Aircraft with laminated tilting rotor structure
By designing an aircraft with a stacked tiltrotor structure, employing a double-layered wing and staggered tiltrotors, the problem of large space occupation in existing aircraft is solved, resulting in a smaller wing area and lower drag, and improving control flexibility and safety.
Patent Information
- Application Number
- CN202520790519.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-24
- Publication Date
- 2025-12-26
- Estimated Expiration
- 2035-04-24
AI Technical Summary
Existing tiltrotor aircraft occupy a large amount of space, limiting their applications.
The aircraft adopts a stacked tiltrotor structure, with a double-layered wing design. The tiltrotors extend out of the wing in opposite directions, forming airflow paths that are stacked relative to the fuselage, reducing airflow interference and drag.
It effectively reduces the space occupied by the wings, lowers drag, facilitates control, and improves the flexibility and safety of applications.
Smart Images
Figure CN223721143U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to an aircraft technical field especially relates to a kind of aircraft of laminated tilt rotor structure. BACKGROUND
[0002] The type of traditional aircraft has fixed-wing aircraft and multicopter etc..Fixed-wing aircraft technology is relatively mature, fast, long range, large carrying capacity, but in the process of take-off or descent needs long runway.Multicopter can be without aircraft runway, vertical take-off and landing in narrow site, but the speed of flight is slower, flight time is short, and the range is short.
[0003] Tilt-rotor aircraft not only has multicopter can be flexible and convenient vertical take-off, also simultaneously takes into account the performance of fixed-wing aircraft speed, long range.But most of the existing single-layer wing sets up the structure of tilt rotor, but most single-layer wing length occupies longer space, can not meet the application needs of some narrow space. UTILITARY MODEL CONTENT
[0004] In order to overcome the above technical defects, the purpose of the utility model is to provide a kind of aircraft of laminated tilt rotor structure, to solve the problem that the aircraft with tilt rotor of prior art occupies larger space, application is limited.
[0005] The utility model discloses a kind of aircraft of laminated tilt rotor structure,
[0006] Including fuselage, wing, tail, landing gear and tilt rotor assembly;
[0007] The wing includes first wing and second wing arranged side by side along the height direction of the fuselage, wherein the first wing is higher than the second wing;
[0008] The tilt rotor assembly includes a first tilt rotor pair and a second tilt rotor pair, and the first tilt rotor pair and the second tilt rotor pair each include at least two tilt rotors;
[0009] The first tilt rotor pair and the second tilt rotor pair are arranged correspondingly and connected to the first wing and the second wing respectively;
[0010] The tilt rotors of the first tilt rotor pair and the tilt rotors of the second tilt rotor pair extend out of the wing in directions opposite to each other to form airflow paths distributed in layers in front and back of the fuselage.
[0011] Preferably, the tilt rotors of the first tilt rotor pair are symmetrically located on the first wing along the fuselage;
[0012] The tilt rotors of the second pair of tilt rotors are located on the second wing in a one-to-one correspondence with the tilt rotors of the first pair of tilt rotors in an up-down manner.
[0013] Preferably, the tilt rotors of the first pair of tilt rotors extend to the rear of the first wing.
[0014] The tilt rotors of the second pair of tilt rotors extend to the front of the second wing.
[0015] Preferably, the tilt rotors comprise support rods, tilt control mechanisms, motors and blades.
[0016] The blades of the first pair of tilt rotors and the second pair of tilt rotors are respectively located at a consistent distance from the centerline of the wing.
[0017] Preferably, the motors and blades of the first pair of tilt rotors are controlled by the tilt control mechanisms thereof to rotate by 90° in the direction of the second wing.
[0018] The motors and blades of the second pair of tilt rotors are controlled by the tilt control mechanisms thereof to rotate by 90° in the direction of the first wing.
[0019] Preferably, the support rods of the tilt rotors extend beyond the length of the blades by the length of the wing portion.
[0020] Preferably, the distance between the support rods and the fuselage exceeds the length of the blades.
