Multi-attitude duct and aircraft

Abstract

The multi-attitude duct comprises a duct ring body, a power propeller is erected in the duct ring body, and a telescopic turbulent flow assembly is arranged on the inner wall of the duct ring body; the telescopic turbulent flow assembly comprises a sliding groove and a turbulent flow plate. A sliding groove is formed in the inner wall of the duct ring body, a spoiler is arranged in the sliding groove in a sliding mode, and the duct ring body is connected with the spoiler through a linear moving mechanism. According to the telescopic turbulent flow assembly, in the single-duct aircraft, the local flow field in the single duct is changed through the telescopic turbulent flow plate, then the local lift force in a single-duct system is changed, and finally the single duct has the vector action function. The telescopic turbulent flow assembly can be used in a multi-duct aircraft in a linkage mode, and the vector action and the flight attitude of the whole aircraft are changed.

Description

Technical Field

[0001] This utility model relates to the field of flight equipment technology, specifically a multi-attitude duct and aircraft. Background Technology

[0002] Conventional ducted systems cannot perform multi-dimensional, multi-attitude control of the duct itself during use. This patent enables the ducted system to provide multi-dimensional, multi-attitude motion control in addition to simply providing power output to the equipment it carries. Utility Model Content

[0003] To address the aforementioned deficiencies in existing technologies, the purpose of this invention is to provide a multi-attitude duct and aircraft, which adds retractable spoilers in multiple directions at the minimum diameter within the duct ring and adds vector control surfaces at the rear end of the duct support arm.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] On the one hand, this utility model provides a multi-attitude duct, including a duct ring, a power propeller mounted inside the duct ring, and a telescopic turbulence-disrupting component installed on the inner wall of the duct ring.

[0006] Furthermore, the telescopic spoiler assembly is located at the point of minimum inner diameter of the duct ring;

[0007] Specifically, the telescopic spoiler assembly includes a chute and a spoiler. The chute is provided on the inner wall of the duct ring, and the spoiler is slidably disposed in the chute. The duct ring and the spoiler are connected by a linear movement mechanism.

[0008] Furthermore, at least two sets of the telescopic spoiler assembly are provided, the spoiler is an arc-shaped plate, and after the spoiler is retracted into the groove, it is smooth and unobstructed with the inner wall of the duct ring. The linear movement mechanism is connected to the symmetrical line of the spoiler, and the end faces of adjacent spoilers are arranged in parallel.

[0009] Furthermore, ribs are provided inside the duct ring between every two spoilers.

[0010] Secondly, this utility model provides an aircraft, including the multi-attitude duct described in one aspect.

[0011] Furthermore, one duct ring is provided, and at least two sets of telescopic spoiler components are provided, which are evenly distributed along the circumference of the duct ring.

[0012] Furthermore, at least two duct rings are provided, and at least two sets of telescopic spoiler components are provided in each duct ring, with all telescopic spoiler components being symmetrically distributed.

[0013] Furthermore, the power propeller includes a stator, a rotor, and blades;

[0014] Specifically, a support arm is provided between the outer wall of the stator and the inner wall of the duct ring, the rotor is rotatably disposed in the stator, the upper end of the rotor is connected to the blade, and a vector control surface is provided directly below the support arm;

[0015] Specifically, the telescopic spoiler assembly is located below the blade, the telescopic spoiler assembly is located at the smallest inner diameter of the duct ring, the telescopic spoiler assembly is located above the support arm, or the telescopic spoiler assembly is flush with the support arm.

[0016] Specifically, at least two support arms are provided and are evenly distributed along the circumference of the duct ring.

[0017] Specifically, the vector control surface is connected to the inner wall of the duct ring via a servo motor, and the vector control surface is connected to the outer wall of the stator via a servo motor.

[0018] Furthermore, one duct ring is provided, and at least two vector control surfaces are provided, which are evenly distributed along the circumference of the duct ring.

[0019] Furthermore, at least two duct rings are provided in each duct ring, and at least one vector control surface is provided below a support arm, with all vector control surfaces symmetrically distributed.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] 1. The telescopic spoiler assembly of this invention, in a single-duct aircraft, alters the local flow field within the single duct by retracting the spoiler, thereby changing the local lift within the single-duct system and ultimately enabling the single duct to perform vector maneuvering. In a multi-duct aircraft, the telescopic spoiler assembly of this invention changes the lift of each duct, altering the overall vector maneuvering and flight attitude of the aircraft.

[0022] 2. This utility model integrates the spoiler system and the control surface system into a unified design and coordinated control, thereby making the ducted jet and ducted aircraft more controllable. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of a multi-position duct of this utility model;

[0024] Figure 2 This is a schematic diagram of the internal structure of a single duct in the application of a multi-position duct according to this utility model.

