Active lift-augmentation tandem wing type ground effect aircraft

Abstract

The invention relates to an active lift augmentation tandem wing type ground effect aircraft, and relates to the field of ground effect aircrafts. The defects that a stable take-off environment is needed, take-off time is long, and operation is complex are overcome. An active lift-increasing tandem wing type ground effect aircraft comprises a machine body, a cockpit is formed in the middle of the top of the machine body, connecting pieces symmetrically arranged in the direction of the machine body are fixedly installed on the front side and the rear side of the machine body correspondingly, and wing structures are fixedly connected to the connecting pieces on the front side and the connecting pieces on the rear side correspondingly; the inclination angle between the wing structures fixed to the connecting pieces on the front side of the aircraft body and the ground, the inclination angle between the wing structures fixed to the connecting pieces on the rear side of the aircraft body and the ground and the inclination angle between the wing structures fixed to the connecting pieces on the rear side of the aircraft body are larger than the inclination angle of the front-side wings. By means of the tandem wing type layout, the inclination angles of the paddles, the front wing structure and the rear wing structure relative to the ground are increased, and when the aircraft runs, the aircraft can obtain the maximum lift force compensation under the influence of the ground effect.

Description

Technical Field

[0001] The invention relates to the field of ground effect vehicles, and in particular to an active lift-enhancing tandem-wing ground effect vehicle. Background Art

[0002] A ground effect vehicle is a multimedia aircraft that can fly across water, ground, shallows, reefs, gravel and other terrains without obstacles. It has the advantages of high lift, high flexibility and stable flight.

[0003] When existing aircraft fly over water, they usually need to accelerate and glide on the water surface for a certain distance. During the gliding process, the aircraft's ailerons and multiple flight control surfaces need to swing in coordination to obtain a sufficiently large lift coefficient to complete takeoff. In this process, a stable takeoff environment is required, the takeoff time is long, and the operation is complicated. Summary of the invention

[0004] In order to overcome the disadvantages of requiring a stable take-off environment, long take-off time and complex operation, the purpose of the present invention is to provide an active lift-enhancing tandem-wing ground effect vehicle.

[0005] The technical scheme is: an active lift-enhancing tandem-wing ground-effect vehicle, comprising an organism, a cockpit is provided in the middle of the top of the organism, connecting pieces symmetrically arranged along the direction of the organism are fixedly installed on the front and rear sides of the organism, the front connecting piece and the rear connecting piece are fixedly connected with a wing structure, the wing structure fixed with the connecting piece on the front side of the organism and the ground have an inclination angle of 7° to 9°, the wing structure fixed with the connecting piece on the rear side of the organism and the ground have an inclination angle of 6° to 8°, the front wing inclination angle is greater than the rear wing inclination angle, and the aircraft's own equipment load is arranged on the front side of the organism, for To achieve the self-load balance of the aircraft during flight, the fuselage is fixedly connected to a fixing frame symmetrically arranged along the fuselage, a vertical tail is connected to the side of the fuselage away from the fixing frame, the symmetrically arranged fixing frame is fixedly connected to a fixing tube, the fixing tube is fixedly connected to a cable tube symmetrically arranged along the fixing tube, a brushless motor is fixedly installed on the side of the cable tube away from the fuselage, the output end of the brushless motor is fixedly connected to a blade, the wind outlet surface and the bottom surface of the blade are inclined at an angle of 40° to 60°, and are used to guide air between the wing and the ground, so as to generate a ground effect between the aircraft and the ground or water surface during operation.

[0006] As a further preferred solution, the wing structure on the front side of the fuselage has exactly the same shape and area as the wing structure on the rear side.

[0007] As a further preferred embodiment, the height of the trailing edge of the wing structure is flush with the ground or water surface.

[0008] As a further preferred embodiment, a skid is also included, which is fixedly connected to the side of the wing away from the fuselage structure. The skid extends downward from the bottom of the wing to form a supporting surface, which is used to increase the contact area between the aircraft and the ground or water surface. A retaining wall is formed between the skid and the bottom of the wing to prevent airflow from diffusing.

