CN-121973926-A - Water-air amphibious medium-crossing aircraft

CN121973926ACN 121973926 ACN121973926 ACN 121973926ACN-121973926-A

Abstract

The application relates to a water-air amphibious medium-spanning aircraft, which belongs to the field of underwater and air multipurpose aircrafts and aims to solve the problems of poor rigid-flexible self-adaptive conversion performance, slow propulsion switching and weak multi-state control adaptation degree of the existing medium-spanning aircraft, the inner section wing is arranged on the aircraft body, two ends of the inner section wing are respectively provided with a variable wing unit, each variable wing unit comprises a swing arm section wing and a rigid-flexible conversion section wing, each swing arm section wing is arranged on the inner section wing and can realize folding and unfolding deformation in the plane of the inner section wing, and each rigid-flexible conversion section wing is arranged on each swing arm section wing and can realize rotation in the terminal plane of each swing arm section wing. The application is mainly used as a multipurpose craft capable of flexibly switching operation in two different medium environments of underwater and air.

Inventors

ZHANG JUNMING
LI YUAN
LIN SEN
SONG YUHANG
LIU YUBIN
ZHU YANHE
ZHAO JIE

Assignees

哈尔滨工业大学

Dates

Publication Date: 20260505
Application Date: 20260408

Claims (10)