[0021] Preferably, the first wing and / or the second wing respectively comprise a main wing and two auxiliary wings connected to the side edges of the main wing.
[0022] The auxiliary wings are located on the rear side of the main wing, and the tilt rotors extend to the tilt rotors along the side edges of the main wing away from the fuselage.
[0023] Preferably, the tail wing comprises a vertical tail wing and horizontal tail wings located on both sides of the vertical tail wing.
[0024] Preferably, the control module and the sensor assembly are further included.
[0025] The control module collects flight information in real time through the sensor assembly and dynamically optimizes the control parameters of each tilt rotor according to the flight information.
[0026] After the above technical solutions are adopted, the following beneficial effects are achieved compared with the prior art:
[0027] The application provides a kind of aircraft of laminated tilt rotor structure, including fuselage, wing, tail, landing gear and tilt rotor assembly, application double-layer wing, and tilt rotor extends out wing in direction of each other opposite departure, forms the airflow path of relative fuselage front-back laminated distribution, effectively reduces the airflow between each tilt rotor generated mutual interference, provides smaller wing area in vertical direction, reduces resistance, facilitates control, solves the problem that existing aircraft with tilt rotor occupies larger space, application is limited. BRIEF DESCRIPTION OF DRAWINGS
[0028] Figure 1 For the aircraft in fixed wing mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0029] Figure 2 For the aircraft in fixed wing mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0030] Figure 3 For the aircraft in fixed wing mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0031] Figure 4 For the aircraft in tilt transition mode in the aircraft embodiment of the utility model, the structure schematic diagram is shown.
[0032] Figure 5 For the aircraft in tilt transition mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0033] Figure 6 For the aircraft in tilt transition mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0034] Figure 7 For the aircraft in helicopter mode in the aircraft embodiment of the utility model, the structure schematic diagram is shown.
[0035] Figure 8 For the aircraft in helicopter mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0036] Figure 9 For the aircraft in helicopter mode in the aircraft embodiment of the utility model, the structure schematic diagram of tilt rotor is shown in another view.
[0037] Reference Signs:
[0038] 1 - fuselage; 2 - wing; 21 - first wing; 22 - second wing; 221 - main wing; 222 - aileron; 3 - tail; 4 - landing gear; 51 - first pair of tilt rotors; 52 - second pair of tilt rotors; 6 - tilt rotor; 61 - support rod; 62 - tilt control mechanism; 63 - motor; 64 - blade. DETAILED DESCRIPTION
[0039] The advantages of the present application are further illustrated in the following description with reference to the accompanying drawings and specific examples.
[0040] The exemplary embodiments will be described in detail herein below with reference to the accompanying drawings. In the following description, unless otherwise indicated, like numbers in the different drawings represent similar or analogous elements. The embodiments described in the following exemplary embodiments are not meant to represent all embodiments consistent with the present disclosure. Rather, they are merely examples of apparatuses and methods consistent with some aspects of the present disclosure as detailed in the appended claims.
[0041] The terminology used in the present disclosure is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used in the present disclosure and the appended claims, the singular forms "a," "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
[0042] It will be understood that, although the terms first, second, third, etc. can be used herein to describe various information, these terms are not intended to denote a temporal or chronological order. Rather, these terms are used only to distinguish different sets of information from one another. For example, a first information can be termed a second information, and similarly, a second information can also be termed a first information, without departing from the scope of the present disclosure. As used herein, the word "if' can be construed to mean "when" or "in response to determining" depending on the context.
[0043] In the description of the present application, it should be understood that the terms "longitudinal", "transverse", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like refer to the orientation or positional relationship of the fuselage shown in the drawings.
[0044] In the description of the utility model, unless otherwise specified and limited, it needs to be explained that the terms "mounting", "connection" should be understood broadly, for example, it can be mechanical connection or electrical connection, it can also be the communication inside two elements, it can be directly connected, or it can be indirectly connected through intermediate medium, for the ordinary skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.