[0009] As a further preferred solution, a winglet is also included, which is fixedly connected to the side of the rear wing structure away from the fuselage and is used to reduce the wingtip vortex generated during the flight of the aircraft.

[0010] As a further preferred scheme, it also includes a steering wheel, which is rotatably connected to the fuselage, the steering wheel is located on the front side of the cockpit, and an angle sensor is fixedly installed on the side of the fuselage adjacent to the steering wheel. The angle sensor is in contact with the steering wheel, and the angle sensor is electrically connected to the brushless motor through the control module, so as to control the power of the brushless motor, thereby realizing the control of the aircraft's turning and U-turn.

[0011] As a further preferred solution, the front side of the fuselage is provided with a guide surface inclined toward the rear side for reducing resistance when gliding on the water surface. The bottom of the fuselage is concave upward to form at least two step surfaces for reducing the area of ​​contact with the water surface when the aircraft is flying on the water surface.

[0012] As a further preferred embodiment, the wing structure also includes a circular main beam, which runs through the wall of the fuselage. There are at least four circular main beams, and each group of two circular main beams. The two circular main beams in each group are respectively fixedly connected to the front and rear sides of the fuselage. The two circular main beams in each group are fixedly connected to the wing ribs with equal spacing, and the wing ribs with equal spacing are fixedly connected to each other in an interlaced manner with stringers with equal spacing, and the outer sides of the stringers and the wing ribs are fixedly covered with skin.

[0013] The beneficial effects of the present invention are as follows: the present invention increases the inclination angle between the blades and the front and rear wing structures and the ground through a tandem-wing layout. When the aircraft is in operation, under the influence of the ground effect, the aircraft can obtain maximum lift compensation, so that the aircraft can be quickly lifted up without gliding. At the same time, it avoids the phenomenon of separation of the airflow on the wing surface when the aircraft is started due to the excessively large inclination angle of the front and rear wings, thereby causing a decrease in lift compensation.

[0014] The diffusion of the high-pressure airflow at the bottom of the wing structure is blocked by the retaining wall, thereby further improving the utilization rate of the ground effect high-pressure airflow.

[0015] By making the angle of attack of the front wing structure larger than that of the rear wing structure, the front wing mechanism can drive the weight-bearing part of the fuselage to lift up quickly, thereby reducing the load pressure on the rear side of the fuselage. At the same time, when the angle of the front wing structure is too large, the front wing structure will stall, causing the front side of the fuselage to drop, preventing the fuselage from lifting up excessively, and automatically maintaining the pitch balance of the aircraft, thereby achieving rapid takeoff. By turning the steering wheel to control the power of the brushless motor on one side of the fuselage to achieve small radius turns and U-turns, compared with traditional aircraft that control the wing control surfaces through connecting rods, the complex multi-link mechanism is removed, does not rely on pneumatic control surfaces, is simple to operate, has a small turning radius, and is fast, which greatly simplifies the operation process of the aircraft.

[0016] Through the design of the hull guide surface, the gliding resistance of the aircraft is reduced when gliding on the water.

[0017] The multiple step surfaces at the bottom of the wing allow the aircraft to take off more smoothly and quickly when leaving the water.

[0018] By installing a circular main beam that penetrates and fixes the fuselage and the wing structure, the fuselage and the wing structure are firmly fixed together, which greatly improves the strength of the wing structure and the fuselage while reducing the weight, thereby ensuring the safety of the structure when the aircraft is flying. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention.

[0020] Figure 2 It is a side view of the three-dimensional structure of the present invention.

[0021] Figure 3 It is a three-dimensional structural schematic diagram of the body and steering wheel components of the present invention.

[0022] Figure 4 It is a schematic diagram of the three-dimensional structure of the components such as the slide, the guide surface and the step surface of the present invention.

[0023] Figure 5 It is a three-dimensional structural schematic diagram of components such as the cable tray, brushless motor and blades of the present invention.

[0024] Figure 6 It is a schematic diagram of the three-dimensional structure of the circular main beam, girders, wing ribs and other components of the present invention.

