Double-rotor autoroatation aircraft
By using gear transmission components and seesaw blade components in rotor aircraft, synchronous rotation of the dual rotors is achieved, which solves the insufficient carrying capacity and stability of the rotor aircraft under field restrictions and crosswind conditions, and achieves high load weight under small sizes and steady flight.
Patent Information
- Application Number
- CN202421173627.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-27
- Publication Date
- 2024-12-31
- Estimated Expiration
- 2034-05-27
AI Technical Summary
In forest fire extinguishing and other tasks, existing rotor aircraft cannot use long rotors due to site restrictions, resulting in insufficient carrying capacity and complex structure. It is easy to collide up and down rotors under strong crosswind conditions, affecting flight stability.
A dual rotor rotation aircraft is designed to achieve relative rotation and synchronous rotation of the two rotors through gear transmission assembly and seesaw blade assembly, and to maintain rotation with airflow, avoid mutual interference of the rotors and maintain balanced lift.
The load capacity is increased under limited rotor size, reduce takeoff distance, ensure flight stability and easy handling, and reduce structural complexity and drive usage costs.
Smart Images
Figure CN222272341U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to an aircraft, in particular to a double-rotor autorotating aircraft. Background Art
[0002] At present, more and more aircraft have been applied in many places, especially the popularity of unmanned aircraft, making the application of aircraft more and more extensive. In addition to military aircraft, there are many other types of civil aircraft, such as autogyro, which means that the wings are installed above the fuselage, and the wings rotate above the fuselage to generate rising buoyancy. Rotorcraft are divided into single-rotor aircraft and double-rotor autogyro. At present, conventional autogyros have two rotor blades; in order to increase the load, the length of the rotor blades can generally only be increased. However, for rescue and emergency rescue, especially forest fire-fighting aircraft, temporary take-off sites near the fire are generally threshing fields, playgrounds, relatively flat rural roads, etc., which are difficult to accommodate the take-off and landing of large autogyros. Therefore, it is particularly important to manufacture an autogyro with a shorter rotor length but a larger payload.
[0003] The current rotorcraft has limited lift. To increase lift, the number of blades must be increased or the length of the blades must be lengthened. After increasing the number of blades, the simple seesaw structure cannot be used. The function of the seesaw structure is that the forward blade (running in the same direction as the flight direction) has a large lift, and the reverse blade has a small lift. Therefore, a very simple seesaw structure can make the two blades swing up and down during operation, thereby changing the angle with the airflow and balancing the lift. This is why 99% of the current autogyros use two blades and a seesaw structure. After increasing the number of blades, the seesaw can no longer be used, but each blade must be connected to the aircraft with three swing hinges like a helicopter, and the overall structure becomes more complicated, so the advantage of the simple structure of the rotorcraft is gone. Increasing the length of the blades can indeed greatly increase the carrying capacity. However, for tasks such as forest fire rescue, because the rotorcraft needs to take off and land not far from the fire scene and carry fire extinguishing liquid to extinguish the fire, it is limited by the site and cannot use very long blades, which are generally limited to 2 to 3 meters in length. If it is longer, it will be difficult to find a suitable take-off and landing location. In order to solve these problems, in order to retain the simple structure of the seesaw and increase the carrying capacity without increasing the length of the blades, two rotors are currently stacked up and down, rotating separately. Because the rotors will swing up and down while rotating (the principle of the seesaw), therefore, under certain flight conditions, especially under strong side winds, the upper and lower rotors may collide with each other and cause serious accidents. In order to avoid this problem, increasing the upper and lower rotors has limited effect and can only alleviate it. At the same time, it will increase the center of gravity and cause poor flight stability. Although letting the upper and lower rotors rotate synchronously at a fixed difference angle can solve the problem of mutual collision between the upper and lower wings. However, at the same time, because the wind blows against the upper and lower wings and slows down before blowing to the second layer of wings, the rotors rotate at synchronous speed when the wind speeds are inconsistent at the two locations, resulting in a large difference in lift, which prevents the two layers of rotors from achieving the optimal lift efficiency at the same time. Utility Model Content
[0004] In order to solve the above technical problems, the utility model provides a twin-rotor autorotating aircraft, which can obtain a larger load capacity under a relatively limited rotor size.
