High-stability cracking type control surface ground effect aircraft and control method thereof

Abstract

The invention relates to the technical field of aircrafts, and discloses a high-stability cracking type control surface ground effect aircraft and a control method thereof. Multi-dimensional active adjustment of the flight attitude is realized through independent and accurate control of the cracking type turbulent flow devices on the upper surfaces of the wings: the front / rear cracking type turbulent flow devices cooperatively act to intelligently manage the pitch attitude and the water leaving height, and the stability of the lift center is effectively maintained; the cracking type turbulent flow devices on the same side synchronously start and drive rolling and yawing integrated maneuvering, and the risk that wingtips make contact with water is avoided in combination with complete protection of a lower surface integrated structure on a ground effect area; the full-cracking type turbulent flow device is started to provide adjustable downward pressure, and the landing performance is optimized; and the structural durability, the flight stability and the safety controllability of the ground effect aircraft in a complex water surface environment are remarkably improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, in particular to a high-stability cracking control surface ground effect vehicle and a control method thereof. Background Art

[0002] Current aircraft generally design the trailing edge of the stabilizer as an integral moving control surface (such as an elevator or rudder). This structure performs well in conventional flight, but has serious adaptation flaws when applied to ground-effect vehicles. Ground-effect vehicles frequently glide and take off and land on the water, exposing the moving control surfaces to the impact of high-speed water flow, which makes the control surface structure and its drive mechanism extremely vulnerable to damage. In addition, when encountering air disturbances or excessive speed, existing ground-effect vehicles will trigger uncontrollable nose-up climbs, which in turn triggers a vicious cycle of forward movement of the lift focus.

[0003] Deficiencies in existing technologies:

[0004] Structural reliability defects: The impact of water flow during the water planing phase causes continuous physical damage to the rudder mechanism, significantly shortening the life of key components;

[0005] Aerodynamic stability defects: Sudden nose-up climbs cause the center of lift to shift forward, forming a chain reaction of "climb-forward focus-stall", ultimately leading to a crash;

[0006] Risk of ground effect damage: When traditional rudders deflect upward, they directly tear through the ground effect low-pressure area formed by the wing and wingtip panels, causing the wingtip to touch the water or even overturn the aircraft;

[0007] Therefore, a high-stability cracked-control surface ground effect vehicle and its control method are proposed. Summary of the Invention

[0008] In view of the deficiencies of the prior art, the present invention provides a high-stability split-control surface ground effect vehicle and a control method thereof to solve the background technical problems.

[0009] To achieve the above object, the present invention provides the following technical solutions:

[0010] In a first aspect, a high-stability cracking control surface ground effect vehicle is provided, the vehicle comprising:

[0011] The fuselage, four wings located on the front and rear sides of the fuselage;

[0012] At least four sets of independently controlled split-type spoiler devices are symmetrically mounted on the tail of the upper surface of the wing, and the split-type spoiler devices include a drive mechanism and spoilers controlled to rotate by the drive mechanism;

[0013] The splitting spoiler device is configured as follows:

[0014] Open the spoiler upwards to disrupt the airflow on the wing surface and reduce the lift in the corresponding area;

[0015] The aircraft's pitch control, roll control and altitude adjustment are achieved through independent control of the open state.

[0016] Preferably, the driving mechanism in the split-type spoiler device includes a servo installed in the wing, a connecting rod connected to the output end of the servo, and a connecting block installed on the spoiler and rotatably connected to one end of the connecting rod. The servo controls the rotation of the spoiler through the connecting rod and the connecting block.

[0017] Preferably, there are four split-type spoilers, which are independently installed on the upper surfaces of the left front wing, the right front wing, the left rear wing and the right rear wing.

[0018] Preferably, the lower surface of the wing is an integrated structure to improve strength.

[0019] Preferably, a plurality of hinges are installed between the spoiler and the wing to improve the connection strength of the spoiler.

[0020] In a second aspect, a high-stability cracking type control surface ground effect vehicle control method is provided, based on the high-stability cracking type control surface ground effect vehicle described in the first aspect, and the vehicle control method comprises:

[0021] Pitch control:

[0022] The split spoilers on the front left and right wings are activated to reduce the front lift and make the aircraft descend.

[0023] The split spoilers on the left and right rear wings are opened to reduce the rear lift and allow the aircraft to climb upwards.

[0024] Roll and yaw control:

[0025] Right turn control: Synchronously activate the split spoilers on the right front and rear wings to reduce lift and increase drag on the right side, driving the aircraft to roll and yaw to the right;

[0026] Left turn control: Synchronously activate the split spoilers on the left front and rear wings, reducing lift on the left side and increasing drag, driving the aircraft to roll and yaw to the left;

[0027] Anti-disturbance stability control:

[0028] The split spoiler on the front wing is opened synchronously to suppress the forward movement of the lift center;

[0029] Landing Control:

[0030] All split-type spoilers are opened simultaneously to generate maximum downforce and shorten the sliding distance.