[0025] Names of the numbers in the figure: 1- fuselage, 2- cockpit, 21- steering wheel, 22- angle sensor, 3- wing structure, 31- circular main beam, 32- stringer, 33- wing rib, 34- skin, 4- fixing frame, 5- connecting plate, 6- vertical tail, 7- fixing tube, 8- wiring tube, 9- brushless motor, 10- blade, 11- skid, 111- retaining wall, 12- wingtip winglet, 13- guide surface, 14- step surface. DETAILED DESCRIPTION

[0026] The technical solution is further described below in conjunction with specific embodiments. It should be noted that the words indicating directions such as up, down, left, and right mentioned in this article are only for the position of the structure shown in the corresponding drawings. The serial numbers of the parts in this article, such as first, second, etc., are only used to distinguish the objects described and do not have any order or technical meaning. The words such as connection and coupling in this application include direct and indirect connection (coupling) unless otherwise specified.

[0027] Embodiment 1: An active lift-enhancing tandem-wing ground effect vehicle, such as Figure 1-Figure 5 As shown, it includes an organism 1, a cockpit 2 is provided in the middle of the top of the organism 1, connecting pieces 5 symmetrically arranged along the direction of the organism 1 are fixedly installed on the front and rear sides of the organism 1, and the front connecting piece 5 and the rear connecting piece 5 are fixedly connected with a wing structure 3, the wing structure 3 fixed with the connecting piece 5 on the front side of the organism 1 is inclined at an angle of 9° to the ground, and the wing structure 3 fixed with the connecting piece 5 on the rear side of the organism 1 is inclined at an angle of 8° to the ground, and the inclination angle of the front wing is greater than the inclination angle of the rear side by 1°, and the self-load balance of the aircraft during flight is achieved by setting the load of the aircraft's own equipment on the front side of the aircraft 1, and the wing structure 3 on the front side of the aircraft 1 and the rear side of the aircraft are inclined at an angle of 8° to the ground. The shape and area of ​​the wing structure 3 are exactly the same, the height of the trailing edge of the wing structure 3 is flush with the ground or water surface, the front side of the fuselage 1 is fixedly connected to a fixing frame 4 symmetrically arranged along the fuselage 1, and a vertical tail 6 is connected to the top of the rear side of the fuselage, and the symmetrically arranged fixing frame 4 is fixedly connected to a fixing tube 7, and the fixing tube 7 is fixedly connected to a cable tube 8 symmetrically arranged along the fixed tube 7, and a brushless motor 9 is fixedly installed on the outside of the cable tube 8, and a blade 10 is fixedly connected to the output end of the front side of the brushless motor 9, and the wind outlet surface of the blade 10 is inclined at an angle of 60° to the bottom surface, which is used to guide air between the wing and the ground, and is used for the aircraft to produce a ground effect with the ground or water surface during operation.

[0028] like Figure 1 and Figure 4 As shown, it also includes a skid 11, which is fixedly connected to the outer side of the wing. The skid 11 extends downward from the bottom of the wing to form a supporting surface for the aircraft to increase the contact area with the ground or water surface. A retaining wall 111 is formed between the skid 11 and the bottom of the wing to prevent airflow from diffusing.