[0025] Figure 3 This is a schematic diagram of the retracted spoiler in this utility model;

[0026] Figure 4This is a schematic diagram of the extended spoiler in this utility model;

[0027] Figure 5 This is a top view of the present invention in a single-duct application when it undergoes rolling motion via a spoiler.

[0028] Figure 6 This is a schematic diagram of the flow field when the present invention undergoes rolling motion using a spoiler in a single-duct application.

[0029] Figure 7 This is a top view of the present invention in a multi-duct application when it undergoes rolling motion via a spoiler;

[0030] Figure 8 This is a top view of the present invention when it moves forward using a spoiler in a multi-duct application;

[0031] Figure 9 This is a schematic diagram of the flow field when the present invention is used in a multi-duct application to achieve rolling or forward motion through a spoiler.

[0032] Figure 10 This utility model provides a top view and an internal structural schematic diagram of a single duct with a multi-position duct.

[0033] Figure 11 This is a schematic diagram of the zero-position state vector control surface in this utility model;

[0034] Figure 12 This is a schematic diagram of the steering state vector control surface in this utility model;

[0035] Figure 13 This is a schematic diagram of the flow field when the present invention performs steering motion using vector control surfaces in a single-duct application;

[0036] Figure 14 This is a top view of the present invention when it is used for steering motion via vector control surfaces in a single-duct application;

[0037] Figure 15 This is a schematic diagram of the distribution of vector control surfaces in a multi-duct application of this utility model;

[0038] Figure 16 This is a top view of the present invention when performing steering maneuvers using vector rudder surfaces in a multi-duct application.

[0039] Figure 17 This is a schematic diagram of the coordinated operation of the spoiler and vector control surface in a single-duct application of this utility model;

[0040] Figure 18 This is a schematic diagram of the arrangement of the linear motion mechanism in this utility model.

[0041] In the diagram: 1. Ductwork; 2. Power propeller; 2.1. Stator; 2.2. Rotor; 2.3. Blade; 3. Slide; 4. Spoiler; 4.1. Spoiler in retracted state; 4.2. Spoiler in extended state; 5. Linear movement mechanism; 5.1. Power guide; 5.2. Telescopic rod; 5.3. Connecting rod; 5.4. Equipment cavity; 5.5. Guide slot; 6. Support arm; 7. Vector control surface; 7.1. Vector control surface in zero position; 7.2. Vector control surface in steering state. Detailed Implementation

[0042] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0043] Example 1: Please refer to Figures 1 to 18 This embodiment provides a multi-attitude duct, including a duct ring 1, a power propeller 2 mounted inside the duct ring 1, and a telescopic turbulence component provided on the inner wall of the duct ring 1.

[0044] Specifically, the telescopic spoiler assembly includes a groove 3 and a spoiler 4. The inner wall of the duct ring 1 is provided with a groove 3, and the spoiler 4 is slidably disposed in the groove 3. The duct ring 1 and the spoiler 4 are connected by a linear movement mechanism 5.

[0045] Specifically, at least two sets of telescopic spoiler components are provided. The spoiler plate 4 is an arc-shaped plate, and after the spoiler plate 4 is retracted into the sliding groove 3, it is smooth and unobstructed with the inner wall of the duct ring 1. The linear movement mechanism 5 is connected to the symmetry line of the spoiler plate 4. The end faces of adjacent spoiler plates 4 are arranged in parallel. The more telescopic spoiler components are provided, the smaller the distance difference generated by the movement of the spoiler plate 4 from the symmetry line and the two ends towards the center will be during the movement.

[0046] Specifically, ribs are provided inside the duct ring 1 between every two spoilers 4 to strengthen the duct ring 1.

[0047] Specifically, such as Figure 2 As shown, the telescopic spoiler component is located at the minimum inner diameter of the duct ring 1 to improve the influence of the telescopic spoiler component on the airflow.

[0048] Specifically, such as Figure 18As shown, the linear movement mechanism 5 includes a power guide body 5.1 and a telescopic rod 5.2. An equipment cavity 5.4 is provided inside the duct ring 1. The equipment cavity 5.4 overlaps with the slide groove 3. The equipment cavity 5.4 and the slide groove 3 are connected at the overlapping part through a guide slot 5.5. A connecting rod 5.3 is provided inside the guide slot 5.5. The connecting rod 5.3 is connected to the spoiler 4 and the telescopic rod 5.2. The power guide body 5.1 is bolted to one end of the equipment cavity 5.4 away from the guide slot 5.5. The power guide body 5.1 drives the telescopic rod 5.2 to move linearly, causing the spoiler 4 to extend or retract.

[0049] Preferably, the linear movement mechanism 5 is a linear motor, and the moving shaft of the linear motor is a telescopic rod 5.2, which is connected to the spoiler 4 through a connecting rod 5.3; or the linear movement mechanism 5 is a hydraulic cylinder, and the piston rod of the hydraulic cylinder is a telescopic rod 5.2, which is connected to the spoiler 4 through a connecting rod 5.3.

