Cross-medium variant aircraft
By designing a morphing wing and ducted propulsion system, the problems of high drag and low speed in water for cross-medium aircraft were solved, enabling efficient propulsion and stable flight in different media.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-15
- Publication Date
- 2026-03-10
AI Technical Summary
Existing cross-medium aircraft mostly adopt multi-rotor or tiltrotor configurations, which have high drag, low speed and high failure rate in water, making them unsuitable for long-term operation.
Employing a variator wing and ducted propulsion system, the wing can rotate in the horizontal plane to change its angle, the ducted propulsion system is used for underwater propulsion, and the rotor is used for aerial flight. Combined with a control plate, the entry angle and heading can be adjusted to reduce drag and improve efficiency.
By designing vari-wing and ducted propulsion systems, water resistance is reduced, propulsion efficiency is improved, and the adaptability and practicality of the aircraft in different media are enhanced.
Smart Images
Figure CN223982662U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of variator technology, specifically a cross-medium variator. Background Technology
[0002] Transmedium-based aircraft are a new type of future aircraft that can be widely used in various applications requiring cross-medium flight. They possess the capability to navigate in different media and have a very broad application prospect. Taking navigation in water and air as an example, such aircraft can autonomously exit and re-enter water to achieve water-to-air and air-to-water transitions, expanding the aircraft's working range and optimizing its performance.
[0003] However, most existing cross-medium aircraft adopt multi-rotor or tilt-rotor configurations, which have high drag in water, very low speed limits, and high failure rates of tilt-rotor aircraft, making them unsuitable for long-term operation. Utility Model Content
[0004] The technical problem to be solved by this utility model is to provide a cross-medium variant aircraft in response to the above-mentioned shortcomings.
[0005] To solve the above technical problems, the present invention adopts the following technical solution:
[0006] A trans-medium morphing aircraft includes a fuselage, morphing wings, control plates, a ducted propulsion system, and a rotor. The morphing wings are symmetrically arranged horizontally on both sides of the middle of the fuselage, and the morphing wings can rotate around the fuselage in the horizontal plane to change the angle with the fuselage. Control plates are symmetrically arranged on both sides of the front of the fuselage, and the control plates can rotate back and forth in the vertical plane to change the angle with the airflow in front. A ducted propulsion system is arranged at the bottom of the fuselage, and the ducted propulsion system is used to propel the aircraft forward in water. A rotor is arranged at the tail of the fuselage, and the rotor is used to propel the aircraft in air.
[0007] Furthermore, the fuselage has connecting slots on both the left and right sides for connecting and accommodating the variator wings. When the variator wings rotate to their maximum extent inside the connecting slots, the angle between them and the fuselage is 30 degrees or 90 degrees.
[0008] Furthermore, the ducted propulsion device includes a duct and a propeller. The duct is located at the bottom of the fuselage, and the propeller is located inside the duct. The upper part of the duct is embedded inside the fuselage to form a semi-hidden duct.
[0009] Furthermore, the bottom of the fuselage is provided with brackets located on the left and right sides of the duct propulsion device, respectively.
[0010] Compared with the prior art, the present invention, by adopting the above technical solution, has the following advantages:
[0011] This utility model relates to a ducted propulsion device that employs a duct and a propeller. The upper part of the duct is embedded in the fuselage to form a semi-concealed duct, propelling the aircraft forward in water. Compared to a complete duct, this reduces the fuselage cross-sectional area and improves propulsion efficiency. A connecting slot in the fuselage accommodates a vari-rotating wing, which can rotate around the fuselage in the horizontal plane, changing its angle with the fuselage to reduce drag in water and adapt to different flight environments. A support frame at the bottom of the fuselage can be used to secure and carry items, increasing the aircraft's practicality and functional versatility.
[0012] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. Attached Figure Description
[0013] Figure 1 This is a three-dimensional structural diagram of the present invention;
[0014] Figure 2 Rear view with wings deployed;
[0015] Figure 3 A top view of the aircraft with its wings folded.
[0016] Figure 4 This is a rear view of the aircraft with its wings folded.
[0017] The attached diagram lists the components represented by each number as follows:
[0018] 1. Fuselage; 2. Variant wing; 3. Adjustment plate; 4. Ducted propulsion system; 401. Duct; 402. Propeller; 5. Rotor; 6. Support; 7. Connecting slot. Detailed Implementation
[0019] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.
[0020] In the description of this utility model, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", "clockwise", "counterclockwise", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0021] like Figure 1-4As shown, a trans-medium morphing aircraft includes a fuselage 1, morphing wings 2, control plates 3, a ducted propulsion device 4, and a rotor 5. The morphing wings 2 are symmetrically arranged horizontally on the left and right sides of the middle of the fuselage 1. The morphing wings 2 can rotate around the fuselage 1 in the horizontal plane to change the angle with the fuselage 1. The control plates 3 are symmetrically arranged on the left and right sides of the front end of the fuselage 1. The control plates 3 can rotate back and forth in the vertical plane to change the angle with the airflow in front. The ducted propulsion device 4 is arranged at the bottom of the fuselage 1. The ducted propulsion device 4 is used to propel the aircraft forward in water. The rotor 5 is arranged at the tail of the fuselage 1. The rotor 5 is used to propel the aircraft in air.
