Aircraft with foldable lift system
By designing a foldable inclined rotor power system and front and rear wing structure, the shortcomings in urban aircraft in terms of speed, endurance and space requirements are solved, and aircraft with high stability, safety and operational efficiency are achieved.
Patent Information
- Application Number
- CN202420630245.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-03-29
- Publication Date
- 2025-03-28
- Estimated Expiration
- 2034-03-29
AI Technical Summary
Existing urban aircraft have shortcomings in speed and endurance. At the same time, the control logic is complex and the space requirements are large, making it difficult to deploy efficiently in a crowded urban environment.
A lift system foldable aircraft is designed, adopting a tilted rotor power system and front and rear wing structure, which can fold the fuselage and wing through folding components, reducing space requirements during storage, and adding a vertical tail to improve heading stability.
The aircraft is achieved with high stability and high safety, while reducing energy loss, increasing battery life, simplifying control logic, and improving deployment density and operational efficiency.
Smart Images
Figure CN222682674U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aviation, in particular to an aircraft with a foldable lift system. Background Art
[0002] Currently, there are various types of vertical take-off and landing urban aircraft, most of which include multi-rotor, composite wing, tilt-rotor, etc.
[0003] Composite wing and tilt-rotor aircraft fly in fixed-wing mode, so they have a faster speed, which can greatly reduce the time spent on the road, and also have better endurance. However, the control logic is more complicated, and there is still a high risk during flight conversion.
[0004] Pure multi-rotor structures are simple and relatively safe, and multi-rotors are at the forefront of airworthiness certification, making them undoubtedly the urban aircraft that can obtain airworthiness certification the fastest. However, they are slightly short on speed and endurance. Urban spaces are generally more crowded, and aircraft with wings will require a larger space in the wingspan direction. Utility Model Content
[0005] The technical problem solved by the utility model is to provide an aircraft with a foldable lifting system which is convenient to park and has high stability and high safety.
[0006] The technical solution adopted by the utility model to solve its technical problems is:
[0007] An aircraft with a foldable lift system, comprising:
[0008] A fuselage, wherein a cabin is arranged inside the fuselage, and openable fuselage doors are regularly arranged on the left and right sides of the fuselage;
[0009] Front wings, the front wings are symmetrically arranged at the upper front section of the fuselage to form left and right front wings, the front wings include inner front wings and outer front wings, and the roots of the inner front wings on the left and right sides are hinged and rotatably arranged with the fuselage through a folding assembly;
[0010] The rear wings are symmetrically arranged at the upper rear section of the fuselage to form left and right rear wings, the rear wings include an inner rear wing and an outer rear wing, and the roots of the inner rear wings on the left and right sides are also hinged and rotatably arranged with the fuselage through a folding assembly;
[0011] A power support frame, the power support frame is disposed between the inner front wing and the outer front wing, and the inner rear wing and the outer rear wing and is fixedly connected thereto to form a whole, and is symmetrically arranged on the left and right sides of the fuselage to form left and right power support frames;
[0012] A rotor power system, the rotor power system comprising a plurality of rotor power devices, the plurality of rotor power devices being regularly arranged and installed on the left and right power support frames with respect to the front wing and the rear wing, a front rotor power device being formed on the front side of the front wing, a middle rotor power device being formed between the front wing and the rear wing, and a rear rotor power device being formed on the rear side of the rear wing, the front, middle and rear rotor power devices being symmetrically arranged on the left and right power support frames on the left and right sides of the fuselage;
[0013] The rotor power system is rotated and folded upward on the power support frame through a folding assembly at the hinged joint of the inner front wing and the inner rear wing root;
[0014] A wheel system is regularly arranged and installed on the front and rear sections of the lower belly of the fuselage.
[0015] Furthermore, a vertical tail is arranged and installed on the upper side of the tail of the fuselage.
[0016] Preferably, the vertical tail is installed on the upper side of the tail of the fuselage in a bilaterally symmetrical arrangement.
[0017] Furthermore, the front wing and the rear wing are set to have an installation angle of 18°-22°.
[0018] Furthermore, the inner front wing is arranged upward to form a front wing dihedral angle, and the angle of the front wing dihedral angle is 8°-12°; the inner rear wing is also arranged upward to form a rear wing dihedral angle, and the angle of the rear wing dihedral angle is 26°-30°; the power support frame is fixed to the tips of the inner front wing and the inner rear wing, and connected to the roots of the outer front wing and the outer rear wing, the power support frames on the left and right sides of the fuselage are inclined upward through the upwardly arranged inner front wing and the inner rear wing, and the rotor power system on the left and right power support frames is also inclined upward through the inclined upwardly arranged left and right power support frames to form a tilted rotor power system; the propeller planes of all rotor power devices in the tilted rotor power system are inclined upward with respect to the horizontal plane of the fuselage when it is grounded, and the inclination angle is 12°-16°.