[0029] First, when the aircraft stays on the water surface, the skid 11 on the outside of the wing structure 3 is used to increase the contact area between the aircraft and the water surface, ensuring that the aircraft does not tilt to one side when it stays on the water surface. When it is necessary to fly, the brushless motor 9 is started, and the brushless motor 9 drives the blades 10 to rotate. The rotation of the blades 10 drives the airflow to flow toward the rear and lower side at high speed. After the airflow passes through the wing structures 3 on the front and rear sides of the fuselage 1, the air flow rate on the upper side of the wing structure 3 is greater than the air flow rate on the lower side of the wing structure 3. The air flow rate on the upper side of the wing structure 3 is fast and the pressure is low, so that the wing structure 3 generates lift, and then the airflow flows toward the water surface and the ground. Due to the ground effect, after the airflow passes through the wing, when it reaches the bottom of the fuselage 1, the air between the lower surface of the wing structure and the water surface and the ground is squeezed to form a high-pressure area like an air cushion, thereby increasing the lift. The pressure difference between the upper and lower surfaces of the wing structure 3 is increased. At the same time, the diffusion of the airflow in the high-pressure area at the bottom of the wing structure 3 is further blocked by the retaining wall 111 between the skid 11 and the wing structure 3. This enables the aircraft to obtain additional lift, thereby increasing the lift at the bottom of the aircraft. Under the support of the lift generated by the above-mentioned airflow and ground effect, the front wing structure 3 is driven by the force to quickly lift the front side of the fuselage 1 upward. Since the inclination angle of the front wing is greater than the inclination angle of the rear wing structure 3 during the lifting process of the fuselage 1, the obtained lift coefficient is greater than that of the rear wing structure 3. During the lifting process of the fuselage 1, the main load of the aircraft itself is lifted, and the load pressure of the rear wing structure 3 is reduced. Subsequently, the rear wing structure 3 is affected by the airflow and ground effect, driving the rear side of the fuselage 1 to follow and lift up, completing the takeoff. During takeoff, when the front wing structure 3 is subjected to excessive lift, causing the front side of the fuselage 1 to over-lift, the wing changes with the pitch of the fuselage, and the angle of attack between the wing chord and the relative airflow increases. When the angle of attack exceeds the critical value, the flow state of the airflow on the upper surface of the wing will be destroyed, causing stall, reducing the lift of the wing, causing the front side of the fuselage 1 to automatically press down, restoring the pitch balance of the aircraft, thereby ensuring that the aircraft maintains a balanced state during takeoff. When the entire fuselage 1 is about 20 centimeters above the ground, the takeoff action is completed; Subsequently, as the throttle continues to increase, the aircraft flies forward, and the vertical tail 6 on the rear side of the fuselage 1 is used to maintain the heading of the aircraft during flight, preventing the aircraft from deviating from its heading or rotating during flight. In summary, the present invention increases the inclination angle between the blades 10 and the front and rear wing structures 3 and the ground through a tandem wing layout. When the aircraft is running, under the influence of the ground effect, the aircraft can obtain maximum lift compensation, so that the aircraft can be quickly lifted up without gliding. At the same time, it avoids the separation of the airflow on the upper surface of the wing when the aircraft starts due to the excessive design of the inclination angle of the front and rear wings, thereby causing a decrease in lift compensation. The phenomenon occurs. During takeoff, the diffusion of the high-pressure airflow at the bottom of the wing structure 3 is blocked by the retaining wall 111, thereby further improving the utilization rate of the ground effect high-pressure airflow. During takeoff, the angle of attack of the front wing structure 3 is greater than the angle of attack of the rear wing structure 3, so that the front wing mechanism can drive the weight-bearing part of the fuselage 1 to lift up quickly, thereby reducing the load pressure on the rear side of the fuselage 1. At the same time, when the lifting angle of the front wing structure 3 is too large, the front wing structure 3 stalls, causing the front side of the fuselage 1 to descend, preventing the fuselage 1 from lifting up excessively, and automatically maintaining the pitch balance of the aircraft, thereby achieving a quick takeoff.

[0030] Embodiment 2: Based on embodiment 1, Figure 1 As shown, a wingtip winglet 12 is also included. The wingtip winglet 12 is fixedly connected to the side of the rear wing structure 3 away from the fuselage 1, and is used to reduce the wingtip vortex generated by the aircraft during flight, while achieving the function of the vertical tail and maintaining flight stability.

[0031] like Figure 1 and Figure 3 As shown, a steering wheel 21 is also included, which is rotatably connected to the top of the body 1. The steering wheel 21 is located on the front side of the cockpit 2. An angle sensor 22 is fixedly installed on one side of the body 1 adjacent to the steering wheel 21. The angle sensor 22 is in contact with the steering wheel 21. The angle sensor 22 is electrically connected to the brushless motor 9 through the control module, and is used to control the power of the brushless motor 9, thereby realizing the control of the aircraft's turning and U-turn.