[0050] The basic principle of this embodiment is that the extension and retraction of the spoiler 4 changes the local duct inner diameter. By reducing the duct inner diameter without changing the propeller speed, the flow rate in the local duct is reduced. The lack of flow rate will reduce the lift (thrust) in the blocked area. The local thrust reduction will cause the duct to yaw towards the blocked area, thereby causing the aircraft to change its operating attitude.

[0051] All aircraft require overall balance configuration while in a suspended (level flight) state. Conventional aircraft need to adjust the speed of the propeller blades in each direction, but propellers with certain fixed speeds cannot effectively adjust the aircraft's attitude. This spoiler 4 changes the lift of each duct by rapidly and frequently extending and retracting, thereby changing the aircraft's operating attitude through the different lift of each duct.

[0052] Example 2: Based on Example 1, such as Figure 5 As shown, in a single-duct aircraft, at least two sets of the telescopic spoiler components are provided and are evenly distributed along the circumference of the duct body 1.

[0053] Take a single-ducted aircraft with eight telescopic spoiler components as an example:

[0054] In a single-ducted duct aircraft, spoilers 4 are distributed at multiple points and operate independently. For example... Figure 5 , Figure 6 As shown, in a single-duct system, some of the spoilers 4 are retracted inward, reducing the flow field in the duct at the corresponding position, which reduces the lift on one side of the duct, thereby causing the duct to roll (tilt) in an attitude.

[0055] Example 3: Based on Example 1, such as Figure 7As shown, in a multi-duct aircraft, at least two sets of telescopic spoiler components are provided in each duct ring 1, and all telescopic spoiler components are symmetrically distributed.

[0056] Telescopic spoilers can be designed throughout the entire duct in 360° direction, but depending on efficiency, some locations can be omitted. Locations with lower efficiency can be left undesigned. For example... Figure 7 As shown, no telescopic spoiler components are installed near the connecting frame of the two duct rings 1.

[0057] Taking a multi-ducted aircraft with two ducted coils 1, each containing six telescopic spoiler components, and without any telescopic spoiler components near the connecting frame of the ducted coils 1 as an example, its working principle is as follows:

[0058] Inside a multi-ducted aircraft, spoilers 4 are distributed at multiple points and move in unison. For example... Figure 7 , Figure 8 As shown, in a multi-duct system, the local spoiler 4 is retracted to reduce the flow field inside the duct at the corresponding location, causing the duct to drive the entire system to roll and move forward.

[0059] Roll control, such as Figure 7 As shown: the left / right spoilers of the aircraft duct relative to the direction of travel can be extended as needed to reduce the side lift of the aircraft, thereby enabling the aircraft to roll.

[0060] Forward control, such as Figure 8 As shown: When the aircraft needs to move forward, the ducted spoiler at the front of the aircraft moves according to the usage requirements, changing the duct lift and causing the aircraft to tilt forward. This, in turn, produces a forward flight maneuver.

[0061] Another implementation of this embodiment, such as Figure 9 As shown, the telescopic spoiler components in each duct ring 1 are evenly distributed circumferentially. By extending the left / right spoilers of the aircraft relative to the direction of travel as required, the side lift of the aircraft is changed, thereby enabling the aircraft to roll or move forward.

[0062] Example 4: Based on Example 1, in this example, the propeller 2 includes a stator 2.1, a rotor 2.2, and blades 2.3. A support arm 6 is provided between the outer wall of the stator 2.1 and the inner wall of the duct ring 1. The rotor 2.2 is rotatably mounted in the stator 2.1. The upper end of the rotor 2.2 is connected to the blades 2.3. A vector control surface 7 is provided directly below the support arm 6. The vector control surface 7 can be swung by a servo motor. The function of the vector control surface 7 is to change the slipstream direction at the tail of the duct, thereby changing the direction of the slipstream output flow field of the duct system, and thus enabling the duct and the equipment carrying the duct to perform left and right turning actions.

[0063] Specifically, the telescopic spoiler assembly is located below the blade 2.3, the telescopic spoiler assembly is set at the smallest inner diameter of the duct ring 1, the telescopic spoiler assembly is flush with the support arm 6, or the telescopic spoiler assembly is located above the support arm 6.

[0064] Specifically, the vector control surface 7 is connected to the inner wall of the duct coil 1 via a servo motor, and the vector control surface 7 is connected to the outer wall of the stator 2.1 via a servo motor. It should be noted that the connection method and control method of the servo motor are existing technologies, so they will not be described in detail here.

[0065] Specifically, at least two support arms 6 are provided and are evenly distributed around the circumference of the duct ring 1.