[0005] In order to solve the above technical problems, the utility model adopts the following technical solutions:
[0006] A twin-rotor autorotating aircraft comprises a fuselage, a nose being arranged on one side of the fuselage, a tail being arranged on the other side of the fuselage, a propeller being arranged on the tail, and a wheel being installed at the bottom of the fuselage, a driving assembly being arranged in the fuselage, a connecting rod being installed on the fuselage, one end of the connecting rod extending into the fuselage and connected with the driving assembly, the connecting rod being driven to rotate by the driving assembly, a gear transmission assembly being installed at the other end of the connecting rod, a supporting bracket being installed on the fuselage, the gear transmission assembly being installed in the supporting bracket, a first rotor and a second rotor being arranged in opposite inclination directions, the driving assembly driving the gear transmission assembly to operate through the connecting rod, so that the first rotor and the second rotor rotate relative to each other, the first rotor and the second rotor both comprising a seesaw blade assembly, and the seesaw blade assembly having two blades.
[0007] The gear transmission assembly includes a driving gear, a first synchronous gear and a second synchronous gear, the first synchronous gear and the second synchronous gear are arranged on both sides of the driving gear and are meshed with the driving gear, the connecting rod is connected to the driving gear, a first rotating shaft is installed on the first rotor, the first rotating shaft is connected to the first synchronous gear, a second rotating shaft is installed on the second rotor, the second rotating shaft is connected to the second synchronous gear, and the first rotating shaft and the second rotating shaft are inclined in opposite directions.
[0008] The first synchronous gear and the second synchronous gear are symmetrically distributed around the driving gear.
[0009] The gear transmission assembly includes a driving gear, a first synchronous gear and a second synchronous gear, the driving gear is meshed and connected with the first synchronous gear or the second synchronous gear, the first synchronous gear is meshed and connected with the second synchronous gear, the connecting rod is connected with the driving gear, a first rotating shaft is installed on the first rotor, the first rotating shaft is connected with the first synchronous gear, a second rotating shaft is installed on the second rotor, the second rotating shaft is connected with the second synchronous gear, and the first rotating shaft and the second rotating shaft are inclined in opposite directions.
[0010] The gear transmission assembly includes a first synchronous gear and a second synchronous gear, the first synchronous gear is meshed and connected with the second synchronous gear, the connecting rod is connected with the first synchronous gear or the second synchronous gear, a first rotating shaft is installed on the first rotor, the first rotating shaft is connected with the first synchronous gear, a second rotating shaft is installed on the second rotor, the second rotating shaft is connected with the second synchronous gear, and the first rotating shaft and the second rotating shaft are inclined in opposite directions.
[0011] The first rotor and the second rotor have the same inclination angle.
[0012] The driving assembly is a driving motor, and the output shaft of the driving motor is connected to the connecting rod through a coupling.
[0013] The first rotating shaft and the second rotating shaft are both equipped with fixed blocks for assembling blades. The seesaw blade assembly includes a seesaw, a mounting groove is provided in the fixed block, the middle part of the seesaw is placed in the mounting groove and is rotatably installed with the fixed block through a pin shaft, and the two ends of the seesaw are respectively used for installing blades.
[0014] The first rotor is arranged above the second rotor, or the second rotor is arranged above the first rotor, forming a tilted posture of one high and one low.
[0015] The first rotor and the second rotor have the same size specifications.
[0016] Compared with the prior art, the utility model has the following beneficial technical effects:
[0017] The two rotors are driven by a drive motor to rotate synchronously relative to each other. During the takeoff phase, the drive motor drives the two rotors to perform a pre-rotation. The forward flight power comes from the propulsion propeller behind the fuselage. Once the aircraft moves forward, the drive motor stops running and no longer drives the two rotors to rotate, that is, the drive motor no longer outputs power. The drive motor drives the two rotors to perform a pre-rotation. This pre-rotation mainly reduces the takeoff distance from about 100 meters to 10 to 30 meters.
