Ground effect aircraft capable of reducing steering radius
By adding spoiler and water skiing board to the ground effect aircraft and controlling its swing through the drive mechanism, the problem of a large steering radius and easy to touch water in the traditional ground effect aircraft is solved, and the effect of a small radius steering is achieved.
Patent Information
- Application Number
- CN202422024654.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-20
- Publication Date
- 2025-05-16
- Estimated Expiration
- 2034-08-20
AI Technical Summary
Due to the limited flight altitude of traditional ground-effect aircraft, it is difficult to achieve small radius steering, the steering radius is extremely large, and it requires rolling to turn, which is easy to lose control due to contact with water.
The spoiler and water skiing plates designed to swing upwards through the first driving mechanism, and the second driving mechanism drives the water skiing plates to swing downwards, so that the water skiing plates come into contact with the water surface or press into the water, increasing the resistance on one side of the aircraft, thereby obtaining a larger yaw torque and achieving small radius steering.
By adding spoiler and water ski plate design, the aircraft can reduce the steering radius within a controllable range, achieve small radius steering, and avoid the risk of water contact due to rolling steering.
Smart Images
Figure CN222876271U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of ground effect vehicles, in particular to a ground effect vehicle capable of reducing a turning radius. Background Art
[0002] Ground effect vehicles usually refer to aircraft that use the ground effect to fly at low altitudes close to the water surface. The ground effect is when the aircraft approaches the water surface, the wings compress the air, forming a layer of high-pressure air cushion under the wings, which generates additional lift in addition to the original wing lift. Compared with ordinary high-altitude aircraft, ground effect vehicles have a larger and stronger carrying capacity because of the additional lift provided by the ground effect. Compared with ordinary ships, ground effect vehicles do not need to be in direct contact with the water surface for a long time, so they can achieve higher speeds, greatly improving the efficiency and maneuverability of water surface transportation.
[0003] Ground effect vehicles generally need to fly at an altitude within the range of ground effect, so the flight altitude is relatively low and the fuselage is relatively close to the water surface. Traditional ground effect vehicles mostly use the rudder located at the tail to control the yaw of the aircraft to achieve the steering of the aircraft. Some also cooperate with the ailerons located on the main wings to roll and turn. Existing steering methods require the aircraft to roll, but due to the limited flight altitude of ground effect vehicles, in order to avoid the fuselage touching the water and disintegrating, it can only roll at a smaller angle. Therefore, the turning radius of the aircraft is extremely large, and it is difficult to achieve a small radius steering. Utility Model Content
[0004] The utility model provides a ground effect vehicle capable of reducing a turning radius. The ground effect vehicle can lower a fuselage through an additional spoiler, so that the vehicle presses a water ski into water within a controllable range under the action of the spoiler, thereby increasing the resistance on one side of the vehicle, thereby obtaining a larger yaw moment and realizing a small radius turning.
[0005] In order to achieve the above object, the utility model provides the following technical solutions:
[0006] A ground effect vehicle capable of reducing a turning radius, the ground effect vehicle comprising a fuselage, a power system, a main wing, a float and a flight control system;
[0007] The power system is symmetrically installed on both sides of the front part of the fuselage, and the main wings are symmetrically installed on both sides of the middle part; the power system includes an engine and a propeller; the engine has a pitch angle;
[0008] The main wing includes an airfoil, an aileron and a main beam; the aileron is rotatably connected to the rear side of the airfoil; the end of the main beam is fixedly connected to the buoy;
[0009] The buoy includes a buoy body, a spoiler, a water ski, a first driving mechanism and a second driving mechanism; one end of the spoiler, the water ski, the first driving mechanism and the second driving mechanism are all rotatably installed in the buoy body; the other end of the first driving mechanism is hinged to the middle of the spoiler, and is used to drive the spoiler to swing in a vertical plane to extend out of the upper side of the buoy body; the other end of the second driving mechanism is hinged to the middle of the water ski, and is used to drive the water ski to swing in a vertical plane to extend out of the lower side of the buoy body;
[0010] When the ground effect vehicle needs to turn toward one side, the flight control system controls the first driving mechanism on the side to drive the spoiler to swing upward, and controls the second driving mechanism on the side to drive the water ski to swing downward, while keeping the spoiler and the water ski on the other side stationary, thereby obtaining a yaw moment to achieve a small radius turn.