[0031] Preferably, in the pitch control, the height of the aircraft above the water is controlled by adjusting the opening amplitude of the front / rear wing spoilers.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] The present invention realizes multi-dimensional active adjustment of flight attitude through independent and precise control of the split-type spoiler device on the upper surface of the wing: the front / rear split-type spoiler devices work together to intelligently manage the pitch attitude and water height, effectively maintaining the stability of the lift center; the split-type spoiler devices on the same side are synchronously opened to drive the integrated roll and yaw maneuver, combined with the complete protection of the ground effect area by the integrated structure of the lower surface, avoiding the risk of wingtip touching the water; the full split-type spoiler device is opened to provide adjustable downforce, optimizing landing performance; significantly improving the structural durability, flight stability and safe controllability of the ground effect vehicle in the complex environment of the water surface.

[0034] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 Schematic diagram of the overall structure of the aircraft of the present invention;

[0036] Figure 2 This is a schematic diagram of the overall top view of the aircraft of the present invention;

[0037] Figure 3 for Figure 1 A partial enlarged view of point A in the middle;

[0038] Figure 4 Schematic diagram of the perspective structure of the splitting spoiler device of the present invention;

[0039] Figure 5 It is a structural schematic diagram of the wing and spoiler of the present invention.

[0040] In the figure: 1. Servo; 2. Wing; 3. Split spoiler; 31. Servo; 32. Connecting rod; 33. Connecting block; 34. Spoiler; 4. Hinge. DETAILED DESCRIPTION

[0041] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this technical field without making any creative efforts shall fall within the scope of protection of the present invention.

[0042] See also Figure 1-5 The present invention provides a high-stability cracking control surface ground effect vehicle and a control method thereof, comprising the following contents:

[0043] 1. Aircraft Structure Implementation

[0044] The body 1 adopts a streamlined design, with a cockpit at the front and a power system.

[0045] Four independent wings2:

[0046] The left front wing 2 and the right front wing 2 are installed on the front side of the fuselage 1; the left rear wing 2 and the right rear wing 2 are installed on the rear side of the fuselage;

[0047] The lower surface of each wing 2 is an integrally formed structure (without seams), and the thickness decreases from the wing root to the wing tip (to enhance the ability to resist water impact), so it is not easily damaged by water impact.

[0048] Splitting spoiler 3:

[0049] It includes a spoiler 34 installed at the tail end of the upper surface of each wing 2. The spoiler 34 is connected to the wing 2 through a plurality of stainless steel hinges 4. The spoiler 34 is controlled to rotate by a driving mechanism.

[0050] Driving mechanism:

[0051] The steering gear 31 is embedded in the wing 2;

[0052] The connecting block 33 is mounted on the spoiler 34

[0053] The connecting rod 32 is connected to the output shaft of the steering gear 31 and is rotatably connected to the connecting block 33;

[0054] The steering gear 31 drives the connecting rod 32 to push the connecting block 33, causing the spoiler 34 to rotate upward 0°-90° around the hinge 4;

[0055] The splitting spoiler 3 is configured as follows:

[0056] Open the spoiler 34 upward to disrupt the airflow on the upper surface of the wing 2 and reduce the lift in the corresponding area;

[0057] The aircraft's pitch control, roll control and altitude adjustment are achieved through independent control of the open state.

[0058] 2. Control Methods

[0059] 1. Pitch control and height adjustment

[0060] Implementation process:

[0061] When you need to lower the flight altitude:

[0062] The split-type spoiler devices 3 on the left and right front wings 2 of the aircraft are opened to separate the airflow on the upper surface of the front wing 2, reduce the front lift, and generate a nose-down moment for the aircraft to descend in altitude;

[0063] When you need to increase the flight altitude:

[0064] The split spoiler devices 3 on the left and right rear wings 2 are opened to reduce the rear lift, generating a nose-up moment for the aircraft to climb.

[0065] Highly precise adjustment:

[0066] By linearly adjusting the opening amplitude of the front / rear spoilers 34, the degree of lift reduction is changed, and the aircraft is controlled to cruise stably within the water height range (expanding the speed adaptation range).

[0067] 2. Roll and yaw control

[0068] Implementation process:

[0069] Right turn control:

[0070] Synchronously activate the splitting spoiler 3 on the right front and rear wings 2:

[0071] The lift on the upper surface of the right wing 2 decreases → the aircraft rolls to the right;

[0072] The right side resistance increases → produces a rightward yawing moment;

[0073] Ground effect zone protection: The integrated structure of the lower surface of Wing 2 maintains its complete contour, maintaining the ground effect zone intact and ensuring that the wingtip avoids contact with water;

[0074] Left turn control:

[0075] The left side splitting spoiler 3 is opened synchronously to achieve reverse rolling and yaw, while also keeping the lower surface structure intact.