[0045] In the subsequent description, the suffix such as "module", "component" or "unit" used for indicating elements is only for the convenience of the description of the utility model, and it does not have specific meaning itself. Therefore, "module" and "component" can be used mixedly.
[0046] Regarding the drawing, only in the attached Figure 2 The main wing and aileron are marked, each drawing includes, but it can cause unclear indication of repeated lines, so it is not marked; only in the attached Figure 3 The specific structure of the tilt rotor is marked, and the actual other drawings are similar, and it can cause unclear indication of repeated lines, so it is not marked; each drawing includes the structure possessed by the aircraft, but the line part is not repeatedly marked, and it should not be understood as the limitation of the embodiment.
[0047] Embodiment: the embodiment discloses a kind of aircraft of laminated tilt rotor structure, specifically, referring to Figures 1-9 The aircraft can be airplane, small unmanned aerial vehicle etc., including fuselage, wing, tail, landing gear and tilt rotor assembly;
[0048] In the present embodiment, the wing is double-layer wing, and the tilt rotor assembly is arranged on the double wing to realize the laminated tilt rotor structure on the aircraft, as a preferred arrangement, the wing length of the double-layer wing (i.e. the first wing and the second wing described below) does not exceed 1.5 times the length of the fuselage, to be suitable for application in narrow scene, by the setting of double-layer wing, the vertical wing of the aircraft in helicopter mode occupies smaller space than existing most aircraft, and the ascending resistance is smaller, which is convenient for control, and in fixed-wing mode, it can provide larger lift.
[0049] Specifically, the wings include a first wing and a second wing arranged side by side along the height direction of the fuselage, wherein the first wing is higher than the second wing; the tilt-rotor assembly includes a first tilt-rotor pair and a second tilt-rotor pair, the first tilt-rotor pair and the second tilt-rotor pair each include at least two tilt-rotors, i.e., the tilt-rotors can be four or a multiple of four; the first tilt-rotor pair and the second tilt-rotor pair are arranged correspondingly and connected to the first wing and the second wing respectively; the tilt-rotors of the first tilt-rotor pair and the tilt-rotors of the second tilt-rotor pair extend out of the wings in directions opposite to each other to form airflow paths that are stacked in front and back directions relative to the fuselage.
[0050] It should be noted that the tilt-rotors on the first wing and the second wing are staggered in the embodiment, wherein the staggering includes front and back (front relative to the fuselage, the nose part is the front, and the wings are the back) and up and down (there is a height difference between the double-layer wings), and at least four mutually parallel airflow paths are formed. In any state, the working parameters of each group of tilt-rotor pairs are controlled. It can be understood that there is a height difference between the first tilt-rotor pair and the second tilt-rotor pair, and there is a difference in the airflow environment between the up and down layers of wings. The lower layer of wings is closer to the ground, and the airflow is more turbulent, and may be disturbed by the wake of the upper layer of wings. The upper layer of wings is in a relatively smooth airflow. Therefore, the upper layer of rotors (the tilt-rotors on the first wing) may need to generate greater pull to compensate for the lift lost by the lower layer of rotors (the tilt-rotors on the second wing) due to airflow disturbance. According to the relationship between the preset / standard rotor pull and power, corresponding control parameters are generated.
[0051] In the embodiment, the tilt-rotors on the upper and lower first wing and second wing in the application are staggered in the front and back directions, which effectively reduces the mutual interference between the airflows generated by the upper and lower layers, is safer, and only needs to consider the pull effect caused by the height for power control, which is simple to control.
[0052] Specifically, the wings are double-layer wings, and the specific structure can adopt the existing wing structure or be improved according to the scene by setting specific parameters, such as wing surface inclination, length, turning angle area, thickness, etc. The first wing and / or the second wing each include a main wing and two auxiliary wings connected to the side edges of the main wing. The auxiliary wings are located at the rear side of the main wing, and the tilt-rotors extend to the tilt-rotors along the side edges of the main wing away from the fuselage. The main wing is used to provide main lift and control the longitudinal (pitch) attitude. The auxiliary wings are located at the trailing edge of the main wing, which can facilitate the longitudinal axis roll attitude of the aircraft.