[0011] Furthermore, it also includes a slip ring corresponding to each of the water skis;
[0012] The water ski is mounted on the main beam through the slip ring.
[0013] Furthermore, the first driving mechanism and the second driving mechanism are both hydraulic cylinders;
[0014] The spoiler and the water ski are connected to the piston rod of the hydraulic cylinder.
[0015] Furthermore, the rotation directions of the two engines are opposite;
[0016] The two propellers are both forward and reverse propellers, which are used to balance the torque caused by the rotation of the propellers to reduce the rudder trim.
[0017] Furthermore, it also includes a vertical tail and a horizontal tail;
[0018] The vertical tail is fixedly mounted on the tail of the fuselage;
[0019] The two horizontal tails are distributed in a V shape and are symmetrically installed on both sides of the vertical tail; the horizontal tail includes a horizontal stabilizer and an elevator; the elevator is rotatably connected to the rear side of the horizontal stabilizer and is linked and controlled by the flight control system to achieve pitch action.
[0020] Furthermore, the vertical tail includes a vertical stabilizer and a rudder rotatably mounted on the rear side of the vertical stabilizer;
[0021] The rudder is controlled by the flight control system to achieve yaw action.
[0022] Furthermore, the horizontal tail has an upward dihedral angle, so that the ground effect vehicle generates a centering moment when rolling.
[0023] Furthermore, the power system further includes an engine nacelle fixedly mounted on both sides of the fuselage;
[0024] The engine is fixedly installed in the engine compartment;
[0025] The propeller is rigidly connected to the engine via a transmission shaft, so that the propeller has a pitch angle.
[0026] Furthermore, the main wing also includes a plurality of ribs fixedly connected to the main beam; the ribs are used to increase the structural strength of the main wing.
[0027] Furthermore, the flight control system includes an airspeed meter and an altimeter, and determines the flight status based on the airspeed meter and the altimeter.
[0028] Compared with the prior art, the ground effect vehicle of the utility model has the following beneficial effects:
[0029] The ground effect vehicle of the utility model is provided with a spoiler and a water ski on the buoy, and the first driving mechanism drives the spoiler to swing upward to generate an upward torque, so that the main wing on that side moves downward, and the second driving mechanism drives the water ski to swing downward so that the water ski contacts the water surface or is pressed into the water, thereby increasing the resistance on one side of the vehicle, so that the vehicle obtains a larger yaw moment, reduces the turning radius, and realizes a small radius turn. BRIEF DESCRIPTION OF THE DRAWINGS
[0030] Figure 1 A top view of the ground effect vehicle of the utility model;
[0031] Figure 2 It is a side view of the ground effect vehicle of the utility model;
[0032] Figure 3 It is a front view of the ground effect vehicle of the utility model;
[0033] Figure 4 A side view of a float of the ground effect vehicle of the utility model;
[0034] Figure 5 The utility model is a side view of another buoy of the ground effect vehicle.
[0035] Among them, 1-fuselage, 2-power system, 3-main wing, 4-float, 5-vertical tail, 6-horizontal tail, 21-engine, 22-propeller, 23-engine compartment, 24-transmission shaft, 31-wing surface, 32-aileron, 33-main beam, 41-float body, 42-spoiler, 43-water ski, 44-first drive mechanism, 45-second drive mechanism, 46-slip ring, 51-vertical stabilizer, 52-rudder, 61-horizontal stabilizer, 62-elevator. DETAILED DESCRIPTION
[0036] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0037] Traditional ground effect vehicle, in order to reach the ground effect area, needs many groups of engines and vector devices, makes the structure of aircraft extremely complicated.Thereby traditional ground effect vehicle uses rudder 52 to control the yaw of aircraft to realize the turning of aircraft more, some also cooperate aileron 32 to roll thereby turn, and all steering modes all need aircraft to make roll, but because ground effect vehicle flying height is limited, so in order to avoid the body touching water and losing control and disintegrating, can only roll with less angle, so turning radius becomes very large.And ground effect vehicle of the utility model is by designing engine 21 and propeller 22 that are tilted downward at fixed inclination angle, and by flight control system according to the airspeed that airspeed meter detects, control engine 21 power output, reach the structure with two engines 21 and fixed inclination angle, realized the control of ground effect vehicle take-off and cruising. At the same time, the ground effect vehicle of the utility model is designed with a spoiler 42 extending upward and a water ski 43 in contact with the water surface, so that the aircraft can press down the fuselage 1 under the action of the spoiler 42, and press the water ski 43 into the water within a controllable range, thereby increasing the resistance on one side of the aircraft, thereby obtaining a larger yaw moment and realizing a small radius turn.