[0032] In order to make the aircraft easier to control during flight, the specific operations are as follows: by increasing the power of the brushless motor 9, the blades 10 rotate faster, thereby increasing the air flow rate and making the aircraft fly forward. During flight, the stability of the aircraft is maintained by the vertical tail 6. Then, the winglets 12 arranged on both sides of the rear wing structure 3 reduce the wingtip vortex caused by the airflow passing through the rear wing structure 3, thereby reducing the induced drag generated by the wingtip vortex, further ensuring the stability of the flight attitude. When the aircraft needs to turn during flight, for example, turning to the right, by turning the steering wheel 21 clockwise, the angle sensor 22 sends an electrical signal when detecting the rotation of the steering wheel 21. After receiving the electrical signal, the control module controls the brushless motor 9 located on the left side of the body 1 to increase the power, so that the left side of the aircraft turns. The air flow rate on the side is accelerated, and the power of the brushless motor 9 located on the right side of the body 1 is adaptively reduced. Through the flow rate difference of the airflow on the left and right sides of the body 1, the wing on the left side of the body 1 is driven to deflect quickly to the right to realize the turning or U-turn of the aircraft. When the steering wheel 21 is rotated more, the greater the power of the controlled brushless motor 9 is, the faster the turning and U-turn speed of the aircraft is. When the aircraft completes the turn or U-turn, the steering wheel 21 can be straightened. In summary, the power of the brushless motor 9 on one side of the body 1 is controlled by rotating the steering wheel 21 to realize small-radius turns and U-turns. Compared with traditional aircraft that realize turning or U-turns by controlling the wing control surfaces through connecting rods, the complex multi-link mechanism is eliminated, does not rely on pneumatic control surfaces, is simple to operate, has a small turning radius, and a fast speed, which greatly simplifies the operation process of the aircraft.

[0033] Embodiment 3: Based on embodiment 2, Figure 2 and Figure 4 As shown, the lower front part of the fuselage 1 is provided with a guide surface 13 inclined toward the rear side for reducing the resistance when gliding on the water surface. The bottom of the fuselage 1 is concave upward to form two step surfaces 14 for reducing the area of ​​contact with the water surface when the aircraft is flying on the water surface.

[0034] When the aircraft is gliding on the water, in order to ensure that the aircraft flies more smoothly from the water to the air, the specific operation is as follows: when the aircraft is gliding on the water, the guide surface 13 on the front side of the body 1 is used to reduce the resistance of the aircraft when gliding on the water. When it is necessary to fly during the gliding process, the power of the brushless motor 9 is increased to make the body 1 glide quickly on the water. The contact between the bottom of the body 1 and the water surface is reduced through the multiple step surfaces 14 at the bottom of the body 1. When the aircraft accelerates, the step surfaces 14 can quickly push the water away, reduce the water resistance, and make it easier for the aircraft to take off. In summary, through the design of the hull guide surface 13, the gliding resistance of the aircraft is reduced when gliding on the water. At the same time, when the aircraft is flying away from the water, the multiple step surfaces 14 at the bottom of the wing are used to achieve a smoother and faster take-off when the aircraft glides.

[0035] Embodiment 4: Based on embodiment 3, Figure 6 As shown, the wing structure 3 also includes a circular main beam 31, which runs through the left and right walls of the fuselage 1. There are four circular main beams 31, and each two circular main beams 31 form a group. The two circular main beams 31 in each group are respectively fixedly connected to the front and rear sides of the fuselage 1. The circular main beams 31 are made of carbon fiber material, and the two circular main beams 31 in each group are fixedly connected with wing ribs 33 with equal intervals. The wing ribs 33 with equal intervals are fixedly connected with stringers 32 with equal intervals in an interlaced manner. The outer sides of the stringers 32 and the wing ribs 33 are fixedly covered with skins 34.

[0036] In order to further strengthen the strength of the wing structure 3 and the fuselage 1, a circular main beam 31 is fixedly installed between the wing structure 3 and the fuselage 1, so that the fuselage 1 and the wing structure 3 are firmly fixed together, so that the strength of the wing structure 3 and the fuselage 1 is greatly improved while reducing the weight, thereby ensuring the safety of the structure when the aircraft is flying.