[0053] Specifically, the above-mentioned aircraft further comprises a tail wing, a landing gear, and the general structure of the existing aircraft can be applied. In the present embodiment, the tail wing is connected to the tail end of the fuselage, and the tail wing comprises a vertical tail and a rudder. The vertical tail is used to maintain the heading balance of the aircraft during flight, and the rudder is used to provide heading control. It also includes a horizontal tail and an elevator. The horizontal tail is used to maintain the pitch balance of the aircraft during flight, and the elevator is used to provide pitch control. For example, in the fixed-wing mode, the aircraft needs to be controlled to ascend, and the elevator of the horizontal tail is deflected downward, and the nose of the aircraft will be lifted and climb. The landing gear includes a retractable mechanism, wheels, shock-absorbing mechanisms, etc.
[0054] Specifically, the above-mentioned aircraft includes a tilt-rotor assembly, the tilt-rotors of the first pair of tilt-rotors are symmetrically located on the first wing along the fuselage, and the tilt-rotors of the second pair of tilt-rotors are correspondingly located on the second wing above and below the tilt-rotors of the first pair of tilt-rotors. In the present embodiment, the above-mentioned "corresponding arrangement" refers to the corresponding positions on the first wing and the second wing, that is, the first pair of tilt-rotors and the second pair of tilt-rotors are in the same position in two planes at different heights. It can be understood that the "corresponding arrangement" is mainly to maintain the symmetry of the aircraft as a whole, thereby simplifying the control of each tilt-rotor. The first pair of tilt-rotors and the second pair of tilt-rotors can not be completely corresponding, but they need to be distributed in pairs on the first wing and the second wing, respectively. As an example, the distance between the tilt-rotors of the first pair of tilt-rotors can be less than / greater than (i.e., not exactly equal to) the distance between the tilt-rotors of the second pair of tilt-rotors, or the tilt-rotors of the first pair of tilt-rotors and the tilt-rotors of the second pair of tilt-rotors are not completely parallel, but have a certain displacement in the direction of the wing, that is, the first pair of tilt-rotors and the second pair of tilt-rotors are distributed in different positions inside and outside the part, but at this time the control parameters of each tilt-rotor need to be adjusted (each tilt-rotor control is different, and the specific control parameters are complex) to maintain the stable operation of the aircraft.
[0055] Specifically, in the embodiment, the tilt rotors of the first tilt rotor pair extend to the rear of the first wing, and the tilt rotors of the second tilt rotor pair extend to the front of the second wing, that is, staggered in the front-rear direction. The tilt rotors include a support rod, a tilt control mechanism, a motor, and a blade. The blades of the first tilt rotor pair and the second tilt rotor pair are respectively consistent in distance relative to the wing center line (the blades are distributed equidistantly on both sides of the wing center line), and the distance of the blades relative to the wing center line is limited (for precise positioning, it can be the center of the blade). In fact, the "distance of the blade relative to the wing center line" can be understood as a plane formed by the center lines of the double-layer wings, and the distance of the blade to the plane when the tilt rotor is in a vertical state (fixed wing mode). The center of gravity of the wing is located in the plane, and the purpose is to make the tilt rotor assembly symmetrically distributed on the wing, thereby making the control process simple and improving safety during application of the aircraft.
[0056] It can be understood that the motor and the blade of the tilt rotor are driven to deflect by the tilt control mechanism (a structure for controlling the tilt of the rotor, which specifically can include a connecting rod, a tilt steering machine, a joint, etc.). As an example, the tilt control mechanism is connected to the motor, and the motor is connected to the blade, which is sleeved on the end of the support rod, so that the tilt control mechanism drives the motor and the blade to deflect at different angles.
