CN114348242A - Variable-drift-diameter duct structure and aircraft - Google Patents
Variable-drift-diameter duct structure and aircraft Download PDFInfo
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- CN114348242A CN114348242A CN202210101970.5A CN202210101970A CN114348242A CN 114348242 A CN114348242 A CN 114348242A CN 202210101970 A CN202210101970 A CN 202210101970A CN 114348242 A CN114348242 A CN 114348242A
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Abstract
The invention relates to the technical field of aircraft duct structures, in particular to a duct structure with variable drift diameter and an aircraft, wherein the duct structure comprises: the culvert comprises outer culvert sections and inner culvert sections, wherein the outer culvert sections and the inner culvert sections are distributed at intervals, are spliced end to form a ring shape, and form a culvert inside; a culvert support structure connected to the outer culvert sections; wherein the outer duct sections are slidable relative to the inner duct sections, the duct support structure being arranged to drive adjacent outer duct sections towards or away from each other, increasing or decreasing the diameter of the duct. The duct structure is telescopic, the drift diameter in the duct can be changed, and the duct type rotor wing system can provide rich and variable lift force and thrust performance after having the variable drift diameter, so that the aircraft has higher maneuverability and is suitable for more complex flight working conditions.
Description
Technical Field
The invention relates to the technical field of aircraft duct structures, in particular to a duct structure with a variable drift diameter and an aircraft.
Background
The aircraft lift device or power device with the duct structure can obtain higher lift efficiency or power performance due to the optimization of the flow field of the duct wall, and has been widely applied to the propeller power devices of rotor aircrafts and fixed-wing aircrafts.
In engineering practice, the rotor type aircraft with the large-diameter rotor can obtain larger absolute lift force, and can realize the flight performance of vertical take-off and landing, hovering and the like, but the larger rotor diameter restricts the maximum flat flight speed of the aircraft, and higher flight speed cannot be obtained.
In order to obtain the optimal power performance at a higher cruising speed, the propeller-type power device has the advantages that the diameter of a blade cannot be too large, so that the maximum pulling force at a low speed is limited, the aircraft is difficult to realize maneuvering flight actions such as vertical take-off and landing, and the take-off and landing are completed by depending on an airport with a longer running runway.
And only have the scheme through control duct afterbody latus rectum among the prior art, it can't adapt to the paddle of equidimension not, also can not realize above-mentioned effect, consequently, needs a kind of duct structure that can be suitable for multiple flight operating mode urgently.
Prior art documents:
patent document 1: CN 107031850A-variable geometry ducted fan and related methods
Disclosure of Invention
Aiming at the defects and shortcomings of the duct structure in the prior art, the invention aims to control the drift diameter of the duct so as to provide rich and variable lift force and thrust performance and adapt to more complex flight working conditions.
The invention provides a variable-diameter duct structure in a first aspect, which comprises:
the culvert comprises outer culvert sections and inner culvert sections, wherein the outer culvert sections and the inner culvert sections are distributed at intervals, are spliced end to form a ring shape, and form a culvert inside;
a culvert support structure connected to the outer culvert sections;
wherein the outer duct sections are slidable relative to the inner duct sections, the duct support structure being arranged to drive adjacent outer duct sections towards or away from each other, causing the diameter of the duct to decrease or increase.
Preferably, the stent comprises a double-shaft and a plurality of telescoping rods disposed on an outer wall of the double-shaft, the second end of each telescoping rod being connected to an inner wall of the corresponding outer stent section, the telescoping rods being configured to have a stretched position and a compressed position, the stent having a maximum open diameter area when the telescoping rods are in the stretched position and a minimum open diameter area when the telescoping rods are in the compressed position.
Preferably, the length of the telescopic rod at the extension position is R, the length of the telescopic rod at the compression position is R, the curvature of the inner side wall surface of the outer duct section is R, the curvature of the inner side wall surface of the inner duct section is R, the length range of the telescopic rod is R-R, and the drift diameter area range of the duct is pi R2-πr2。
Preferably, when the duct is in the minimum area, the outer duct sections are connected end to end, the formed channel section is circular, and when the duct is in the maximum area, the outer duct sections and the inner duct sections are connected end to end, and the formed channel section shape comprises arcs with curvature R and arcs with curvature R which are distributed at intervals.