[0037] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An active lift-enhancing tandem-wing ground-effect vehicle, characterized in that: The invention comprises an organism (1), wherein a cockpit (2) is provided in the middle of the top of the organism (1), and connecting pieces (5) are fixedly installed on the front and rear sides of the organism (1) and are symmetrically arranged along the direction of the organism (1), and the front connecting piece (5) and the rear connecting piece (5) are both fixedly connected to a wing structure (3), and the wing structure (3) fixed to the connecting piece (5) on the front side of the organism (1) has an inclination angle of 7° to 9° with the ground, and the wing structure (3) fixed to the connecting piece (5) on the rear side of the organism (1) has an inclination angle of 6° to 8° with the ground, and the inclination angle of the front wing is greater than the inclination angle of the rear wing, and the self-load of the aircraft during flight is realized by arranging the equipment load of the aircraft on the front side of the organism (1). The invention relates to a balance device, wherein a fuselage (1) is fixedly connected to a fixing frame (4) symmetrically arranged along the fuselage (1), a side of the fuselage (1) away from the fixing frame (4) is connected to a vertical tail (6), the symmetrically arranged fixing frame (4) is fixedly connected to a fixing pipe (7), the fixing pipe (7) is fixedly connected to a cable duct (8) symmetrically arranged along the fixing pipe (7), a brushless motor (9) is fixedly installed on the side of the cable duct (8) away from the fuselage (1), an output end of the brushless motor (9) is fixedly connected to a blade (10), the wind outlet surface of the blade (10) and the bottom surface are inclined at an angle of 40° to 60°, and are used to guide air between the wing and the ground, so as to generate a ground effect with the ground or water surface during the operation of the aircraft.

2. An active lift-enhancing tandem-wing ground effect vehicle as claimed in claim 1, characterized in that: The wing structure (3) on the front side of the fuselage (1) and the wing structure (3) on the rear side have the same shape and area.

3. An active lift-enhancing tandem-wing ground-effect vehicle as claimed in claim 2, characterized in that: The height of the trailing edge of the wing structure (3) is flush with the ground or water surface.

4. An active lift-enhancing tandem-wing ground effect vehicle as claimed in claim 3, characterized in that: The invention also includes a skid (11), which is fixedly connected to a side of the wing away from the body (1) structure. The skid (11) extends downward from the bottom of the wing to form a support surface for increasing the contact area between the aircraft and the ground or water surface. A retaining wall (111) is formed between the skid (11) and the bottom of the wing to prevent airflow from diffusing.

5. An active lift-enhancing tandem-wing ground-effect vehicle as claimed in claim 4, characterized in that: It also includes a winglet (12), which is fixedly connected to a side of the rear wing structure (3) away from the fuselage (1) and is used to reduce wingtip vortices generated by the aircraft during flight.

6. An active lift-enhancing tandem-wing ground-effect vehicle as claimed in claim 5, characterized in that: The invention also comprises a steering wheel (21), the steering wheel (21) being rotatably connected to the body (1), the steering wheel (21) being located at the front side of the cockpit (2), an angle sensor (22) being fixedly mounted on a side of the body (1) adjacent to the steering wheel (21), the angle sensor (22) being in contact with the steering wheel (21), the angle sensor (22) being electrically connected to the brushless motor (9) via a control module, and being used to control the power of the brushless motor (9), thereby realizing the control of turning and U-turning of the aircraft.

7. An active lift-enhancing tandem-wing ground effect vehicle as claimed in claim 6, characterized in that: The front side of the fuselage (1) is provided with a guide surface (13) inclined toward the rear side, which is used to reduce the resistance when gliding on the water surface. The bottom of the fuselage (1) is concave upward to form at least two step surfaces (14), which are used to reduce the area of ​​contact with the water surface when the aircraft is flying on the water surface.

8. An active lift-enhancing tandem-wing ground effect vehicle as claimed in claim 7, characterized in that: The wing structure (3) also includes a circular main beam (31), the circular main beam (31) penetrates the wall of the fuselage (1), the number of the circular main beams (31) is at least four, and the circular main beams (31) form a group of two. The two circular main beams (31) in each group are respectively fixedly connected to the front and rear sides of the fuselage (1), and the two circular main beams (31) in each group are fixedly connected to the wing ribs (33) with equal spacing, and the wing ribs (33) with equal spacing are fixedly connected to each other in an interlaced manner. The outer sides of the stringers (32) and the wing ribs (33) are fixedly covered with skins (34).

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