[0057] Specifically, taking the tilt rotors of the first tilt rotor pair as an example, one end of the tilt rotor support rod is connected to the first wing, and the other end is connected to the blade. When the tilt rotor is in a horizontal state, the blade faces downward, and the support rod is connected to the upward side of the blade. During control, the blade is positionally limited by the support rod, and the direction of the generated airflow is also considered. It is set that the blade can only be driven to rotate in the downward plane. Therefore, in the embodiment, the motor and the blade of the first tilt rotor pair are controlled by the tilt control mechanism thereof to rotate by 90° in the direction facing the second wing, and the motor and the blade of the second tilt rotor pair are controlled by the tilt control mechanism thereof to rotate by 90° in the direction facing the first wing. In the embodiment, the tilt rotor deflects from the horizontal direction to the vertical direction, that is, rotates by 90°. The first tilt rotor pair is at the rear, and the second tilt rotor pair is at the front. The front row of tilt rotors is limited to be driven to tilt upward, and the rear row of tilt rotors is driven to tilt downward.
[0058] It can be understood that the first tilt rotor pair can also be arranged forwardly, and the second tilt rotor pair can also be arranged rearwardly, but needs to be limited in the above-mentioned rotation direction.
[0059] As a preferred configuration, the support rod of the tilt rotor extends to cover at least 1 / 2 of the wing width and connects to the wing. That is, in the first tilt rotor pair of the above example, the support rod of the tilt rotor extends from the trailing edge of the first wing to cover at least 1 / 2 of the wing width, as shown in the figure, and can extend to 2 / 3 of the wing width, which makes the tilt rotor connection more stable.
[0060] As a preferred configuration, the length of the support rod extending beyond the wing portion of the tiltrotor exceeds the length of the blade; and / or, the distance between the support rod and the fuselage exceeds the length of the blade, ensuring that the blade maintains a certain distance from the fuselage and wing during rotation, preventing the tiltrotor from contacting the fuselage / wing under any conditions. Furthermore, the length of the support rod can be set separately according to the different control requirements of the upper and lower wings, thereby achieving stable control of the aircraft. For example, considering the altitude difference, the length of the support rod covering the first wing can be set longer than that covering the second wing, thus providing greater lift to the first tiltrotor and improving operational safety.
[0061] Based on the above, this embodiment also provides a control method for an aircraft with a stacked tilt rotor structure. Using the above-described aircraft, the control method includes a fixed-wing mode, a tilt transition mode, and a helicopter mode.
[0062] Fixed-wing mode (e.g.) Figures 1-3 Under these conditions, each tilt rotor is controlled by its tilt control mechanism to remain in a vertical position;
[0063] Tilting transition mode (e.g.) Figures 4-6 Under these conditions, each tilt rotor is controlled by its tilt control mechanism to maintain a certain angular velocity;
[0064] Helicopter mode (e.g.) Figures 7-9 Under these conditions, each tilt rotor is controlled by its tilt control mechanism to remain in a horizontal position;
[0065] The control method also includes yaw control in fixed-wing and / or helicopter modes. Each tilt rotor is controlled by its tilt control mechanism to yaw within a preset angle range, with the preset angle not exceeding 10 degrees, i.e., a small yaw (distinct from the large yaw in the tilt transition mode). This can be achieved by controlling the tilt rotors through the tilt control mechanism, or optionally by controlling the tail fin's control surfaces, the tilt rotor's motor output, etc. When yawing to the left, the tilt rotor on the left side of the fuselage tilts backward, while the tilt rotor on the right side tilts slightly (i.e., a few degrees) forward; when yawing to the right, the tilt rotor on the left side of the fuselage tilts forward, while the tilt rotor on the right side tilts slightly backward.
[0066] The above modes can be applied individually or in combination. The flight control system of the aircraft of the present embodiment includes control surfaces of ailerons, rudders and elevators of wings, and blades and tilt control mechanisms of tilt rotors, to achieve control in the corresponding modes.
[0067] Specifically, as an example, the four tilt rotors are in a vertical state under the drive of the respective tilt control mechanisms, at this time, the tilt rotors of the second tilt rotor pair rotate to generate a force pulling the aircraft forward, the tilt rotors of the first tilt rotor pair rotate to generate a force pushing the aircraft backward, and the state control of the aircraft is achieved through ailerons, rudders, and elevators.