[0038] This embodiment provides a ground effect vehicle that can reduce the turning radius. Figure 1 , Figure 2 and Figure 3 As shown, the ground effect vehicle includes a fuselage 1, a power system 2, a main wing 3, a float 4, a flight control system, a vertical tail 5 and a horizontal tail 6; in this embodiment, Figure 1 is a top view of the ground effect vehicle. Figure 2 This is the left side view of the ground effect vehicle. Figure 3 is the front side view of the ground effect vehicle. Figure 1The lower side of the page where the middle figure is located is the left side of the fuselage 1. Figure 1 The upper side of the page where the middle figure is located is taken as an example for explanation as the right side of the fuselage 1;
[0039] The front two sides of the fuselage 1 are symmetrically provided with a power system 2, the middle two sides are symmetrically provided with a main wing 3, the upper side of the tail of the fuselage 1 is fixedly provided with a vertical tail 5, and two horizontal tails 6 are symmetrically provided on the upper part of the vertical displacement, that is, the left and right sides of the ground effect vehicle are provided with a power system 2, a main wing 3 and a horizontal tail 6;
[0040] The power system 2 is located on both sides of the front end of the fuselage 1, and the power system 2 includes an engine compartment 23, an engine 21 and a propeller 22; the engine compartment 23 is fixedly installed on both sides of the fuselage 1; the engine 21 is fixedly installed in the engine compartment 23, and under the protection of the engine compartment 23, the erosion of the engine 21 by sea breeze and waves can be effectively reduced, which is beneficial to prolonging the life of the engine 21 and reducing the failure rate of the engine 21. The engine 21 has a pitch angle, which can be 15 to 20 degrees; the propeller 22 is rigidly connected to the engine 21 through a transmission shaft 24, so that the propeller 22 has the same pitch angle as the engine 21; the two engines 21 rotate in opposite directions, and the two propellers 22 are both forward and reverse propellers, which are used to balance the torque caused by the rotation of the propeller 22 to reduce the rudder trim, making the aircraft route more accurate and easier to control. Figure 1 and Figure 3 As shown, an engine 21 and a propeller 22 are installed on the left and right sides of the fuselage 1, and the output shaft of the engine 21 is coaxially fixedly connected with the propeller 22 through a transmission shaft 24;
[0041] like Figure 1 As shown, the main wing 3 includes an airfoil 31, an aileron 32, a main beam 33 and a plurality of ribs (not shown in the figure), the main beam 33 and the airfoil 31 constitute the main structure of the main wing 3; the aileron 32 is rotatably connected to the rear side of the airfoil 31, the aileron 32 can rotate up and down, and the aileron 32 is controlled to rotate under the operation of the flight control system to realize the roll of the aircraft; the end of the main beam 33 is fixedly connected to a buoy 4, and the connection between the buoy 4 and the main beam 33 can ensure the structural strength; a plurality of ribs are arranged on the inner side of the airfoil 31, and are fixedly connected to the main beam 33, forming a skeleton structure of the main wing 3; the ribs are used to increase the structural strength of the main wing 3.
