Multi-attitude duct control system and aircraft

Abstract

The invention discloses a multi-attitude duct control system and an aircraft, the multi-attitude duct control system 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 spoiler assembly, in the single-duct aircraft, the local flow field in the single duct is changed through the telescopic spoiler, 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] The present invention relates to the technical field of flight equipment, in particular to a multi-attitude ducted control system and an aircraft. Background Art

[0002] Conventional duct systems cannot perform multi-dimensional and multi-posture control on the duct body itself during use. This patent enables the duct system to provide multi-dimensional and multi-posture motion control in addition to simply providing power output for the equipment it carries. Summary of the invention

[0003] In view of the above-mentioned defects in the prior art, the purpose of the present invention is to provide a multi-attitude duct control system and an aircraft, adding retractable spoilers in multiple directions at the minimum diameter inside the duct body, and adding vector control surfaces at the rear end of the duct support arm.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions: On the one hand, the present invention provides a multi-attitude duct control system, including a duct body, wherein a power propeller is installed inside the duct body, and a telescopic spoiler assembly is arranged on the inner wall of the duct body.

[0005] Furthermore, the telescopic spoiler assembly is arranged at the location where the inner diameter of the duct ring is the smallest; Specifically, the telescopic spoiler assembly includes a slide groove and a spoiler plate. The slide groove is arranged on the inner wall of the duct ring body. The spoiler plate is slidably arranged in the slide groove. The duct ring body and the spoiler plate are connected by a linear moving mechanism.

[0006] Furthermore, at least two groups of the telescopic spoiler components are provided, the spoiler is an arc-shaped plate, and after the spoiler is retracted into the slide groove, it is smoothly connected to the inner wall of the duct ring body, the linear moving mechanism is connected to the symmetry line of the spoiler, and adjacent spoiler end faces are arranged in parallel.

[0007] Furthermore, a rib is arranged between every two spoilers inside the duct body.

[0008] In a second aspect, the present invention provides an aircraft, comprising a multi-attitude ducted control system as described in the first aspect.

[0009] Furthermore, one duct body is provided, and at least two groups of telescopic spoiler components are provided and are evenly distributed along the circumference of the duct body.

[0010] Furthermore, at least two duct ring bodies are provided, at least two groups of telescopic spoiler components are provided in each duct ring body, and all the telescopic spoiler components are symmetrically distributed.

[0011] Furthermore, the power propeller includes a stator, a rotor, and blades; Specifically, a support arm is arranged between the outer wall of the stator and the inner wall of the duct ring, the rotor is rotatably arranged in the stator, the upper end of the rotor is connected to the blade, and a vector control surface is arranged directly below the support arm; 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; Specifically, at least two support arms are provided and are evenly distributed along the circumference of the duct body; Specifically, the vector control surface is connected to the inner wall of the duct ring through the steering gear, and the vector control surface is connected to the outer wall of the stator through the steering gear.

[0012] Furthermore, one duct body is provided, and at least two vector control surfaces are provided and are evenly distributed along the circumference of the duct body.

[0013] Furthermore, at least two duct ring bodies are provided, and in each duct ring body, a vector rudder surface is provided under at least one support arm, and all the vector rudder surfaces are symmetrically distributed.

[0014] Compared with the prior art, the present invention has the following beneficial effects: 1. The telescopic spoiler assembly provided by the present invention changes the local flow field in the single duct through the telescopic spoiler in a single duct aircraft, thereby changing the local lift in the single duct system, and finally making the single duct have a vector action function. The telescopic spoiler assembly provided by the present invention changes the lift of each duct in a multi-duct aircraft, changes the vector action and flight attitude of the entire aircraft.

