfoil surface of the nose of the front wing 1, the first power rotor 5 is fixedly installed; on the upper airfoil surface of the left wing tip position of the front wing 1, the second power rotor is fixedly installed. Rotor 6; on the upper airfoil surface of the right wing tip position of the front wing 1, the third power rotor 7 is fixedly installed; on the upper airfoil surface of the tail position of the rear wing 2, the The fourth power rotor 8; wherein, the first power rotor 5, the second power rotor 6, the third power rotor 7 and the fourth power rotor 8 are arranged in parallel.

The main design parameters of the present invention are introduced in detail below:

(1) The airfoils of the front wing 1 and the rear wing 2 are the same, which are symmetrical airfoils; the airfoil chord length is defined as c, the airfoil leading edge is a semicircular arc whose radius is R, and the airfoil trailing edge is For a semicircular arc whose radius is r, then: R/c=0.2～0.4, r/c=0.05～0.1; define the wingspan as L, L/c=4～7.

(2) The center of the semicircle arc at the leading edge of the airfoil and the center of the semicircle arc at the trailing edge of the airfoil are on a horizontal line, the upper endpoint A1 of the semicircle arc at the leading edge of the airfoil, and the upper endpoint of the semicircle arc at the trailing edge of the airfoil A2 is connected by the straight line F1 of the upper airfoil; the lower end point B1 of the semicircular arc of the leading edge of the airfoil is connected with the lower end point B2 of the semicircular arc of the trailing edge of the airfoil by the straight line F2 of the lower airfoil.

(3) The shape of the amphibious surface life preserver based on the aerodynamic layout of the box wing is mirror-symmetrical about the central axis of the fuselage;

Front wing sweep angle _θ1 is the included angle between the leading edge of the front wing and the vertical line of the central axis of the fuselage;

The rear wing sweep angle _θ2 is the angle between the leading edge of the rear wing and the vertical line of the central axis of the fuselage;

Then there is: front wing sweep angle θ ₁ = rear wing sweep angle θ ₂ .

(4) The front wing 1 includes integrally formed left front wing part H1, right front wing part H2 and front wing connecting transition section H3;

The front wing connecting transition section H3 is a circular arc with a central angle θ ₃ , and the central angle θ ₃ =2θ ₁ . The left end point of the front wing connection transition section H3 extends outwards from the linear left front wing part H1, and the right end point of the front wing connection transition section H3 extends outwards from the linear right front wing part H2;

The rear wing 2 has the same shape as the front wing 1 .

(5) The height difference between the front wing 1 and the rear wing 2 is h, h/c=0.7˜1.2.

(6) The connecting section 3 of the left front and rear wings and the connecting section 4 of the right front and rear wings are thin plates with a thickness of d; d/c=0.2～0.3;

The angle between the left front and rear wing connecting section 3 and the horizontal direction is the same as the angle between the right front and rear wing connecting section 4 and the horizontal direction, both being β. β=30-60, as a preferred mode, β=45°.

(7) Define the total length of the fuselage as Z, Z/c=5～7;

The distance from the first powered rotor 5 to the front end of the lifeguard is x ₁ , x ₁ /Z=0.05～0.07;

The distance from the second powered rotor 6 to the front end of the life preserver is the same as the distance from the third powered rotor 7 to the front end of the life preserver, both are x ₂ , x ₂ /Z=0.35～0.37;

The distance from the second powered rotor 6 to the left tip of the front wing 1 is the same as the distance from the third powered rotor 7 to the right wing tip of the front wing 1, both are y, y/c=0.35～0.45;

The distance from the fourth power rotor 8 to the front end of the lifeguard is x ₃ , and x ₃ /Z=0.93-0.95.

It can be seen that the present invention improves the circular layout of the traditional life buoy into an aerodynamic layout based on box-type wings, and at the same time installs four rotors at the head, both sides of the wing and the tail to provide power, so that it has the ability to fly in the air . The present invention proposes an unmanned air and water surface amphibious lifesaving device based on a box-type wing layout. The life preserver organically combines the box-type wing structure with the swimming ring, including the main body of the aircraft, the power system, and the tow rope. The lifesaving device has an ergonomic lifesaving shape, and can quickly and actively reach the rescued object by flying in the air and cruising on the water to carry out rescue, and finally the rescuer will drag the lifesaving device and the rescuer to a safe area through the towing rope of the lifesaving device .

The present invention provides an amphibious water surface life preserver based on the aerodynamic layout of box-type wings, and its operating principle is as follows:

1) Driven by four powered rotors, the amphibious water surface life preserver flies in the air, and when it flies to the target position, the amphibious water surface life preserver lands on the water surface at a fixed point.

2) When the amphibious surface life preserver falls on the water surface, it acts as a swimming ring, allowing the body of the searched and rescued object to penetrate into the closed ring structure of the life preserver to rescue the searched and rescued object.

3) At this time, one end of the tow rope is fixed to the amphibious surface life-saving device, and the other end is in the hands of the rescuer, and the rescuer pulls the tow rope to make the amphibious surface life-saving device cruise on the water surface, and then transport the searched and rescued object to shore, to achieve rescue.

The extension effect of the present invention is:

(1) Through the research and development process of the target life preserver, explore the best solution to integrate the unmanned aerial vehicle, unmanned ship, and lifebuoy, so as to make new developments in the amphibious unmanned aerial vehicles.