[0042] like Figure 1 and Figure 2As shown, the vertical tail 5 is fixedly mounted on the tail of the fuselage 1, and the center of the vertical tail 5 coincides with the center of the width direction of the fuselage 1; The vertical tail 5 comprises a vertical stabilizer 51 arranged in the vertical direction and a rudder 52 that is rotationally mounted on the rear side of the vertical stabilizer 51, and the rudder 52 can swing along the width direction of the fuselage 1; The rudder 52 is controlled by the flight control system, and the yaw action of the ground effect vehicle is realized by the swing of the rudder 52; Two horizontal stabilizers 6 are distributed in a V shape, and are symmetrically mounted on the both sides of the vertical tail 5; The horizontal tail 6 comprises a horizontal stabilizer 61 and an elevator 62 that are tilted; The elevator 62 is rotationally connected to the rear side of the horizontal stabilizer 61, and is controlled by the flight control system linkage, and the pitching action of the ground effect vehicle is realized by the swing of the elevator 62 in the height direction of the fuselage 1; The horizontal tail 6 has an upper dihedral angle, so that the ground effect vehicle produces a return moment when rolling in flight, increases the stability of the aircraft, and avoids the aircraft from losing control, and the upper dihedral angle can be 25~29 °.
[0043] like Figure 1 and Figure 3 As shown, the two pontoons 4 are respectively a left pontoon 4 located on the left side of the fuselage 1 and a right pontoon 4 located on the right side of the fuselage 1. The left and right pontoons 4 have the same structure. The pontoons 4 are fixedly connected to the ends of the main wings 3 on the corresponding sides and are connected to the main beam 33. Figure 4 As shown, the buoy 4 includes a buoy body 41, a spoiler 42, a water ski 43, a first drive mechanism 44 and a second drive mechanism 45; one end of the spoiler 42, the water ski 43, the first drive mechanism 44 and the second drive mechanism 45 are all rotatably installed in the buoy body 41; the spoiler 42 is installed on the upper part of the buoy 4; the other end of the first drive mechanism 44 is hinged to the middle part of the spoiler 42, and is used to drive the spoiler 42 to swing in a vertical plane to extend out of the upper side of the buoy body 41, as shown in FIG. Figure 4 As shown in FIG. 1 , when the spoiler 42 extends out of the top surface of the buoy body 41, the spoiler 42 is tilted, and the rear end of the spoiler 42 is higher than the front end, and an acute angle with the opening facing the tail side is formed between the spoiler 42 and the top surface of the buoy body 41; the water ski 43 is installed at the middle and lower part of the buoy 4; the other end of the second driving mechanism 45 is hinged to the middle part of the water ski 43, and is used to drive the water ski 43 to swing in the vertical plane to extend out of the lower side of the buoy body 41, as shown in FIG. Figure 4As shown, when the water ski 43 extends out of the bottom surface of the pontoon body 41, the water ski 43 is tilted, and the front end of the water ski 43 is higher than the rear end, and an acute angle with an opening toward the tail side is formed between the water ski 43 and the bottom surface of the pontoon body 41; the first driving mechanism 44 and the second driving mechanism 45 are both hydraulic cylinders, electric cylinders or pneumatic cylinders; the spoiler 42 and the water ski 43 are connected to the piston rod of the hydraulic cylinder; a slip ring 46 is installed at the end of the main beam 33 of each main wing 3; the water ski 43 is installed on the main beam 33 through the slip ring 46, and the water ski 43 rotates around the slip ring 46, thereby increasing the tension that the water ski 43 can withstand and increasing the structural strength of the water ski 43. In order to realize the flight control system to control the extension and retraction of the hydraulic cylinder, a hydraulic system that provides hydraulic oil to the hydraulic cylinder can be arranged in the buoy 4 or the main wing 3. The hydraulic system includes a hydraulic pump, a hydraulic pipeline, and a hydraulic valve installed in the hydraulic pipeline to control the flow of the pipeline. The flight control system controls the first drive mechanism 44 and the second drive mechanism 45 by controlling the hydraulic pump and the hydraulic valve. The water ski 43 can adopt an integral structure or a two-stage structure; when the water ski 43 adopts a two-stage structure, such as Figure 5 As shown, the water ski 43 can be composed of a first section and a second section that are movably connected; the first section is located in the buoy body 41, one end of which can be directly fixedly installed on the buoy body 41 or the slip ring 46, and the other end is rotatably connected to one end of the second section, so that the second section can rotate around the connection point between it and the first section; the middle part of the second section is hinged to the other end of the second drive mechanism 45, and the second section is driven to rotate around the connection point between the first section and the second section by the second drive mechanism 45; when the second drive mechanism 45 adopts a hydraulic cylinder, the middle part of the second section is hinged to the piston rod end of the hydraulic cylinder. When the water ski 43 adopts a two-section structure, it is convenient for the ground effect vehicle to accommodate the water ski 43 in the buoy body 41 during flight.