[0015] 2. The present invention integrates the spoiler system and the control surface system for linkage control, thereby making the duct and the ducted aircraft more controllable. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of a multi-attitude ducted control system of the present invention; Figure 2 It is a schematic diagram of the internal structure of a single duct application of a multi-attitude duct control system of the present invention; Figure 3 is a schematic diagram of a spoiler in a retracted state in the present invention; Figure 4 is a schematic diagram of a spoiler in an extended state in the present invention; Figure 5 is a top view of the present invention in a single duct application when the spoiler performs a rolling motion; Figure 6 is a schematic diagram of the flow field when the present invention performs rolling motion through the spoiler in a single duct application; Figure 7is a top view of the present invention in a multi-duct application when the spoiler performs a rolling motion; Figure 8 is a top view of the present invention in a multi-duct application while in forward motion through a spoiler; Fig. 9 is a schematic diagram of the flow field of the present invention when the spoiler performs rolling or forward motion in a multi-duct application; Fig.10 It is a bottom view and internal structure schematic diagram of a single duct application of a multi-attitude duct control system of the present invention; Fig.11 It is a schematic diagram of the zero-position state vector control surface in the present invention; Fig.12 It is a schematic diagram of the steering state vector control surface in the present invention; Fig.13 It is a schematic diagram of the flow field when the present invention performs steering motion through the vector control surface in a single duct application; Fig.14 is a top view of the present invention when performing a steering motion through a vector control surface in a single duct application; Fig.15 It is a schematic diagram of the distribution of vector control surfaces in multi-duct applications of the present invention; Fig.16 It is a top view of the present invention when performing a steering action through a vector control surface in a multi-duct application.

[0017] Fig.17 It is a schematic diagram of the coordinated operation of the spoiler and the vector control surface in the single duct application of the present invention; Fig.18 It is a schematic diagram of the arrangement of the linear motion mechanism in the present invention.

[0018] In the figure: duct body 1, power propeller 2, stator 2.1, rotor 2.2, blade 2.3, slide 3, spoiler 4, spoiler 4.1 in retracted state, spoiler 4.2 in extended state, linear moving mechanism 5, power guide body 5.1, telescopic rod 5.2, connecting rod 5.3, equipment cavity 5.4, guide notch 5.5, support arm 6, vector rudder surface 7, vector rudder surface 7.1 in zero position state, vector rudder surface 7.2 in steering state. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] Example 1: Please refer to Figures 1 to 18 The present embodiment provides a multi-attitude duct control system, comprising a duct body 1, a power propeller 2 is installed inside the duct body 1, and a telescopic spoiler component is arranged on the inner wall of the duct body 1.

[0021] Specifically, the telescopic spoiler assembly includes a slide groove 3 and a spoiler plate 4. The slide groove 3 is arranged on the inner wall of the duct ring body 1. The spoiler plate 4 is slidably arranged in the slide groove 3. The duct ring body 1 and the spoiler plate 4 are connected by a linear moving mechanism 5.

[0022] Specifically, at least two groups of the telescopic spoiler components are provided, the spoiler 4 is an arc-shaped plate, and after the spoiler 4 is retracted into the slide groove 3, it is smoothly connected to the inner wall of the duct ring body 1, the linear moving mechanism 5 is connected to the symmetry line of the spoiler 4, and the adjacent end faces of the spoiler 4 are arranged in parallel. The more telescopic spoiler components are provided, the smaller the distance difference between the symmetry line and the two ends moving toward the center will be during the movement of the spoiler 4.

[0023] Specifically, a rib is arranged between every two spoilers 4 inside the duct body 1 to enhance the strength of the duct body 1 .

[0024] Specifically, Figure 2 As shown, the telescopic spoiler assembly is arranged at the smallest inner diameter of the duct ring body 1 to increase the influence of the telescopic spoiler assembly on the airflow.

[0025] Specifically, Fig.18 As shown, the linear motion mechanism 5 includes a power guide body 5.1 and a telescopic rod 5.2. An equipment cavity 5.4 is arranged in the duct ring body 1. The equipment cavity 5.4 has an overlapping portion with the slide groove 3. The equipment cavity 5.4 is connected with the slide groove 3 through a guide slot 5.5 at the overlapping portion. A connecting rod 5.3 is arranged in the guide slot 5.5. The connecting rod 5.3 is connected to the spoiler 4. The connecting rod 5.3 is connected to the telescopic rod 5.2. The power guide body 5.1 is arranged at one end of the equipment cavity 5.4 away from the guide slot 5.5 by a bolt. The telescopic rod 5.2 is driven by the power guide body 5.1 to move linearly, so that the spoiler 4 is extended or retracted.

[0026] Preferably, the linear moving mechanism 5 is a linear motor, the moving axis 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 moving mechanism 5 is a hydraulic cylinder, 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.

[0027] The basic working principle of this embodiment is as follows: the role of the extension and retraction of the spoiler 4 is to change the inner diameter of the local duct. By not changing the propeller speed, only the inner diameter of the duct is reduced, thereby reducing the local flow field flow in the duct. The lack of flow field flow will cause the lift (thrust) of the blocked area to decrease. The local thrust reduction will cause the duct body to produce a yaw attitude toward the blocked part, thereby driving the aircraft to change its operating attitude.