1. The amphibious medium-crossing aircraft comprises a fuselage and a wing assembly, wherein the wing assembly is arranged on the fuselage, and is characterized in that the wing assembly comprises an inner section wing (4), the inner section wing (4) is arranged on the fuselage, two ends of the inner section wing (4) are respectively provided with a variable wing unit, the variable wing units comprise a swing arm section wing (5) and a rigid-flexible conversion section wing (6), the swing arm section wing (5) is arranged on the inner section wing (4) and can realize folding and unfolding deformation in the plane of the inner section wing (4), the rigid-flexible conversion section wing (6) is arranged on the swing arm section wing (5) and can realize rotation in the terminal plane of the swing arm section wing (5), the rigid-flexible conversion section wing (6) is in a rigid state and provides flying lifting force when the aircraft moves, and the rigid-flexible conversion section wing (6) is in a flexible state and drives the flexible driving force generated by the swing of the swing arm section wing (5) to provide forward direction when the aircraft moves in the water.
2. The amphibious medium-crossing aircraft as claimed in claim 1, wherein the aircraft body comprises an aircraft nose (1), a sealed cabin section (2) and an aircraft tail (3), the sealed cabin section (2) is fixedly arranged between the aircraft nose (1) and the aircraft tail (3), and the inner section wing (4) is arranged on the sealed cabin section (2).
3. The amphibious medium-crossing aircraft as set forth in claim 2, wherein the aircraft nose (1) comprises a folding paddle (7), a power motor (8), a motor mounting piece (9) and an aircraft nose shell (10), the power motor (8) is mounted at the front end of the aircraft nose shell (10) through the motor mounting piece (9), the folding paddle (7) is mounted on a power output shaft of the power motor (8) and synchronously rotates with the power output shaft of the power motor (8), and the rear end of the aircraft nose shell (10) is mounted at the front end of the sealed cabin section (2).
4. The amphibious medium-crossing aircraft of claim 2, wherein the sealed cabin section (2) comprises a sealed cabin front cover (11), a sealed cabin shell (12), an electronic device mounting rack (13) and a sealed cabin rear cover (14), the electronic device mounting rack (13) is fixed in the sealed cabin shell (12) and used for mounting electronic devices in a cabin, the sealed cabin front cover (11) and the sealed cabin rear cover (14) are respectively arranged at the front end and the rear end of the sealed cabin shell (12), the front end of the sealed cabin shell (12) is connected with the aircraft nose (1) through the sealed cabin front cover (11), and the rear end of the sealed cabin shell (12) is connected with the aircraft tail (3) through the sealed cabin rear cover (14).
5. The amphibious medium-crossing aircraft as set forth in claim 2, wherein the tail (3) comprises a fairing (15), a tail pipe (16), a tail steering engine (17) and a tail wing (18), the front end of the tail pipe (16) is connected with the rear end of the sealed cabin shell (12) through the fairing (15), the tail wing steering engine (17) is mounted at the rear end of the tail pipe (16), and the tail wing (18) is mounted on the power output end of the tail wing steering engine (17) and moves synchronously with the power output end of the tail wing steering engine (17).
6. An amphibious cross-medium aircraft according to claim 1, wherein the inner section wing (4) comprises a wing main body structure (19), a control panel sealing box (20), two wing drive power assemblies (24), four first aileron steering engines (23) and two aileron units, the wing main body structure (19) is mounted on the aircraft body through a plurality of fuselage hoops (25), the control panel sealing box (20) is mounted in the wing main body structure (19) and is used for carrying the control panel of the aircraft, the two aileron units are symmetrically arranged at the rear edge of the wing main body structure (19) along the axis of the aircraft body, each aileron unit comprises an upper aileron (21) and a lower aileron (22), the upper aileron (21) and the lower aileron (22) in each aileron unit are hinged with the upper surface and the lower surface of the rear edge of the wing main body structure (19) respectively, the four first aileron steering engines (23) are arranged in the wing main body structure (19), the upper aileron (21) and the lower aileron (22) in each aileron unit are respectively deflectable upwards or downwards relative to the wing main body structure (19) by one driving aileron (23), the two wing driving power assemblies (24) are respectively arranged at two ends of the wing main body structure (19) and are used for driving the swing arm section wing (5) to realize folding and unfolding deformation in the plane of the wing main body structure (19).
7. An amphibious across-the-air medium aircraft according to claim 1, wherein the swing arm section wing (5) comprises a swing arm section wing main body structure (37), a rigid-flexible conversion wing rotary driving mechanism (38), a rigid-flexible conversion wing spar rotary driving mechanism (39) and a rigid-flexible conversion wing mounting part (43), one end of the swing arm section wing main body structure (37) is connected with the inner Duan Jiyi (4) and can be folded and unfolded and deformed in the plane of the inner section wing (4) under the driving of the inner section wing (4), the rigid-flexible conversion wing mounting part (43) used for being connected with the rigid-flexible conversion section wing (6) is mounted on the other end of the swing arm section wing main body structure (37), and the rigid-flexible conversion wing rotary driving mechanism (38) and the rigid-flexible conversion wing spar rotary driving mechanism (39) are mounted in the swing arm section wing main body structure (37), and the rigid-flexible conversion wing rotary driving mechanism (38) is used for driving the rigid-flexible conversion wing mounting part (43) to rotate in the terminal plane of the swing arm section wing (5).
8. The amphibious across-the-air medium aircraft of claim 7, wherein the swing arm section wing (5) is further provided with a rigid-flexible conversion wing locking mechanism (40) for locking the working pose of the rigid-flexible conversion section wing (6).
9. The amphibious across-the-air medium aircraft of claim 8, wherein the rigid-flexible transition section wing (6) comprises an end mounting piece (60), a square tube wing spar (62), a round tube wing spar (63), two carbon fiber elastic plates (65), two torsion springs (59) and N wing ribs (61), N is a positive integer, the end mounting piece (60) is hinged with the rigid-flexible transition wing mounting piece (43) through the two torsion springs (59), the square tube wing spar (62) is arranged on one side of the end mounting piece (60) far away from the rigid-flexible transition wing mounting piece (43), one end of the square tube wing spar (62) is fixedly connected with the end mounting piece (60), two carbon fiber elastic plates (65) are oppositely arranged on two sides of the square tube wing spar (62), one end of each carbon fiber elastic plate (65) is inserted into the end mounting piece (60), N wing ribs (61) are sequentially sleeved on the square tube wing spar (62) and the two carbon fiber elastic plates (65) at equal intervals along the length extension direction of the square tube wing spar (62), one end of the square tube wing spar (62) is inserted into the square tube wing spar (62) and one end of the round tube wing spar (62) is fixedly connected with the end of the rigid-flexible wing spar (39), the rigid-flexible conversion wing spar rotary transmission mechanism (39) is used as a power source to drive the round pipe wing spar (63) to rotate in the square pipe wing spar (62) so as to realize the rigidity change of the whole rigid-flexible conversion section wing (6).
10. The amphibious medium-crossing aircraft as claimed in claim 1, wherein the outer surfaces of the inner section wing (4), the swing arm section wing (5) and the rigid-flexible transition section wing (6) are covered with skin structures.