[0019] Furthermore, the propellers of all rotor power devices in the tilt-rotor power system avoid the fuselage through the tilted power support frame.
[0020] Furthermore, all rotor power devices in the rotor power system include two sets of upper and lower propeller systems.
[0021] Furthermore, the fuselage is optimized based on the appearance of a car body.
[0022] The beneficial effects of the utility model are:
[0023] 1. The utility model aircraft adopts a foldable tilt-rotor design, which can provide forward flight power and lift direction power. At the same time, front and rear wings are added to provide a certain lift during the flight of the aircraft. The lift direction power component of the tilt-rotor and the lift provided by the front and rear wings act simultaneously to suspend upward, which greatly reduces the energy loss compared to pure multi-rotors, thereby increasing the endurance.
[0024] 2. The aircraft of the utility model can increase the heading stability during flight by adding a vertical tail design to the tail of the fuselage.
[0025] 3. The structure of the aircraft of the utility model is relatively simple, and the control logic is similar to that of a multi-rotor aircraft, and it has the stability and safety of a multi-rotor aircraft. The aircraft of the utility model can fold the tilt-rotor power, thereby reducing the space requirement in the wingspan direction during storage, greatly improving the deployment density of the aircraft and improving operational efficiency. At the same time, the folded state can also reduce the space requirement for driving on the road. BRIEF DESCRIPTION OF THE DRAWINGS
[0026] Figure 1 It is a three-dimensional structural diagram of the utility model;
[0027] Figure 2 It is a side view of the utility model;
[0028] Figure 3 It is a front view of the utility model;
[0029] Figure 4 It is a top view of the utility model;
[0030] Figure 5 It is a three-dimensional diagram of the utility model in a folded state;
[0031] Figure 6 It is a side view of the utility model in a folded state;
[0032] Figure 7 It is a front view of the utility model in a folded state;
[0033] The markings in the figure are:
[0034] 1. Fuselage, 2. Front wing, 201. Inner front wing, 202. Outer front wing, 3. Rear wing, 301. Inner rear wing, 302. Outer rear wing, 4. Vertical tail, 501. Front rotor power unit, 502. Middle rotor power unit, 503. Rear rotor power unit, 6. Power support frame, 7. Front wheels, 8. Rear wheels. DETAILED DESCRIPTION
[0035] In order to make the above contents, purposes and beneficial effects of the utility model more obvious and easy to understand, the specific implementation methods of the utility model are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the utility model. However, the utility model can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the utility model, so the utility model is not limited by the specific embodiments disclosed below.
[0036] It should be noted that, unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art in the technical field of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.
[0037] like Figure 1-7 As shown, the utility model provides an aircraft with a foldable lift system, comprising a fuselage 1, a foldable front wing 2 and a foldable rear wing 3, a vertical tail 4, a rotor power system and a wheel system.
[0038] Among them, the foldable front wing 2 and rear wing 3 are regularly arranged on the front and rear sections of the fuselage 1 through the activities of the folding components, the rotor power system is regularly arranged on the left and right sides of the fuselage through the power support frame 6, and is flexibly arranged on the left and right sides of the fuselage by connecting with the foldable front wing 2 and rear wing 3 through the power support frame, the vertical tail 4 is symmetrically arranged on the upper side of the tail of the fuselage 1, and the wheel system is regularly arranged on the lower abdomen of the fuselage 1.
[0039] Further, such as Figure 1 As shown, the fuselage 1 adopts a streamlined fuselage, but is not limited to a streamlined fuselage, and can be optimized based on the existing automobile body shape. The interior of the fuselage 1 is a cabin, and openable fuselage doors are regularly arranged on the left and right sides of the cabin. Seats for passengers and drivers to sit on, as well as a control module, are regularly arranged inside the cabin.
[0040] Furthermore, the front wing 2 and the rear wing 3 are movably arranged at the front and rear sections of the fuselage 1 through folding components.
[0041] Among them, the canard 2 includes an inner canard 201 and an outer canard 202. Both the inner and outer canards adopt low-speed high-lift airfoils and are symmetrically arranged at the upper front section of the fuselage 1 to form left and right canards. The roots of the left and right inner canards 201 are hinged to the fuselage 1 through a folding assembly.