[0018] After taking off from the ground, the two rotors on the top are pushed by the oncoming airflow to rotate and generate power. No additional driving force is required to keep the aircraft rotating with the help of the airflow, thereby making the aircraft fly smoothly. The two rotors will not interfere with each other, reducing the assembly space and use cost of the drive. The double rotors are set and distributed so that the lift force of the whole aircraft can be roughly balanced, making the aircraft more stable and easier to control. The synchronous rotation of the two gears and the seesaw structure of the seesaw blade assembly ensure that the two rotors will not collide with each other, thereby increasing the rotor area without affecting the normal rotation of the rotor, and being able to obtain a larger load capacity within a limited size. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a schematic diagram of the three-dimensional structure of the utility model;
[0020] Figure 2 This is a schematic diagram of the main structure of the utility model;
[0021] Figure 3 This is a rear view structural diagram of the utility model;
[0022] Figure 4 This is a structural schematic diagram of a first embodiment of the gear transmission assembly in the utility model;
[0023] Figure 5 This is a structural schematic diagram of the second embodiment of the gear transmission assembly in the utility model;
[0024] Figure 6 This is a schematic structural diagram of the third embodiment of the gear transmission assembly in the present utility model;
[0025] Reference numerals:
[0026] Fuselage 1, tail 2, wheel 3, nose 4, connecting rod 5, supporting bracket 6, first rotor 7, second rotor 8, driving gear 9, first synchronous gear 10, second synchronous gear 11, first rotating shaft 12, second rotating shaft 13, fixed block 14, seesaw 15. DETAILED DESCRIPTION
[0027] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.
[0028] In the description of the present utility model, it should be understood that if the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like are involved, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present utility model and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present utility model, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.
[0029] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection. It can be a mechanical connection or an electrical connection. It can be directly connected or indirectly connected through an intermediate medium. It can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0030] Embodiment 1
[0031] like Figure 1-4 As shown, a twin-rotor autorotating aircraft comprises a fuselage 1, a nose 4 is provided on one side of the fuselage 1, a tail 2 is provided on the other side of the fuselage 1, a propeller is provided on the tail, a wheel 3 is installed at the bottom of the fuselage 1, a driving assembly is provided in the fuselage, a connecting rod 5 is installed on the fuselage, one end of the connecting rod 5 extends into the fuselage 1 and is connected to the driving assembly, and the connecting rod is driven to rotate by the driving assembly, a gear transmission assembly is installed on the other end of the connecting rod 5, a supporting bracket 6 is installed on the fuselage 1, and the gear transmission assembly is installed in the supporting bracket 6, a first rotor 7 and a second rotor 8 are installed on the gear transmission assembly, the first rotor 7 and the second rotor 7 are cross-distributed, and the first rotor 7 and the second rotor 8 are both tilted, the driving assembly drives the gear transmission assembly to operate through the connecting rod, so that the first rotor and the second rotor rotate relative to each other, and the first rotor and the second rotor both include a seesaw blade assembly, and the seesaw blade assembly has two blades. By setting the first rotor and the second rotor to be tilted in opposite directions, usually with a tilt of 1-6 degrees, they can just avoid each other and will not interfere with each other, and relative rotation can be achieved. The drive assembly is usually a drive motor, and the specific model and power can be flexibly selected according to the size of the aircraft. The drive assembly drives the gear transmission assembly to rotate, thereby realizing the synchronous relative rotation of the first rotor and the second rotor.
[0032] The gear transmission assembly includes a driving gear 9, a first synchronous gear 10 and a second synchronous gear 11. The first synchronous gear 10 and the second synchronous gear 11 are arranged on both sides of the driving gear 9 and are meshed with the driving gear 9. The connecting rod 5 is connected to the driving gear 9. The first rotating shaft 12 is installed on the first rotor 7, and the first rotating shaft 12 is connected to the first synchronous gear 10. The second rotating shaft 13 is installed on the second rotor 11, and the second rotating shaft 13 is connected to the second synchronous gear 12. The first rotating shaft 12 and the second rotating shaft 13 are both inclined. The first synchronous gear 10 and the second synchronous gear 11 are symmetrically distributed with the driving gear 9 as the center. The driving assembly drives the driving gear to rotate, and the first synchronous gear and the second synchronous gear are located on both sides of the driving gear. Therefore, the first synchronous gear and the second synchronous gear rotate synchronously and in opposite directions, so that the first rotor and the second rotor rotate synchronously relative to each other, ensuring that the rotation process does not interfere with each other.
[0033] During assembly, the first synchronous gear and the second synchronous gear are also tilted in opposite directions to ensure the tilted assembly of the first rotor and the second rotor. The first rotor and the second rotor have the same inclination angle and are usually the same in size to ensure balance.