[0068] When the aircraft needs to be converted from the fixed-wing mode to the helicopter mode, the tilt rotors of the second tilt rotor pair are tilted upward, the tilt rotors of the first tilt rotor pair are tilted downward, the four tilt rotors are tilted synchronously, and the angular velocity of the tilt is consistent, which is the tilt transition mode. During this process, the tilt rotors of the second tilt rotor pair pull the aircraft forward by generating a forward component force through rotation, the tilt rotors of the first tilt rotor pair push the aircraft backward by generating a backward component force through rotation, part of the state control of the aircraft is consistent with that when it is in the fixed-wing mode, and is achieved through ailerons, rudders, and elevators, and the other part provides a certain state control ability through the speed difference of the four tilt rotors. The proportion of the two parts of the aircraft state control is automatically allocated by the control system (or the control module described below) of the aircraft according to the overall tilt angle of the aircraft and the tilt angle of the four tilt rotors, at this time, the state control of the aircraft is in a mixed control mode.
[0069] When the aircraft needs to be converted from the helicopter mode to the fixed-wing mode, the tilt rotors of the second tilt rotor pair and the tilt rotors of the first tilt rotor pair are driven in the opposite directions as described above, respectively.
[0070] When the aircraft is in the helicopter mode, the four tilt rotors are driven to be in a horizontal state, at this time, the four tilt rotors all rotate to generate an upward lift, so that the aircraft can achieve hovering in the air and vertical take-off and landing, and the state control of the aircraft is completely achieved through the speed difference of the four tilt rotors. At the same time, by controlling the tilt control mechanisms of the four tilt rotors to make the four tilt rotors produce small-amplitude symmetrical differential tilt, the state control of the aircraft yaw can be achieved.
[0071] Specifically, when the aircraft is yawing in the fixed-wing mode and / or the helicopter mode: taking the helicopter mode as an example, when the aircraft needs to yaw to the left, the left tilt-rotor of the second pair of tilt-rotors is slightly tilted backward (the tilt angle is controlled by the tilt control mechanism to be 2-3 degrees), the right tilt-rotor of the second pair of tilt-rotors is slightly tilted backward, the left tilt-rotor of the first pair of tilt-rotors is slightly tilted forward, and the right tilt-rotor of the first pair of tilt-rotors is slightly tilted forward, so that two horizontal backward components are generated on the left side, and two horizontal backward components are generated on the right side; the four tilt-rotors are synchronously differentially tilted, so that the entire aircraft obtains a counterclockwise moment, thereby realizing yawing to the left.
[0072] When the aircraft needs to yaw to the right, the tilt-rotors are driven in the opposite direction as described above.
[0073] In a preferred embodiment, the aircraft described above can further be provided with a control module and a sensor assembly; specifically, various sensors including but not limited to an inertial measurement unit, a global positioning system, an air pressure sensor, a visual sensor (collecting environmental information), etc. can be integrated, the control module collects flight information (including but not limited to the attitude, position, speed, etc. of the aircraft) in real time through the sensor assembly, and dynamically optimizes the control parameters of each tilt-rotor in real time according to the flight information. Specifically, as an example, the control parameters of the tilt-rotors can be optimized according to the tilt angle of the entire aircraft and the tilt angles of the four tilt-rotors.
[0074] In addition, the dynamic optimization of the control parameters of each tilt-rotor can also be achieved by loading algorithms on the control module, such as attitude control algorithms, such as PID control algorithms, complementary filtering algorithms; fusing data from multiple sensors to obtain accurate attitude information of the aircraft; path planning algorithms, which find an optimal path from the starting point to the target point in the search space by evaluating the cost function of each node (including the actual cost from the starting point to the current node and the estimated cost from the current node to the target point), obtain a preset path, and autonomously configure the control parameters of each tilt-rotor; obstacle avoidance algorithms, trajectory tracking algorithms, etc., which predict the state of the aircraft in the future by establishing a dynamic model of the aircraft, and optimize the control parameters of the control tilt-rotors according to the target trajectory and the current state, so that the aircraft can track the target trajectory as accurately as possible, etc., thereby being applied in different scenarios.