[0028] Any aircraft needs to be balanced and configured in the suspended (level flight) state. Conventional aircraft need to adjust the blade speed in each direction, but some fixed speed propellers cannot effectively adjust the aircraft attitude. This spoiler 4 changes the lift of each duct through rapid and frequent extension and retraction, and then changes the aircraft's operating attitude through the different lift of each duct.

[0029] Example 2: Based on Example 1, Figure 5 As shown, in a single ducted aircraft, at least two groups of the telescopic spoiler components are provided and are evenly distributed along the circumference of the duct ring body 1.

[0030] Take a single ducted aircraft with eight retractable spoiler components as an example: In a single ducted aircraft, the spoiler 4 is divided into multiple locations and moves independently. Figure 5 , Figure 6 As shown, in a single duct system, part of the spoiler 4 is retracted to reduce the flow field in the duct at the corresponding position, thereby reducing the lift on one side of the duct, thereby causing the duct to produce a rolling (tilting) posture.

[0031] Embodiment 3: Based on embodiment 1, Figure 7 As shown, in a multi-ducted aircraft, at least two groups of telescopic spoiler components are arranged in each duct ring body 1, and all the telescopic spoiler components are symmetrically distributed.

[0032] The entire duct can be designed with telescopic spoiler components in 360° directions, but some positions can be omitted according to different efficiencies. Positions with relatively low efficiency do not need to be set. Figure 7 As shown, no telescopic spoiler assembly is provided at the position of the two duct ring bodies 1 near the connecting frame.

[0033] Taking a multi-ducted aircraft with two ducted bodies 1, six telescopic spoiler assemblies in each ducted body 1, and no telescopic spoiler assembly at the position of the ducted body 1 near the connecting frame as an example, its working principle is as follows: In a multi-duct aircraft, the spoiler 4 will be divided into multiple locations and move in a coordinated manner. Figure 7 , Figure 8 As shown, in the multi-duct system, the local spoiler 4 is retracted to reduce the flow field in the duct at the corresponding position, so that the duct drives the entire system to produce a rolling and forward posture.

[0034] Roll control, such as Figure 7 As shown: the left / right side spoiler of the aircraft duct relative to the direction of travel can be extended according to usage requirements to reduce the side lift of the aircraft, thereby making the aircraft roll.

[0035] Forward control, such as Figure 8 As shown: When the aircraft needs to move forward, the duct spoiler in front of the aircraft moves according to the use requirements, changing the duct lift and making the aircraft tilt forward, thereby generating forward flight action.

[0036] Another implementation of this embodiment is as follows: Fig. 9 As shown, the retractable spoiler components in each duct ring body 1 are evenly distributed along the circumference, and the left / right side spoilers relative to the direction of travel of the aircraft are extended according to usage requirements to change the side lift of the aircraft, thereby causing the aircraft to roll or move forward.

[0037] Embodiment 4: Based on Embodiment 1, in this embodiment, the power propeller 2 includes a stator 2.1, a rotor 2.2, and blades 2.3. A support arm 6 is arranged between the outer wall of the stator 2.1 and the inner wall of the duct ring body 1. The rotor 2.2 is rotatably arranged 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 arranged directly below the support arm 6, and the vector control surface 7 can be swung by the steering gear. The function of the vector control surface 7 is to change the direction of the slipstream at the tail of the duct, so that the direction of the slipstream flow field output by the duct system is changed, thereby achieving the left and right turning action of the duct and the equipment carrying the duct.

[0038] Specifically, the telescopic spoiler assembly is located below the blade 2 . 3 , the telescopic spoiler assembly is arranged at the smallest inner diameter of the duct ring body 1 , the telescopic spoiler assembly is flush with the support arm 6 , or the telescopic spoiler assembly is located above the support arm 6 .

[0039] Specifically, the vector control surface 7 is connected to the inner wall of the duct ring body 1 through a steering gear, and the vector control surface 7 is connected to the outer wall of the stator 2.1 through a steering gear. It should be noted that the connection method and control method of the steering gear belong to the existing technology, so they are not repeated here.

[0040] Specifically, at least two support arms 6 are provided and are evenly distributed along the circumference of the duct body 1 .

