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CN-122009484-A - Pneumatic cooperative type water ground effect aircraft

CN122009484ACN 122009484 ACN122009484 ACN 122009484ACN-122009484-A

Abstract

The invention relates to the technical field of aircrafts and provides a pneumatic synergistic type water ground effect aircrafts, which comprises a fuselage, a nose, wings, a double-hull, a sliding plate, a vertical take-off paddle, a bated cavity, a nose duct, a thrust duct, a rear thrust paddle and a thrust paddle, wherein the fuselage adopts a flat streamline structure and is integrally formed with the wings, the lower part of the fuselage is provided with the cavity to cover 70% of the lower surface area of the fuselage, and the nose duct is utilized to actively inject high-speed air flow into the inverted U-shaped large-area cavity to form a controllable high-pressure air cushion, so that the water surface sliding resistance is greatly reduced, the initial lifting capacity is improved, the aircrafts can finish short-distance take-off and landing in a narrow water area or a complex sea condition, and meanwhile, the dynamic inhibition of wave impact, turbulence and an asymmetric air field is realized through the vertical jet flow at the end part of the wings and the adjustable diversion of the thrust duct of the fuselage, thereby remarkably enhancing the stability and the wind resistance, and improving the running safety in a 3-5-level wind environment.

Inventors

  • LI MING
  • HE YANHENG
  • DU PENGFEI

Assignees

  • 深圳考普特科技有限公司

Dates

Publication Date
20260512
Application Date
20260312

Claims (10)

  1. 1. A pneumatic cooperative type water ground effect aircraft is characterized by comprising a fuselage (101), a nose (102), wings (103), a double-hull (108), a sliding plate (109), a vertical take-off paddle (105), a bated ray-shaped cavity (107), a nose duct (106), a telescopic hydrofoil (112), a thrust duct (110), a rear thrust paddle (111), a thrust paddle (115) and a connecting frame (113), Wherein, the machine body (101) adopts a flat streamline structure and is integrally formed with the wing (103); The lower part of the machine body (101) is provided with a cavity (107) which covers 70% of the area of the lower surface of the machine body (101); 6 nose ducts (106) are arranged at the lower part of the nose (102), and the axis of the nose ducts is inclined downwards by 20 degrees; The nose duct (106) is used for injecting high-speed airflow of 120m/s into the cavity (107) to form an active air cushion; The upper surface of the machine body (101) is provided with two rows of thrust ducts (110) for jetting 200m/s of horizontal air flow to provide main thrust.
  2. 2. The hydraulically operated, collaborative, water ground effect aircraft of claim 1, wherein the active air cushion generated by the nose duct (106) cooperates to shorten the takeoff taxi distance.
  3. 3. A pneumatic synergistic type water ground effect aircraft according to claim 2, characterized in that the high-speed air flow sprayed by said nose duct (106) is guided into the ray-like cavity (107) through the lower part of the nose (102), and a high-pressure area is formed between the lower cavity of the cavity (107) and the water surface.
  4. 4. A pneumatic synergistic type water ground effect aircraft according to claim 3 is characterized in that the thrust duct (110) is provided with an adjustable deflector for adjusting the injection direction and injection quantity of the left and right ducts, and heading control and steering maneuver are realized through differential jet flow.
  5. 5. A pneumatic synergistic water-craft as claimed in claim 4, wherein the hulls (108) are symmetrically arranged in the lower part of the fuselage (101).
  6. 6. A pneumatic synergistic water ground effect aircraft as claimed in claim 5, characterized in that a skid plate (109) is arranged at the bottom of the hull (108).
  7. 7. A pneumatic synergistic water ground effect aircraft as claimed in claim 6, characterized in that said slide plate (109) is used for water surface sliding bearing, attitude buffering and water departure transition and reduces water surface contact resistance in combination with high speed air cushion of cavity (107).
  8. 8. A pneumatic synergistic type water-craft as claimed in claim 7, wherein the thrust duct (110) is used as a main propulsion source, and the rear thrust runner (111) and the thrust runner (115) are used as auxiliary propulsion means, which can be operated independently or cooperatively for providing differential thrust and redundant power support at different flight stages.
  9. 9. The pneumatic cooperative type water ground effect aircraft of claim 8, wherein the equipped flight control system adjusts the working states of a nose duct (106), a thrust duct (110), a wing end vertical jet and a vertical take-off paddle (105) in real time according to data of an attitude sensor, an air pressure sensor and a sea condition monitoring module, so as to realize active wave resistance, attitude stability and energy optimization distribution.
  10. 10. The pneumatic collaborative type water ground effect aircraft according to claim 9, wherein the active jet flow ground effect composite structure formed by the nose duct (106), the cavity (107) and the thrust duct (110) of the aircraft body (101) enables the thrust requirement of the aircraft to be lower than 60% of that of a conventional fixed wing aircraft under the same load and speed conditions, and the unit energy consumption to be remarkably reduced.