Preferably, the length of the telescopic rod in the extended position is R, the length of the telescopic rod in the compressed position is R, and the ratio of the maximum area to the minimum area of the duct is 2:1, wherein R: r is
1, the number of the outer duct sections is at least eight.
Preferably, the outer duct section and the inner duct section are both hollow structures with two open ends, the two end edges of the inner duct section are provided with convex parts protruding outwards, and the two end edges of the outer duct section are provided with shielding parts extending inwards, so that the outer duct section cannot be separated from the outer wall of the inner duct section when sliding.
Preferably, the cross-sectional shapes of the outer duct section and the inner duct section are the same, so that the outer duct section can be sleeved on the outer wall of the inner duct section, and the curvature ratio of the outer duct section to the inner duct section is the radius ratio of the duct when the area is the maximum area and the area is the minimum area.
Preferably, the telescopic rod comprises an inner rod and an outer rod, the outer rod is sleeved on the outer wall of the inner rod, and the sections of the inner rod and the outer rod are streamline.
Preferably, the double-layer shaft comprises an inner shaft and an outer shaft, the inner shaft is rotatably connected to the inner wall of the outer shaft, and the telescopic rod is fixed to the outer wall of the outer shaft.
A second aspect of the invention proposes an aircraft comprising a variable-diameter ducted structure according to the above solution.
Compared with the prior art, the invention has the advantages that:
the duct structure is telescopic, the drift diameter in the duct can be changed, and the duct type rotor wing system can provide rich and variable lift force and thrust performance after having the variable drift diameter, so that the aircraft has higher maneuverability and is suitable for more complex flight working conditions.
Different ducted drift diameters correspond to different flight states, so that fuel consumption can be reduced, fuel economy is improved, and the maximum voyage and endurance time of the aircraft are improved.
Drawings
The drawings are not intended to be drawn to scale. In the drawings, each identical or nearly identical component that is illustrated in various figures may be represented by a like numeral. For purposes of clarity, not every component may be labeled in every drawing. Embodiments of various aspects of the present invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic structural view of a variable-diameter ducted structure of the present invention in a maximum-diameter state;
FIG. 2 is a schematic structural view of a variable-diameter bypass structure of the present invention in a minimum-diameter state;
FIG. 3 is an elevation view of a variable-diameter bypass structure of the present invention shown in a maximum-diameter condition;
FIG. 4 is an elevation view of a variable-diameter bypass structure of the present invention shown in a minimum-diameter condition;
figure 5 is a cross-sectional structural view of the variable-diameter bypass structure of the present invention in a maximum-diameter state.
Detailed Description
In order to better understand the technical content of the present invention, specific embodiments are described below with reference to the accompanying drawings.
As described in the background art, an aircraft can obtain a larger lift force when a rotor with a larger diameter is used, but the flight speed is restricted, and a blade with a smaller diameter has a higher speed but limited lift force, so that the invention aims to provide a bypass structure suitable for blades with different diameters so as to improve the flow field of the blades and provide richer lift force and thrust performance.
With reference to fig. 1-4, a first aspect of the present invention provides a variable-diameter ducted structure for use in lift or power devices of aircraft, such as rotors, propellers, and fans, with variable diameter requirements. Mainly comprises an outer duct section 5 and an inner duct section 4, as shown in figures 1-2, the outer duct section 5 and the inner duct section 4 are distributed at intervals, spliced end to end and closed to form a ring shape, and a duct is formed at the inner side.
Further, the culvert support structure is connected to the culvert sections 5 and the culvert sections 5 are slidable relative to the culvert sections 4, the culvert support structure being configured to drive adjacent culvert sections 5 toward or away from each other, such that the drift diameter of the culvert is reduced or increased.