[0041] Example 5: Based on the combination of Example 2 and Example 4, Fig.10 As shown, in a single ducted aircraft, at least two vector control surfaces 7 are provided and are evenly distributed along the circumference of the duct ring body 1 .

[0042] Taking a single ducted aircraft with eight support arms 6 and four vector control surfaces 7 as an example, its working principle is as follows: like Fig.13 , Fig.14As shown, when a single duct system is used, the vector control surface moves independently, allowing the duct to perform actions such as steering; the swing of the vector control surface 7 affects the flow direction of the slipstream at the tail of the duct body, and further affects the running direction of the entire duct body and its aircraft.

[0043] The simple vector control surface 7 can only change the direction of the slipstream at the tail end of the duct. In order to make the duct more functional, Fig.17 As shown, the retractable spoiler and the vector control surface 7 are integrated and controlled in a linked manner, thereby making the duct and the ducted aircraft more controllable.

[0044] The telescopic spoiler is linked with the vector control surface 7, so that the original vector control surface 7 has only a single function of changing the direction of the flow field, and an overall tilting function is added, making the use posture of the aircraft more controllable.

[0045] Example 6: Based on the combination of Example 3 and Example 4, Fig.15 As shown, in the multi-ducted aircraft, in each duct ring body 1, a vector control surface 7 is arranged under at least one support arm 6, and all the vector control surfaces 7 are symmetrically distributed.

[0046] Taking a multi-ducted aircraft in which a vector control surface 7 is arranged in each duct body 1 as an example, its working principle is as follows: like Fig.15 , Fig.16 As shown, in a multi-duct system, each duct can carry only one rudder surface. When the vector rudder surface is working in the multi-duct system, each rudder surface moves independently to make the duct produce a steering action.

[0047] All components and connection methods of components not discussed in this application belong to the known technologies in this technical field and can be directly applied without further explanation.

[0048] In the present invention, the term "plurality" refers to two or more than two, unless otherwise clearly defined. The terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0049] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by terms such as “upper”, “lower”, “left”, “right”, “front” and “back” are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or unit referred to must have a specific direction, be constructed and operated in a specific orientation, and therefore, cannot be understood as a limitation on the present invention.

[0050] In the description of this specification, the description of the terms "one embodiment", "some embodiments", "specific embodiments", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0051] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A multi-attitude duct control system, comprising a duct body, characterized in that: A power propeller is installed inside the duct circle, and a telescopic spoiler component is arranged on the inner wall of the duct circle.

2. A multi-attitude ducted control system according to claim 1, characterized in that: The telescopic spoiler assembly is arranged at the smallest inner diameter of the duct ring; The telescopic spoiler assembly comprises a slide groove and a spoiler plate. The slide groove is arranged on the inner wall of the duct ring body. The spoiler plate is slidably arranged in the slide groove. The duct ring body and the spoiler plate are connected by a linear moving mechanism.

3. A multi-attitude ducted control system according to claim 2, characterized in that: The telescopic spoiler assembly is provided with at least two groups, the spoiler is an arc-shaped plate, and after the spoiler is retracted into the slide groove, it is smoothly connected to the inner wall of the duct ring body, the linear moving mechanism is connected to the symmetry line of the spoiler, and the adjacent spoiler end faces are arranged in parallel.

4. A multi-attitude ducted control system according to claim 3, characterized in that: A rib is arranged between every two spoilers inside the duct ring body.

5. An aircraft, characterized in that: Including a multi-posture duct control system as described in claim 1.

6. An aircraft according to claim 5, characterized in that: The duct ring body is provided with one, and the telescopic spoiler components are provided with at least two groups and are evenly distributed along the circumference of the duct ring body.

7. An aircraft according to claim 5, characterized in that: At least two duct ring bodies are provided, at least two groups of telescopic spoiler components are provided in each duct ring body, and all the 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 arranged between the outer wall of the stator and the inner wall of the duct ring, the rotor is rotatably arranged in the stator, the upper end of the rotor is connected to the blade, and a vector rudder surface is arranged 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 body; The vector control surface is connected to the inner wall of the duct ring through the steering gear, and the vector control surface is connected to the outer wall of the stator through the steering gear.

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

10. An aircraft according to claim 8, characterized in that: At least two duct ring bodies are provided, and in each duct ring body, a vector rudder surface is provided under at least one support arm, and all the vector rudder surfaces are symmetrically distributed.

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