Description

Water-air amphibious medium-crossing aircraft Technical Field The application belongs to the field of underwater and air multipurpose aircrafts, and particularly relates to a water-air amphibious cross-medium aircraft. Background The water-air amphibious medium-crossing aircraft is used as multipurpose equipment capable of flexibly switching operation in underwater and air two different medium environments, and has wide application prospect and important practical value in a plurality of fields such as marine exploration, environment monitoring, search and rescue and the like. With the continuous improvement of the requirements of the related fields on the maneuvering performance, the operation range and the environmental adaptability of the equipment, the technical problems of taking the air flight lift force requirement and the underwater propulsion efficiency into consideration in the cross-medium operation process of the aircraft are increasingly prominent; In the prior art, the wing design of a water-air amphibious aircraft is difficult to meet the operation requirements in two medium environments at the same time, and the following core problems mainly exist: The rigid wing design limitation is that most traditional amphibious aircrafts adopt a fixed rigid wing structure, the structure can provide stable flying lift force in the air through an aerodynamic principle, and the controllability of the flying attitude is ensured, but when the amphibious aircrafts run underwater, the rigid wing cannot adapt to the fluid characteristics of a water flow environment, so that not only can extremely large fluid resistance be generated, the underwater navigation energy consumption is obviously increased, but also effective propelling force is difficult to generate through structural deformation, the underwater maneuverability is poor, the navigation efficiency is low, and the requirement of complex underwater operation on flexible movement cannot be met; Part of the scheme attempts to adopt a flexible structure as a wing or a propulsion component, although the underwater resistance can be reduced to a certain extent, the propulsion force is generated through swinging, but due to insufficient structural rigidity, a stable lifting surface cannot be formed in the air, so that the lifting force is insufficient and the gesture stability is poor in flying, long-distance and high-precision air cruising is difficult to realize, the strength and durability of the flexible structure are difficult to meet the mechanical requirement of high-speed air flight, and the structural failure risk exists; The cross-medium conversion adaptability is poor, the prior art lacks of an integrated wing structure capable of realizing flexible conversion between air rigid lifting force and underwater flexible propulsion, and part of aircrafts are provided with two functions, and an independent flying lifting force device and an independent underwater propulsion device are required to be additionally arranged, so that the overall structure is complex, the dead weight is increased, the efficiency and the reliability of cross-medium operation are further reduced, the cooperative control difficulty of a plurality of devices is high, and the operation flexibility and the environmental adaptability of the aircrafts are influenced. Therefore, the development of the wing structure capable of adaptively switching the structural states in the water and air medium environments, not only has the air rigid lifting force characteristic, but also can realize underwater flexible high-efficiency propulsion, and the corresponding water-air amphibious medium-crossing aircraft are very in line with actual needs. Disclosure of Invention The application aims to solve the problem that the wing structure in the existing medium-crossing aircraft is relatively fixed, and the requirements of different medium mechanical properties can not be met by adaptively switching structural states in different medium environments, and further provides a water-air amphibious medium-crossing aircraft. A water-air amphibious medium-spanning aircraft comprises a fuselage and a wing assembly, wherein the wing assembly is arranged on the fuselage, the wing assembly comprises an inner section wing, the inner section wing is arranged on the fuselage, two ends of the inner section wing are respectively provided with a variable wing unit, the variable wing units comprise a swing arm section wing and a rigid-flexible conversion section wing, the swing arm section wing is arranged on the inner section wing and can realize folding and unfolding deformation in the plane of the inner section wing, the rigid-flexible conversion section wing is arranged on the swing arm section wing and can realize rotation in the terminal plane of the swing arm section wing, the rigid-flexible conversion section wing is in a rigid state and provides flying lifting force when the aircraft moves in an air environme