[0022] In one embodiment, the fuselage 1 has connecting slots 7 on both the left and right sides for connecting and accommodating the variator wings 2. When the variator wings 2 rotate to their maximum extent inside the connecting slots 7, the angle between them and the fuselage 1 is 30 degrees or 90 degrees.
[0023] In one embodiment, the ducted propulsion device 4 includes a duct 401 and a propeller 402. The duct 401 is provided at the bottom of the fuselage 1, and the propeller 402 is provided inside the duct 401. The upper part of the duct 401 is embedded inside the fuselage 1 to form a semi-hidden duct.
[0024] In one embodiment, the bottom of the fuselage 1 is provided with brackets 6 located on the left and right sides of the ducted propulsion device 4 respectively.
[0025] In this invention, both the variant wings and the adjustment plates are driven by motors inside the fuselage. The two adjustment plates 3 rotate independently. The synchronous rotation of the two adjustment plates 3 can adjust the ascent and descent of the aircraft. The reverse rotation of the two adjustment plates 3 or the rotation of a single adjustment plate 3 can adjust the flight direction of the aircraft. The two variant wings 2 can be deployed or retracted synchronously.
[0026] The working process of this utility model is as follows: The tail rotor 5 of the fuselage 1 is activated, generating lift to take the aircraft into the air. The variator wings 2 on both sides of the fuselage 1 remain in a conventional fixed position, providing stability during flight. As the aircraft approaches the water surface, the variator wings 2 begin to rotate horizontally backward, gradually reducing the angle between the wings and the water flow direction, thus reducing the impact drag upon entering the water. The adjustment plates 3 on both sides of the fuselage 1 rotate vertically synchronously to adjust the entry angle. After entering the water, the rotor 5 stops rotating, and the propeller 402 in the duct 401 at the bottom of the fuselage 1 rotates, propelling the aircraft forward. The heading and depth of the aircraft in the water can be adjusted in real time by rotating the adjustment plates 3 individually. The angle between the variator wings 2 and the fuselage is dynamically adjusted according to the water flow resistance, ranging from a minimum of 30 degrees to a maximum of 90 degrees, forming a V-shape to optimize water flow and reduce drag. When the aircraft approaches the water surface, the variant wing 2 rotates and unfolds to the angle suitable for flight. The two adjustment plates 3 rotate synchronously to adjust the angle with the water surface. The tail rotor 5 starts and propels the aircraft together with the ducted propulsion device 4. After the aircraft leaves the water, the ducted propulsion device 4 stops, and the adjustment plates 3 are rotated to make the aircraft fly smoothly. Items can be tied to the frame.
[0027] The above description provides examples of the preferred embodiments of this utility model. Any aspects not detailed herein are common knowledge to those skilled in the art. The scope of protection of this utility model is determined by the claims. Any equivalent modifications based on the technical teachings of this utility model are also within the scope of protection of this utility model.
Claims
1. A transmedia variant aircraft, characterized by, The utility model relates to a kind of amphibious aircraft, including fuselage (1), variable wing (2), adjusting plate (3), ducted propulsion device (4) and rotor (5), the fuselage (1) middle left and right sides are horizontally symmetrical and provided with variable wing (2), the variable wing (2) can rotate in horizontal plane around fuselage (1), change the angle with fuselage (1), the fuselage (1) front left and right sides are symmetrically provided adjusting plate (3), the adjusting plate (3) can rotate in vertical plane and change the angle with front airflow, the fuselage (1) bottom is provided with ducted propulsion device (4), and the ducted propulsion device (4) is used to drive aircraft to advance in water, the fuselage (1) tail is provided with rotor (5), and the rotor (5) is used to drive aircraft to fly in air.
2. The transmedia variant aircraft of claim 1, wherein, The fuselage (1) left and right sides are each provided with connecting groove (7) for connecting variable wing (2) and accommodating rotating variable wing (2), and the angle between the variable wing (2) and the fuselage (1) is 30 degrees or 90 degrees when the variable wing (2) rotates to the maximum amplitude inside the connecting groove (7).
3. The transmedia variant aircraft of claim 1, wherein, The ducted propulsion device (4) includes duct (401) and propeller (402), the fuselage (1) bottom is provided with duct (401), the duct (401) is provided with propeller (402) inside, and the upper half of the duct (401) is embedded inside the fuselage (1) to form a semi-concealed duct.
4. The transmedia variant aircraft of claim 1, wherein, The fuselage (1) bottom is provided with bracket (6) respectively located on the left and right sides of ducted propulsion device (4).