[0042] Among them, the rear wing 3 includes an inner rear wing 301 and an outer rear wing 302. The inner and outer rear wings also adopt low-speed high-lift airfoils and are symmetrically arranged at the upper rear section of the fuselage 1 to form left and right rear wings. The roots of the left and right inner rear wings 301 are also hinged to the fuselage 1 through a folding assembly.
[0043] Furthermore, both the front wing and the rear wing are provided with a relatively large installation angle, which is 18°-22°.
[0044] Furthermore, in order to ensure the installation position of the rotor power system, the position of the cabin and the fuselage door is avoided as much as possible to ensure flight safety. The inner front wing 201 and the inner rear wing 301 are both provided with a large dihedral angle, thereby ensuring that the rotor power system avoids the cabin. Among them, the inner front wing 201 is set upward, and the dihedral angle is 8°-12°, and the inner rear wing 301 is also set upward, and the dihedral angle is 26°-30°.
[0045] like Figure 1 As shown, the power support frame 6 is symmetrically arranged on the left and right sides of the fuselage 1 to form left and right power support frames. The power support frame 6 is arranged between the inner front wing and the outer front wing, and between the inner rear wing and the outer rear wing, and is fixedly connected with them to form a whole. The tips of the left and right inner front wings and the roots of the left and right outer front wings are respectively fixedly connected to the left and right power support frames, and the tips of the left and right inner rear wings and the roots of the left and right outer rear wings are also respectively fixedly connected to the left and right power support frames. In this way, Figure 1 and Figure 5 As shown, the left and right power support frames 6 can be folded upward around the folding assembly through the roots of the left and right inner front wings and the left and right inner rear wings, thereby saving space in the width direction of the aircraft and facilitating parking.
[0046] Further, such as Figure 2 As shown, because the upward angle of the inner rear wing 301 is much greater than the upward angle of the inner front wing 201, when the power support frame 6 is arranged and installed between the inner front wing and the outer front wing, and between the inner rear wing and the outer rear wing, the left and right power support frames are arranged as a whole to tilt upward. In this way, on the one hand, the cabin can be avoided, and on the other hand, when the rotor power system is regularly arranged and installed on the power support frame, the propeller plane of the entire rotor power system on the aircraft is arranged to tilt upward relative to the horizontal plane of the fuselage when it is parked, forming a tilted rotor power system of the aircraft.
[0047] like Figure 1 and Figure 2As shown, the rotor power system of the aircraft includes a front rotor power device 501, a middle rotor power device 502 and a rear rotor power device 503, and the front, middle and rear rotor power devices are regularly arranged and installed on the left and right power support frames 6 for the front wing and the rear wing. The front rotor power device 501 is symmetrically arranged and installed on the left and right power support frames on the front side of the front wing to form a left and right front rotor power device; the middle rotor power device 502 is symmetrically arranged and installed on the left and right power support frames between the front wing and the rear wing to form a left and right middle rotor power device; the rear rotor power device 503 is symmetrically arranged and installed on the left and right power support frames on the rear side of the rear wing to form a left and right rear rotor power device.
[0048] Furthermore, all the front, middle and rear rotor power units in the rotor power system use two sets of upper and lower propeller systems, thereby realizing twelve propeller systems for the entire aircraft, greatly increasing the safety redundancy of the aircraft.
[0049] Furthermore, for personal safety reasons and to improve safety performance, the propeller planes of the propeller systems under all the front, middle and rear rotor power units in the rotor power system are higher than the fuselage setting, thereby avoiding the fuselage setting and improving safety performance.
[0050] like Figure 2 As shown, all rotor power devices are arranged upwardly tilted through the power support frame arranged upwardly tilted, forming a tilted rotor power system. Therefore, the installation plane (propeller plane) of all rotor power devices is tilted upward with respect to the horizontal plane when the aircraft is grounded, and the tilt angle is 12°-16°.
[0051] like Figure 4 As shown, the left and right front rotor power devices, the left and right middle rotor power devices, and the left and right rear rotor power devices all rotate in opposite directions. In one embodiment, the left front rotor power device rotates clockwise, the right front rotor power device rotates counterclockwise, the left middle rotor power device rotates counterclockwise, the right middle rotor power device rotates clockwise, the left rear rotor power device rotates clockwise, and the right rear rotor power device rotates counterclockwise.
[0052] like Figure 3-6 As shown, the left and right power support frames 6 are designed in an arc shape, which is designed in an arc shape toward the outside of the fuselage or toward the top of the fuselage. In this way, when the power support frame 6 rotates and folds upward with the inner front wing and the inner rear wing, the middle rotor power device 502 can avoid the upper end of the fuselage.