Description

Pneumatic cooperative type water ground effect aircraft Technical Field The invention relates to the technical field of aircrafts, in particular to a pneumatic cooperative type water ground effect aircraft. Background The ground effect on water aircraft is used as a novel traffic tool between a fixed-wing aircraft and a water surface ship, and can obtain remarkable lift gain during low-altitude high-speed flight by utilizing the ground effect under the wing, so that the high-efficiency and low-energy-consumption water surface sliding and low-altitude flight are realized. The prior Chinese patent number is CN119117269A, which discloses a tilting rotor aircraft. The tilting rotor aircraft comprises a fuselage, a vertical take-off paddle, a main wing, a first tilting wing group, a second tilting wing group and a third tilting wing group, wherein the vertical take-off paddle is arranged on a nose of the fuselage, the main wing is arranged on a tail of the fuselage, the first tilting wing group is arranged on the vertical take-off paddle, the second tilting wing group and the third tilting wing are arranged on the main wing, the second tilting wing group is arranged on an axis of a mass center of the aircraft, and projections of at least four tilting wings in the first tilting wing group, the second tilting wing group and the third tilting wing group on a horizontal plane form a parallelogram taking the mass center of the aircraft as a center. According to the aircraft, the vertical take-off paddles are matched with the four balance tilting wings, so that the flight performance and the flight safety of the aircraft can be improved. Reference 2 (CN 107458572 a) discloses a floating bionic ornithopter, which comprises a fuselage, a ornithopter mechanism, a tail mechanism and a posture adjusting device. The machine body is designed by simulating the appearance of a bated ray, the material of the machine body is a composite film material, and helium is filled in the machine body. The flapping wing mechanisms are symmetrically distributed on two sides of the machine body and consist of flapping wing actuators, flapping wing swing arms, a flapping wing fixing frame and flapping wings, wherein output shafts of the flapping wing actuators are connected with the support rods through the flapping wing swing arms. The tail mechanism is positioned at the tail of the fuselage and consists of a tail actuator, a tail rocker arm, a tail fixing frame and a tail, wherein an output shaft of the tail actuator is connected with the tail through the tail rocker arm. The attitude adjusting device is arranged on the machine body and consists of an attitude actuator, an attitude rocker arm, a connecting rod, an attitude fixing frame and a weight, wherein the attitude actuator moves with the animal block through the attitude rocker arm and the connecting rod. Compared with other flapping wing aircrafts, the invention has the advantages of high safety, simple structure, high flying efficiency and good maneuvering performance. The prior art has the characteristics of limited take-off and landing, low pneumatic efficiency and insufficient coordination in the field of water ground effect flight, and has the advantages of dependence on long-distance running, severe requirements on sea conditions and water area space, difficulty in adapting to complex environments, split design of lift force and power system, lack of dynamic adjustment capability in air flow control, unbalanced optimization of ground effect utilization and energy consumption, low integration of pneumatic structure and propulsion and floating body systems, insufficient stability caused by easy disturbance, and obvious intelligentization and environmental tolerance short plates. Disclosure of Invention The invention aims to solve the problems that the prior art has the characteristics of limited take-off and landing, low pneumatic efficiency and poor coordination in the field of water ground effect flight, the take-off and landing depend on long-distance running, the requirements on sea conditions and water areas are severe, complex environments are difficult to adapt, a lift force and power system is designed to be split, the air flow control lacks dynamic adjustment capability, the ground effect utilization and energy consumption are optimized and unbalanced, the integration level of a pneumatic structure and a propulsion and floating body system is low, the stability is insufficient due to easy disturbance, and an intelligent and environment-tolerance short plate is obvious. In order to achieve the aim, the invention adopts the following technical scheme that the pneumatic cooperative type water ground effect aircraft comprises a fuselage, a nose, wings, a double-hull, a skateboard, a vertical take-off paddle, a telescopic hydrofoil, a ray-shaped cavity, a nose duct, a thrust duct, a rear thrust paddle and a thrust paddle, Wherein, the fuselage adopts a flat streamline struct