[0034] Embodiment 2
[0035] refer to Figure 2-3As shown in Figure 5, the gear transmission assembly includes a driving gear 9, a first synchronous gear 10 and a second synchronous gear 11. The driving gear 9 is meshed and connected with the first synchronous gear 10, and the first synchronous gear 10 is meshed and connected with the second synchronous gear 11. The connecting rod 5 is connected with the driving gear 9. The first rotating shaft 12 is installed on the first rotor 7, and the first rotating shaft 12 is connected with the first synchronous gear 10. The second rotating shaft 13 is installed on the second rotor 8, and the second rotating shaft 13 is connected with the second synchronous gear 11. The first rotating shaft 12 and the second rotating shaft 13 are inclined in opposite directions. In the second embodiment, the central gear 9 is only meshed and connected with the first synchronous gear 10. The central gear 9 is arranged on one side of the first synchronous gear 10. The central gear 9 does not contact the second synchronous gear 11, and the second synchronous gear is only meshed and connected with the first synchronous gear. Under the structure, the central gear drives the first synchronous gear to rotate, and the first synchronous gear then drives the second synchronous gear to rotate. The difference from the first embodiment is that in the first embodiment, the central gear is meshed and connected with the first synchronous gear and the second synchronous gear at the same time. Therefore, structurally speaking, the gear transmission efficiency of the structure of the first embodiment will be higher than the gear transmission efficiency of the second embodiment. However, both structures can achieve synchronous relative rotation of the first rotor and the second rotor.
[0036] Of course, there may be another embodiment: the central gear is meshed with the second synchronous gear, and the second synchronous gear is meshed with the first synchronous gear, the central gear drives the second synchronous gear to rotate, and the second synchronous gear drives the first synchronous gear to rotate.
[0037] Embodiment 3
[0038] refer to Figure 1-3 As shown in Figure 6, the gear transmission assembly includes a first synchronous gear 10 and a second synchronous gear 11, the first synchronous gear 10 is meshed and connected with the second synchronous gear 11, the connecting rod 5 is connected with the first synchronous gear 10 or the second synchronous gear 12, the first rotor 7 is equipped with a first rotating shaft 12, the first rotating shaft 12 is connected with the first synchronous gear 10, the second rotor 8 is equipped with a second rotating shaft 13, the second rotating shaft 13 is connected with the second synchronous gear 11, and the first rotating shaft 12 and the second rotating shaft 13 are inclined in opposite directions. That is, in the third embodiment, the central gear in the first and second embodiments is not provided, but the power transmission is realized by directly connecting the first synchronous gear or the second synchronous gear with the driving assembly.
[0039] In addition, a fixed block 14 for assembling blades is installed on the first rotating shaft 12 and the second rotating shaft 13, and a seesaw 15 is rotatably installed on the fixed block 14 through a pin shaft, and the two ends of the seesaw 15 are used to symmetrically install blades. The two ends of the seesaw can be tilted up and down with the pin shaft installed with the fixed block as the center.
[0040] The first rotor is set as the forward rotor and the second rotor is set as the backward rotor. The two blades in a rotor are installed at one end of the seesaw and the other at the other end of the seesaw. One of the two blades is the forward blade and the other is the backward blade. For the counter-rotating double propellers, one blade on each side is forward, so the lift of the whole machine will be roughly balanced, making the aircraft more stable and easier to control. The first rotor and the second rotor are constantly rotating at the top. When one of the blades moves toward the nose (the forward blade), the other blade must move backward (the backward blade). The aircraft itself is also flying forward. Therefore, the relative air speed of the forward blade = the forward blade speed + the aircraft speed, and the backward blade speed = the backward blade speed - the aircraft speed. In this way, the speeds of the two blades are different. According to the lift formula, the lift must be different. Through the seesaw structure, in the same rotor, the forward blade is pressed down and the backward blade is tilted up, thereby changing the angle and balancing the influence of the speed, so that the lift of the two blades is basically kept constant. The structure is very simple, so the cost and maintenance are low.
[0041] When the present application is flying, the first rotor and the second rotor are first driven to rotate by the drive motor. The rotation at this time is a pre-rotation, which can reduce the take-off distance and propel the flight forward through the propeller at the tail. Once the aircraft flies forward, the drive motor no longer needs to provide power. At this time, the drive motor stops running and the airflow is used to keep the first rotor and the second rotor rotating, thereby achieving a smooth flight of the aircraft.
[0042] For tasks such as forest fire fighting, hovering is not required, and a larger number of aircraft and a larger load are required. Therefore, gyroplanes can play an important role. At the same time, the use of cross-synchronous twin autorotating rotors can increase the transportation capacity by nearly 1 times without increasing the size of the gyroplane. Therefore, the twin-rotor autorotating aircraft with the structure of the utility model can achieve a larger load capacity with a smaller size.