[0044] The flight control system includes an airspeed meter and an altimeter, and uses the airspeed meter and altimeter to determine the flight status of the aircraft. The airspeed meter is used to measure the flight speed of the aircraft; the altimeter is used to measure the flight altitude of the aircraft.
[0045] When the ground-effect aircraft needs to turn toward one side, the first driving mechanism 44 on the side is controlled by the flight control system to drive the spoiler 42 to swing upward, so that the spoiler 42 extends out of the top surface of the buoy 4, and the second driving mechanism 45 on the side is controlled by the flight control system to drive the water ski 43 to swing downward, so that the water ski 43 extends out of the bottom surface of the buoy 4, and the spoiler 42 and the water ski 43 on the other side are kept motionless, thereby obtaining a yaw moment to achieve a small radius turn. When the ground-effect aircraft flies normally without turning, the spoiler 42 and the water ski 43 are both in the initial state and are accommodated in the buoy 4.
[0046] The above-mentioned ground effect vehicle is additionally provided with a spoiler 42 and a water ski 43 on the buoy 4, and the first driving mechanism 44 drives the spoiler 42 to swing upward to generate an upward torque, so that the main wing 3 on this side moves downward, and the second driving mechanism 45 drives the water ski 43 to swing downward so that the water ski 43 contacts the water surface or is pressed into the water, thereby increasing the resistance on one side of the aircraft, so that the aircraft obtains a larger yaw moment, reduces the turning radius, and realizes a small radius turn.
[0047] When above-mentioned ground effect vehicle takes off, the pilot pushes the throttle push rod to the large throttle position, after the flight control system receives the signal of airspeed meter and altimeter, automatically judges that the aircraft is in the low-altitude and low-speed state, the whole power output of engine 21 can be given to propeller 22, larger thrust is provided, and high-pressure air cushion is formed under the wing quickly, produces obvious ground effect, and takes off quickly. After the take-off action is completed, the flight control system receives the signal of airspeed meter and altimeter, judges that the aircraft is in the higher-altitude and high-speed state, and the output thrust of automatic control engine 21 avoids the ground effect vehicle from flying out of the ground effect area under the premise of not changing propeller 22 angles, and reaches the purpose of finely controlling the aircraft with simple structure.
[0048] The working principle of ground effect vehicle is introduced in detail below with left turn as example: when ground effect vehicle needs to turn left, the first driving mechanism 44 and the second driving mechanism 45 inside the left side buoy 4, namely the first hydraulic cylinder and the second hydraulic cylinder stretch, the piston rods of the first hydraulic cylinder and the second hydraulic cylinder are all extended, spoiler 42 and water ski 43 are stretched out simultaneously, and spoiler 42 stretches out the top of the left side buoy 4, and water ski 43 stretches out the bottom of the left side buoy 4; At this moment, the right side buoy 4 then does not have any action, that is, the spoiler 42 and the water ski 43 of the right side buoy 4 are all arranged in the buoy 4. Because spoiler 42 stretches out upwards and can produce upward moment, the wing on the left side can move downward, at this moment, water ski 43 can contact the water surface, and buoy 4 is subject to the resistance from water, produces the moment opposite to 4 directions of motion of the left side buoy. In addition, because spoiler 42 stretches out buoy 4 outsides over a large area, is subject to larger air resistance, so also can directly produce moment backward. Under the effect of air and water, when two active forces produced respectively by the spoiler 42 and the water ski 43 on the left side are superimposed on each other, the difference that the left and right wings are subjected to the resistance backward increases.The combined force to the left of the aircraft is large, and the rudder 52 on the vertical tail 5 and the aileron 32 on the main wing 3 are then linked to control yaw and roll under the effect of the flight control system, so that the ground effect vehicle is carried out a small radius turn according to the driver's stick amplitude under the precondition of not losing control.On the contrary, the ground effect vehicle is then stretched by the first drive mechanism 44 and the second drive mechanism 45 on the right side controlled by the flight control system when turning to the right, thereby the spoiler 42 and the water ski 43 are stretched out of the buoy 4.