As shown in fig. 1, when the adjacent outer duct sections 5 are far away from each other, the drift diameter of the duct is increased, so that the blades with larger diameters can be accommodated, larger lift force is obtained, and the vertical take-off and landing requirements can be met. As shown in fig. 2, when the adjacent outer duct sections 5 are close to each other, the drift diameter of the duct is reduced, so that the blades with smaller diameters can be accommodated, a faster speed can be obtained, and the requirement of fast flight can be met.
As shown in fig. 5, the outer duct section 5 and the inner duct section 4 have a duct wall section shape conforming to the fluid mechanics principle, and have the aerodynamic properties of a duct-like structure, thereby providing an effect of improving the flow field for the internal rotor or propeller structure.
Specifically, the duct is composed of outer duct sections 5 and inner duct sections 4 which are distributed at intervals along the circumferential direction, and each of the outer duct sections 5 and the inner duct sections 4 has a complete duct section shape, so that airflow flowing through the duct section direction can obtain good aerodynamic characteristics. Wherein, the profile of the outer duct section 5 is slightly larger than that of the inner duct section 4, and can be sleeved outside the inner duct section 4.
When the culvert wall structure sections are combined into the integral culvert, the outer culvert section 5 and the inner culvert section 4 are distributed in a staggered manner, when the outer culvert section 5 and the inner culvert section 4 are completely unfolded, the culvert obtains the maximum drift diameter, and at the moment, the power device can obtain the maximum tension corresponding to flight states such as vertical take-off and landing, hovering and the like; when the culvert wall is contracted, the outer culvert section 5 is gradually sleeved outside the inner culvert section 4, the drift diameter of the culvert is gradually reduced, and the process can realize stepless change; until the inner duct section 4 is completely collected inside the outer duct section 5, the duct obtains the minimum drift diameter, and at the moment, the power device can adapt to the maximum flying speed and corresponds to the flying states of cruising and the like.
Further, as shown in connection with figures 3-4, the stent comprises a double shaft and a plurality of telescoping rods 3 arranged on the outer wall of the double shaft, the second end of each telescoping rod 3 being connected to the inner wall of the corresponding outer stent section 5, the telescoping rods 3 being arranged to have a stretched position and a compressed position, the open diameter area of the stent being the largest when the telescoping rods 3 are in the stretched position and the open diameter area of the stent being the smallest when the telescoping rods 3 are in the compressed position.
Specifically, the length of the telescopic rod 3 in the extended position is R, the length of the telescopic rod 3 in the compressed position is R, the curvature 51 of the inner side wall surface of the outer duct section is R, the curvature 52 of the inner side wall surface of the inner duct section is R, the length range of the telescopic rod 3 is R-R, and the drift diameter area range of the duct is pi R2-πr2。
Preferably, as shown in fig. 3 to 4, when the duct is at the minimum area, the outer duct section 5 is connected end to end, the formed channel cross section is circular, and when the duct is at the maximum area, the outer duct section 5 and the inner duct section 4 are connected end to end, and the formed channel cross section shape comprises circular arcs with curvature R and circular arcs with curvature R which are distributed at intervals.
In an alternative embodiment, the rotor system may be designed to operate with variable diameter rotor systems,the change rate of the inner drift diameter of the duct, which needs to be provided by the variable-drift-diameter duct structure, needs to reach 1:2, namely the cross section area of the inner drift diameter of the duct in the fully opened state of the segmented duct wall is 2 times of that of the duct wall in the fully contracted state. Therefore, the requirement of the extension range of the corresponding extension inner stay bar is
In other embodiments, to achieve a greater rate of change of cross-sectional area of the diameter, the number of nested layers may be increased, for example three layers, or four layers, but as the size difference between the duct sections increases, the aerodynamic impact is greater with full deployment, and therefore, it is preferred that the duct sections include two layers, an inner duct section and an outer duct section.
Further, the number of the outer duct sections is preferably more, the more the outer duct sections are, the closer the outer duct sections are to the standard circle, the more the pneumatic performance is facilitated, but the structural complexity is increased, the number of the inner support rods is correspondingly increased, and the overall structure is not facilitated. Conversely, the smaller the number of segments, the simpler the structure, but the worse the roundness. The structure realization and the pneumatic performance are comprehensively considered, and an 8-section structure is selected currently.