[0053] Further, such as Figure 4 As shown, the front wing 2 is tilted forward to form a forward sweep angle, and the rear wing 3 is tilted backward to form a backward sweep angle. Through the forward-facing front wing and the backward-facing rear wing, the rotor power system can be reasonably arranged and installed on the left and right power support frames.
[0054] Further, such as Figure 3 As shown, the vertical tail 4 is symmetrically arranged and installed on the upper end of the tail of the fuselage 1 to form left and right vertical tails. The left and right vertical tails can increase the stability of the heading of the aircraft during flight.
[0055] Furthermore, the wheel system includes a front wheel 7 and a rear wheel 8, and the front and rear wheels are respectively arranged symmetrically on the front and rear sections of the lower abdomen of the fuselage 1. Of course, in other embodiments, the wheel system can also be replaced by a landing gear system.
[0056] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. An aircraft with a foldable lift system, characterized in that: include: A fuselage, wherein a cabin is arranged inside the fuselage, and openable fuselage doors are regularly arranged on the left and right sides of the fuselage; Front wings, the front wings are symmetrically arranged at the upper front section of the fuselage to form left and right front wings, the front wings include inner front wings and outer front wings, and the roots of the inner front wings on the left and right sides are hinged and rotatably arranged with the fuselage through a folding assembly; The rear wings are symmetrically arranged at the upper rear section of the fuselage to form left and right rear wings, the rear wings include an inner rear wing and an outer rear wing, and the roots of the inner rear wings on the left and right sides are also hinged and rotatably arranged with the fuselage through a folding assembly; A power support frame, the power support frame is disposed between the inner front wing and the outer front wing, and the inner rear wing and the outer rear wing and is fixedly connected thereto to form a whole, and is symmetrically arranged on the left and right sides of the fuselage to form left and right power support frames; A rotor power system, the rotor power system comprising a plurality of rotor power devices, the plurality of rotor power devices being regularly arranged and installed on the left and right power support frames with respect to the front wing and the rear wing, a front rotor power device being formed on the front side of the front wing, a middle rotor power device being formed between the front wing and the rear wing, and a rear rotor power device being formed on the rear side of the rear wing, the front, middle and rear rotor power devices being symmetrically arranged on the left and right power support frames on the left and right sides of the fuselage; The rotor power system is rotated and folded upward on the power support frame through a folding assembly at the hinged joint of the inner front wing and the inner rear wing root; A wheel system is regularly arranged and installed on the front and rear sections of the lower belly of the fuselage.
2. An aircraft with a foldable lift system as claimed in claim 1, characterized in that: A vertical tail is also arranged and installed on the upper side of the tail of the fuselage.
3. The aircraft with a foldable lift system as claimed in claim 2, characterized in that: The vertical tail is arranged symmetrically on the left and right and is installed on the upper side of the tail of the fuselage.
4. An aircraft with a foldable lift system as claimed in claim 1 or 2, characterized in that: The front wing and the rear wing are set with an installation angle of 18°-22°.
5. An aircraft with a foldable lift system as claimed in claim 1 or 2, characterized in that: The inner front wing is arranged upward to form a front wing dihedral angle, and the angle of the front wing dihedral angle is 8°-12°; the inner rear wing is also arranged upward to form a rear wing dihedral angle, and the angle of the rear wing dihedral angle is 26°-30°; the power support frame is fixed to the tips of the inner front wing and the inner rear wing, and connects the roots of the outer front wing and the outer rear wing. The power support frames on the left and right sides of the fuselage are inclined upward through the upwardly arranged inner front wing and the inner rear wing, and the rotor power system on the left and right power support frames is also inclined upward through the inclined upwardly arranged left and right power support frames to form a tilted rotor power system; the propeller planes of all rotor power devices in the tilted rotor power system are inclined upward with respect to the horizontal plane of the fuselage when it is grounded, and the inclination angle is 12°-16°.
6. The aircraft with a foldable lift system as claimed in claim 5, characterized in that: The propellers of all the rotor power devices in the tilt-rotor power system are kept away from the fuselage by the tilted power support frame.
7. An aircraft with a foldable lift system as claimed in claim 1, 2 or 6, characterized in that: All the rotor power devices in the rotor power system include two sets of upper and lower propeller systems.
8. An aircraft with a foldable lift system as claimed in claim 1 or 2, characterized in that: The fuselage is optimized based on the appearance of the automobile body.