[0043] Because forest fires are often located in remote areas with inconvenient transportation, it is very difficult to find a large take-off and landing site. Therefore, small-sized, large-load rotorcraft have a huge space to play.
[0044] It should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. However, 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. A twin-rotor autorotating aircraft, comprising a fuselage, a nose being arranged on one side of the fuselage, a tail being arranged on the other side of the fuselage, a propeller being arranged on the tail, and a wheel being mounted on the bottom of the fuselage, characterized in that: A driving assembly is provided in the fuselage, and a connecting rod is installed on the fuselage. One end of the connecting rod extends into the fuselage and is connected to the driving assembly, and the connecting rod is driven to rotate by the driving assembly. A gear transmission assembly is installed on the other end of the connecting rod. A supporting bracket is installed on the fuselage, and the gear transmission assembly is installed in the supporting bracket. A first rotor and a second rotor are installed on the gear transmission assembly. The first rotor and the second rotor are cross-distributed, and the first rotor and the second rotor are both inclined with one side higher than the other side. The driving assembly drives the gear transmission assembly to operate through the connecting rod, so that the first rotor and the second rotor rotate relative to each other. The first rotor and the second rotor both include a seesaw blade assembly, and the seesaw blade assembly has two blades.
2. The twin-rotor autorotating aircraft according to claim 1, characterized in that: The gear transmission assembly includes a driving gear, a first synchronous gear and a second synchronous gear, the first synchronous gear and the second synchronous gear are arranged on both sides of the driving gear and are meshed with the driving gear, the connecting rod is connected to the driving gear, a first rotating shaft is installed on the first rotor, the first rotating shaft is connected to the first synchronous gear, a second rotating shaft is installed on the second rotor, the second rotating shaft is connected to the second synchronous gear, and the first rotating shaft and the second rotating shaft are inclined in opposite directions.
3. The twin-rotor autorotating aircraft according to claim 2, characterized in that: The first synchronous gear and the second synchronous gear are symmetrically distributed around the driving gear.
4. The twin-rotor autorotating aircraft according to claim 1, characterized in that: The gear transmission assembly includes a driving gear, a first synchronous gear and a second synchronous gear, the driving gear is meshed and connected with the first synchronous gear or the second synchronous gear, the first synchronous gear is meshed and connected with the second synchronous gear, the connecting rod is connected with the driving gear, a first rotating shaft is installed on the first rotor, the first rotating shaft is connected with the first synchronous gear, a second rotating shaft is installed on the second rotor, the second rotating shaft is connected with the second synchronous gear, and the first rotating shaft and the second rotating shaft are inclined in opposite directions.
5. The twin-rotor autorotating aircraft according to claim 1, characterized in that: The gear transmission assembly includes a first synchronous gear and a second synchronous gear, the first synchronous gear is meshed and connected with the second synchronous gear, the connecting rod is connected with the first synchronous gear or the second synchronous gear, a first rotating shaft is installed on the first rotor, the first rotating shaft is connected with the first synchronous gear, a second rotating shaft is installed on the second rotor, the second rotating shaft is connected with the second synchronous gear, and the first rotating shaft and the second rotating shaft are inclined in opposite directions.
6. The twin-rotor autorotating aircraft according to claim 1, characterized in that: The first rotor and the second rotor have the same inclination angle.
7. The twin-rotor autorotating aircraft according to claim 1, characterized in that: The driving assembly is a driving motor, and the output shaft of the driving motor is connected to the connecting rod through a coupling.
8. The twin-rotor autorotating aircraft according to claim 2, 4 or 5, characterized in that: The first rotating shaft and the second rotating shaft are both equipped with fixed blocks for assembling blades. The seesaw blade assembly includes a seesaw, a mounting groove is provided in the fixed block, the middle part of the seesaw is placed in the mounting groove and is rotatably installed with the fixed block through a pin shaft, and the two ends of the seesaw are respectively used for installing blades.
9. The twin-rotor autorotating aircraft according to claim 1, characterized in that: The first rotor is arranged above the second rotor, or the second rotor is arranged above the first rotor, forming a tilted posture of one high and one low.
10. The twin-rotor autorotating aircraft according to claim 8, characterized in that: The first rotor and the second rotor have the same size specifications.