[0076] 3. Anti-airflow disturbance stability control

[0077] Implementation process:

[0078] When airflow disturbances are detected causing the aircraft to tilt upwards:

[0079] Synchronously open the split spoiler 3 on the front wing 2:

[0080] The front lift decreases rapidly → suppresses the nose-up moment;

[0081] Block the vicious cycle of forward movement of the lift center → prevent stall and crash.

[0082] 4. Landing control

[0083] Implementation process:

[0084] Synchronously activate all cracking spoiler devices 3:

[0085] The lift on the upper surface of each wing 2 is greatly reduced → maximum downforce is generated;

[0086] The aircraft is quickly pressed towards the water surface → shortening the landing glide distance;

[0087] The integrated structure on the lower surface of wing 2 withstands the impact of water flow and avoids damage to the mechanism.

[0088] This embodiment provides independently controlled split-type spoilers 3 at the tail ends of the upper surfaces of the four wings 2 of the ground effect vehicle, and cooperates with the integrated structure of the lower surface of the wing 2 to achieve the following: during pitch control, the front / rear split-type spoilers 3 are opened to adjust the altitude; during turning, the split-type spoilers 3 on the same side are synchronously actuated to drive roll and yaw while the lower surface maintains the ground effect area intact to prevent water contact; during anti-disturbance, the front split-type spoilers 3 suppress nose-up stall; during landing, all the split-type spoilers 3 are opened to generate downforce to shorten the gliding distance, thereby solving the three major technical problems of water impact damage, sudden climb stall, and turning wingtip water contact.

Claims

1. A high stability cracking control surface ground effect vehicle, characterized in that the aircraft include: A body (1), four wings (2) located at the front and rear sides of the body (1); At least four groups of independently controlled split-type spoiler devices (3) are symmetrically mounted on the tail of the upper surface of the wing (2), and the split-type spoiler devices (3) include a driving mechanism and a spoiler (34) whose rotation is controlled by the driving mechanism; The splitting spoiler device (3) is configured as follows: Opening the spoiler (34) upwards to disrupt the airflow on the upper surface of the wing (2) and reduce the lift in the corresponding area; The aircraft's pitch control, roll control and altitude adjustment are achieved through independent control of the open state.

2. A high-stability cracking type control surface ground effect vehicle according to claim 1, characterized in that: The driving mechanism in the splitting spoiler device (3) comprises a steering gear (31) installed in the wing (2), a connecting rod (32) connected to the output end of the steering gear (31), and a connecting block (33) installed on a spoiler (34) and rotatably connected to one end of the connecting rod (32). The steering gear (31) controls the spoiler (34) to rotate through the connecting rod (32) and the connecting block (33).

3. A high-stability cracking type control surface ground effect vehicle according to claim 1, characterized in that: There are four split-type spoiler devices (3), which are independently installed on the upper surfaces of the left front wing (2), the right front wing (2), the left rear wing (2), and the right rear wing (2).

4. A high-stability cracking type control surface ground effect vehicle according to claim 1, characterized in that: The lower surface of the wing (2) is an integrated structure, which improves the strength.

5. A high-stability cracking type control surface ground effect vehicle according to claim 1, characterized in that: A plurality of hinges (4) are installed between the spoiler (34) and the wing (2) to improve the connection strength of the spoiler (34).

6. A high-stability cracking control surface ground effect vehicle control method, characterized in that: Based on the high-stability cracking control surface ground effect vehicle described in claims 1-5, the aircraft control method includes: Pitch control: The splitting spoiler devices (3) of the front left and right wings (2) are opened to reduce the front lift and make the aircraft descend with its head down; Opening the splitting spoiler devices (3) on the left and right rear wings (2) to reduce the rear lift and enable the aircraft to lift its head and climb; Roll and yaw control: Right turn control: Synchronously open the splitting spoiler (3) on the right front and rear wings (2), reduce the right lift and increase the drag, and drive the aircraft to roll and yaw to the right; Left turn control: Synchronously open the splitting spoiler (3) on the left front and rear wings (2), reduce the left lift and increase the drag, and drive the aircraft to roll and yaw to the left; Anti-disturbance stability control: Synchronously opening the splitting spoiler (3) of the front wing (2) to suppress the forward movement of the lift center; Landing Control: All the splitting spoiler devices (3) are opened synchronously to generate maximum downforce and shorten the sliding distance.

7. A high-stability cracking type control surface ground effect vehicle control method according to claim 6, characterized in that: In the pitch control, the height of the aircraft above the water is controlled by adjusting the opening amplitude of the spoilers (34) of the front / rear wings (2).

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