[0075] Based on the above control method, the dynamic control of the aircraft with the above stacked tilt-rotor structure is realized, the efficiency in the hovering state and the fixed-wing cruising state of the multi-rotor machine is considered, all the rotors are controlled differently in any state, the power system of the whole aircraft is always in a high-efficiency state, the aircraft has a simple structure and forms a stacked structure, which is beneficial to reduce the structural weight and overall aerodynamic performance of the aircraft, the double-wing design has a larger wing area, thereby obtaining a larger lift, reducing the wing span size of the aircraft, and being suitable for a narrower take-off site, being convenient to arrange and applied to various rotor systems, ensuring that the aircraft has a larger rotor disc area and a lower rotor disc load, having abundant power output and excellent flight performance in improving hovering and vertical take-off.
[0076] It should be noted that the embodiments of the present application have better implementation, and do not limit the present application in any form, any skilled person in the art can change or modify the equivalent effective embodiments by using the disclosed technical content, as long as it does not deviate from the technical scheme of the present application, any modification or equivalent change and modification of the above embodiments according to the technical essence of the present application still belongs to the scope of the technical scheme of the present application.
Claims
1. An aircraft with a stacked tiltrotor structure, characterized in that: This includes the fuselage, wings, tail, landing gear, and tiltrotor assembly; The wing includes a first wing and a second wing arranged side by side along the height of the fuselage, wherein the first wing is higher than the second wing; The tilt rotor assembly includes a first tilt rotor pair and a second tilt rotor pair, wherein the first tilt rotor pair and the second tilt rotor pair each include at least two tilt rotors; The first tiltrotor pair and the second tiltrotor pair are arranged correspondingly and connected to the first wing and the second wing respectively; The tilt rotors of the first tilt rotor pair and the tilt rotors of the second tilt rotor pair extend out of the wings in directions that are relatively opposite to each other, so as to form airflow paths that are stacked in front of and behind the fuselage.
2. The aircraft according to claim 1, characterized in that: The tilt rotors of the first tilt rotor pair are symmetrically located on the first wing along the fuselage; The tilt rotors of the second tilt rotor pair are located vertically on the second wing, corresponding to the tilt rotors of the first tilt rotor pair.
3. The aircraft according to claim 1, characterized in that: The tilt rotors of the first tilt rotor pair extend to the rear of the first wing; The tilt rotor of the second tilt rotor pair extends to the front of the second wing.
4. The aircraft according to claim 1, characterized in that: The tilt rotor includes a support rod, a tilt control mechanism, a motor, and blades; The blades on the first tiltrotor pair and the second tiltrotor pair are equidistant from the centerline of the wing.
5. The aircraft according to claim 4, characterized in that: The motor and blades of the first tilt rotor pair are controlled by their tilt control mechanism to rotate within a 90° range toward the direction of the second wing; The motor and blades of the second tilt rotor pair are controlled by their tilt control mechanism to rotate within a 90° range toward the direction of the first wing.
6. The aircraft according to claim 4, characterized in that: The support rod on the tilt rotor extends beyond the wing portion by a length exceeding the length of the blades.
7. The aircraft according to claim 4, characterized in that: The distance between the support rod and the fuselage exceeds the length of the propeller blade.
8. The aircraft according to claim 1, characterized in that: The first wing and / or the second wing each include a main wing and two ailerons connected to the sides of the main wing; The aileron is located behind the main wing, and the tilt rotor extends along the edge of the main wing away from the fuselage to the tilt rotor.
9. The aircraft according to claim 1, characterized in that: The tail fin includes a vertical tail fin and horizontal tail fins located on either side of the vertical tail fin.
10. The aircraft according to claim 1, characterized in that: It also includes a control module and sensor components; The control module collects flight information in real time through the sensor components and dynamically optimizes the control parameters of each tilt rotor based on the flight information.