[0049] Obviously, those skilled in the art can make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.
Claims
1. A ground effect vehicle capable of reducing a turning radius, characterized in that: Including fuselage, power system, main wing, float and flight control system; The power system is symmetrically installed on both sides of the front part of the fuselage, and the main wings are symmetrically installed on both sides of the middle part; the power system includes an engine and a propeller; the engine has a pitch angle; The main wing includes an airfoil, an aileron and a main beam; the aileron is rotatably connected to the rear side of the airfoil; the end of the main beam is fixedly connected to the buoy; The buoy includes a buoy body, a spoiler, a water ski, a first driving mechanism and a second driving mechanism; one end of the spoiler, the water ski, the first driving mechanism and the second driving mechanism are all rotatably installed in the buoy body; the other end of the first driving mechanism is hinged to the middle of the spoiler, and is used to drive the spoiler to swing in a vertical plane to extend out of the upper side of the buoy body; the other end of the second driving mechanism is hinged to the middle of the water ski, and is used to drive the water ski to swing in a vertical plane to extend out of the lower side of the buoy body; When the ground effect vehicle needs to turn toward one side, the flight control system controls the first driving mechanism on the side to drive the spoiler to swing upward, and controls the second driving mechanism on the side to drive the water ski to swing downward, while keeping the spoiler and the water ski on the other side stationary, thereby obtaining a yaw moment to achieve a small radius turn.
2. The ground effect vehicle according to claim 1, characterized in that: Also included are slip rings corresponding one-to-one to the water skis; The water ski is mounted on the main beam through the slip ring.
3. The ground effect vehicle according to claim 1, characterized in that: The first driving mechanism and the second driving mechanism are both hydraulic cylinders; The spoiler and the water ski are connected to the piston rod of the hydraulic cylinder.
4. The ground effect vehicle according to claim 1, characterized in that: The two engines rotate in opposite directions; The two propellers are both forward and reverse propellers, which are used to balance the torque caused by the rotation of the propellers to reduce the rudder trim.
5. The ground effect vehicle according to claim 1, characterized in that: It also includes the vertical tail and horizontal tail; The vertical tail is fixedly mounted on the tail of the fuselage; The two horizontal tails are distributed in a V shape and are symmetrically installed on both sides of the vertical tail; the horizontal tail includes a horizontal stabilizer and an elevator; the elevator is rotatably connected to the rear side of the horizontal stabilizer and is linked and controlled by the flight control system to achieve pitch action.
6. The ground effect vehicle according to claim 5, characterized in that: The vertical tail comprises a vertical stabilizer and a rudder rotatably mounted on the rear side of the vertical stabilizer; The rudder is controlled by the flight control system to achieve yaw action.
7. The ground effect vehicle according to claim 5, characterized in that: The horizontal tail has an upward dihedral angle, so that the ground effect vehicle generates a centering moment when rolling.
8. The ground effect vehicle according to claim 1, characterized in that: The power system also includes an engine nacelle fixedly mounted on both sides of the fuselage; The engine is fixedly installed in the engine compartment; The propeller is rigidly connected to the engine via a transmission shaft, so that the propeller has a pitch angle.
9. The ground effect vehicle according to claim 1, characterized in that: The main wing also includes a plurality of ribs fixedly connected to the main beam; the ribs are used to increase the structural strength of the main wing.
10. The ground effect vehicle according to claim 1, characterized in that: The flight control system includes an airspeed meter and an altimeter, and determines the flight status according to the airspeed meter and the altimeter.