[0066] Example 5: Based on the combination of Example 2 and Example 4, such as... Figure 10 As shown, in a single-duct aircraft, at least two vector control surfaces 7 are provided and are evenly distributed along the circumference of the duct body 1.

[0067] Taking a single-ducted jet aircraft with eight support arms 6 and four vector control surfaces 7 as an example, its working principle is as follows:

[0068] like Figure 13 , Figure 14 As shown, when the single-duct system is in use, the vector control surface moves independently, enabling the duct to perform actions such as turning; the oscillation of the vector control surface 7 affects the flow direction of the slipstream at the tail of the duct, and thus affects the running direction of the entire duct and its aircraft.

[0069] A simple vector control surface 7 can only change the direction of the slipstream at the tail end of the duct. To make the duct more functional, such as Figure 17 As shown, the telescopic spoiler and the vector control surface 7 are integrated into the design and linked for control, thereby making the ducted jet and ducted aircraft more controllable.

[0070] The telescopic spoiler is linked with the vector control surface 7, which originally only had the single function of changing the direction of the flow field. It has been expanded to include an overall tilting function, making the aircraft's attitude more controllable.

[0071] Example 6: Based on the combination of Examples 3 and 4, such as... Figure 15 As shown, in a multi-ducted aircraft, at least one vector control surface 7 is provided below a support arm 6 in each duct ring 1, and all vector control surfaces 7 are symmetrically distributed.

[0072] Taking a multi-ducted aircraft with one vector control surface 7 inside each ducted coil 1 as an example, its working principle is as follows:

[0073] like Figure 15 , Figure 16As shown, in a multi-duct system, each duct can carry only one control surface. When the vector control surface is working in a multi-duct system, each control surface moves independently, causing the duct to produce a steering action.

[0074] All components not discussed in detail in this application, as well as the connection methods of these components, are well-known technologies in this field. They can be directly applied and will not be elaborated further.

[0075] In this utility model, the term "multiple" refers to two or more unless otherwise explicitly defined. The terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; "linking" can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0076] In the description of this utility model, it should be understood that the terms "upper", "lower", "left", "right", "front", "rear", 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 unit 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.

[0077] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0078] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A multi-position duct, comprising a duct coil, characterized in that, A powered propeller is mounted inside the duct ring, and a telescopic turbulence-disrupting component is installed on the inner wall of the duct ring.

2. The multi-attitude duct according to claim 1, characterized in that, The telescopic spoiler assembly is located at the minimum inner diameter of the culvert ring. The telescopic spoiler assembly includes a chute and a spoiler plate. The chute is provided on the inner wall of the duct ring, and the spoiler plate is slidably disposed in the chute. The duct ring and the spoiler plate are connected by a linear movement mechanism.

3. A multi-attitude duct according to claim 2, characterized in that, At least two sets of the telescopic spoiler components are provided. The spoiler is an arc-shaped plate, and after the spoiler is retracted into the groove, it is smooth and flush with the inner wall of the duct ring. The linear movement mechanism is connected to the symmetrical line of the spoiler, and the end faces of adjacent spoilers are arranged in parallel.

4. A multi-attitude duct according to claim 3, characterized in that, The duct ring has ribs between every two spoilers inside.

5. An aircraft, characterized in that, Includes the multi-position duct described in claim 1.

6. An aircraft according to claim 5, characterized in that, One duct ring is provided, and at least two sets of telescopic spoiler components are provided, which are evenly distributed along the circumference of the duct ring.

7. An aircraft according to claim 5, characterized in that, At least two duct rings are provided, and at least two sets of telescopic spoiler components are provided in each duct ring. All telescopic spoiler components are symmetrically distributed.

8. An aircraft according to claim 5, characterized in that, The power propeller includes a stator, a rotor, and blades; A support arm is provided between the outer wall of the stator and the inner wall of the duct ring. The rotor is rotatably mounted in the stator. The upper end of the rotor is connected to the blade. A vector control surface is provided directly below the support arm. The telescopic spoiler assembly is located below the blade, the telescopic spoiler assembly is located at the smallest inner diameter of the duct ring, the telescopic spoiler assembly is located above the support arm, or the telescopic spoiler assembly is flush with the support arm. At least two support arms are provided and are evenly distributed along the circumference of the duct ring. The vector control surface is connected to the inner wall of the duct ring via a servo motor, and the vector control surface is connected to the outer wall of the stator via a servo motor.

9. An aircraft according to claim 8, characterized in that, One duct ring is provided, and at least two vector control surfaces are provided, which are evenly distributed along the circumference of the duct ring.

10. An aircraft according to claim 8, characterized in that, The duct ring is provided in at least two parts. In each duct ring, at least one vector control surface is provided below a support arm, and all vector control surfaces are symmetrically distributed.

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