(2) Explore a new way of rescue, create a precedent for drone autonomous rescue, and provide new innovative ideas for other life-saving devices.

(3) When there is no rescue mission, the UAV can be equipped with a payload with specific functions, so as to complete emergency support work such as lighting and on-duty, complete survey tasks such as water quality and humidity, and provide navigation and location information. provide tactical assistance.

The amphibious water surface life preserver based on box wing aerodynamic layout provided by the present invention has the following advantages:

(1) The aircraft has an ergonomic life-saving shape through the box-shaped wing layout, and has three functions of drone, unmanned ship, and lifebuoy. With self-rescue function.

(2) It makes up for the inaccurate and random defects of the existing UAV rescue method, improves rescue efficiency, and maximizes the survival rate of the rescued.

The above is only a preferred embodiment of the present invention, it should be pointed out that, for those of ordinary skill in the art, without departing from the principle of the present invention, some improvements and modifications can also be made, and these improvements and modifications can also be made. It should be regarded as the protection scope of the present invention.

Claims (1)

1. An amphibious water surface life preserver based on box-type wing aerodynamic layout, it is characterized in that, the profile of the amphibious type water surface life preserver based on box-type wing aerodynamic layout is a box-type wing aerodynamic layout, comprising: front wing ( 1), rear wing (2), left front and rear wing connection section (3), right front and rear wing connection section (4), first power rotor (5), second power rotor (6), third power rotor ( 7) and the fourth power rotor (8); The front wing (1), the left front and rear wing connection section (3), the rear wing (2) and the right front and rear wing connection section (4) are connected end to end to form a closed ring structure; The front wing (1) and the rear wing (2) are horizontally arranged in parallel; the height of the front wing (1) is lower than the height of the rear wing (2); On the upper airfoil surface of the nose of the front wing (1), the first power rotor (5) is fixedly installed; on the upper airfoil surface of the left wing tip position of the front wing (1), fixed The second power rotor (6) is installed; on the upper airfoil surface of the right wing tip position of the front wing (1), the third power rotor (7) is fixedly installed; on the rear wing (2) ) on the airfoil surface of the tail position, the fourth power rotor (8) is fixedly installed; wherein, the first power rotor (5), the second power rotor (6), the third power rotor (7) is arranged in parallel with the fourth power rotor (8); Wherein, the airfoils of the front wing (1) and the rear wing (2) are the same, which are symmetrical airfoils; the airfoil chord length is defined as c, and the leading edge of the airfoil is a semicircular arc with a radius of R, and the airfoil The trailing edge is a semicircular arc with a radius of r, then: R/c=0.2～0.4, r/c=0.05～0.1; define the wingspan as L, L/c=4～7; Among them, the center of the semicircle arc of the leading edge of the airfoil and the center of the semicircle arc of the trailing edge of the airfoil are on a horizontal line, and the upper end point (A1) of the semicircle arc of the leading edge of the airfoil and the upper point of the semicircle arc of the trailing edge of the airfoil The end point (A2) is connected by the upper airfoil straight line (F1); the lower end point (B1) of the airfoil leading edge semicircle arc and the lower end point (B2) of the airfoil trailing edge semicircle arc are connected by the lower airfoil straight line ( F2) connect; Wherein, the shape of the amphibious surface lifesaving device based on the aerodynamic layout of the box wing is mirror-symmetrical about the central axis of the fuselage; Front wing sweep angle _θ1 is the included angle between the leading edge of the front wing and the vertical line of the central axis of the fuselage; The rear wing sweep angle _θ2 is the angle between the leading edge of the rear wing and the vertical line of the central axis of the fuselage; Then there are: front wing sweep angle θ ₁ = rear wing sweep angle θ ₂ ; Wherein, the front wing (1) includes integrally formed left front wing (H1), right front wing (H2) and front wing connecting transition section (H3); The connecting transition section (H3) of the front wing is a circular arc with a central angle of θ ₃ , and the left end point of the connecting transition section (H3) of the front wing extends outwards from the linear left front wing (H1), so The right end point of the front wing connection transition section (H3) extends outwards to a straight line of the right front wing portion (H2); The shape of the rear wing (2) is the same as that of the front wing (1); Among them, central angle θ ₃ =2θ ₁ ; Wherein, the height difference between the front wing (1) and the rear wing (2) is h, h/c=0.7～1.2; Wherein, the connecting section of the left front and rear wings (3) and the connecting section of the right front and rear wings (4) are thin plates with thickness d; d/c=0.2～0.3; The angle between the left front and rear wing connecting section (3) and the horizontal direction is the same as the angle between the right front and rear wing connecting section (4) and the horizontal direction, both being β; Among them, β=30～60°; Among them, the total length of the fuselage is defined as Z, Z/c=5～7; The distance from the first powered rotor (5) to the front end of the lifeguard is x ₁ , x ₁ /Z=0.05～0.07; The distance from the second powered rotor (6) to the front end of the life preserver is the same as the distance from the third powered rotor (7) to the front end of the life preserver, both are x ₂ , x ₂ /Z=0.35～0.37; The distance from the second power rotor (6) to the left tip of the front wing (1) is the same as the distance from the third power rotor (7) to the right wing tip of the front wing (1), Both are y, y/c=0.35～0.45; The distance between the fourth power rotor (8) and the front end of the lifeguard is x ₃ , and x ₃ /Z=0.93-0.95.

Images