The cross-sectional shape of outer duct section 5 and inner duct section 4 is the same, makes outer duct section 5 can overlap the outer wall of interior duct section 4, and the radius ratio when the camber ratio of outer duct section 5 and inner duct section 4 is the biggest area of duct and minimum area, so, guarantees that inner duct section 4 can contract in outer duct section 5.
Further, outer duct section 5 and inner duct section 4 are the open hollow structure in both ends, and the both ends border of inner duct section 4 is equipped with outside convex bellying 42, and the both ends border of outer duct section 5 is equipped with the shelter from portion 52 of inside extension, makes outer duct section 5 can not deviate from when inner duct section 4 outer wall slides.
Further, the telescopic rod 3 comprises an inner rod 32 and an outer rod 31, the outer rod 31 is sleeved on the outer wall of the inner rod 32, and the sections of the inner rod 32 and the outer rod 31 are streamline. The inner rod 32 and the outer rod 31 have streamline shapes, adopt a sleeve type telescopic structure, are driven by the electric push rod, and realize synchronous telescopic operation of all rod pieces by controlling the parallel connection of the electric push rods in the telescopic rods 3.
Specifically, the inner rod 32 extends outwards to drive the outer duct section 5 to be unfolded, the inner duct section 4 is gradually exposed, and the drift diameter of the duct is increased; the inner rod 32 contracts to drive the outer duct section 5 to contract, the inner duct section 4 is collected inside the outer duct section 5, and the drift diameter of the duct is reduced. The telescopic length range of the telescopic rod 3 is as follows: R-R.
Referring to fig. 5, the double-layered shaft comprises an inner shaft 1 and an outer shaft 2, the inner shaft 1 is rotatably connected to the inner wall of the outer shaft 2, and the telescopic rod 3 is fixed to the outer wall of the outer shaft 2. In this way, support can be formed for the bypass section 5. The inner shaft 1 is used for mounting the blades, and when the blades rotate, power is generated.
A second aspect of the invention proposes an aircraft comprising a variable-diameter ducted structure according to the above solution.
For example, the aircraft is a tiltrotor aircraft. The tilt rotor aircraft uses two sets (or 4 sets) of rotor systems installed in a transverse arrangement, and the rotor systems can tilt for 90 degrees through a tilt shaft, so that the rotors can be freely switched between a vertical upward working state and a forward working state, and the aircraft simultaneously has a vertical take-off and landing working mode of a helicopter and a propeller driving front flying mode of a fixed-wing aircraft. The addition of variable latus rectum ducted system can greatly improve the rotor aerodynamic efficiency of rotor aircraft verting under two kinds of mode, makes flight performance and fuel economy all obtain promoting.
In an alternative embodiment, a flying automobile. With the gradual maturity of control technology of four rotor crafts, rotor class hovercar for civilian use becomes possible. But the safety of the flying automobile in a general use scene is a more outstanding problem. Set up ducted system in the rotor outside, both can play the safety protection effect, can improve rotor aerodynamic characteristic again. The variable-drift-diameter duct system provides duct pneumatic environments facing different scenes for the aerocar lift system, and meets different use requirements of vertical take-off and landing, crossing and flying patrol and the like respectively.
By combining the embodiment, the duct structure is of a telescopic type, the drift diameter in the duct can be changed, and after the duct type rotor wing system has the variable drift diameter, the duct type rotor wing system can provide rich and variable lift force and thrust performance, so that the aircraft has higher maneuverability and adapts to more complex flight working conditions.
Different ducted drift diameters correspond to different flight states, so that fuel consumption can be reduced, fuel economy is improved, and the maximum voyage and endurance time of the aircraft are improved.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to be limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the invention. Therefore, the protection scope of the present invention should be determined by the appended claims.
Claims (10)
1. A variable-diameter ducted structure, comprising:
the culvert comprises outer culvert sections and inner culvert sections, wherein the outer culvert sections and the inner culvert sections are distributed at intervals, are spliced end to form a ring shape, and form a culvert inside;
a culvert support structure connected to the outer culvert sections;
wherein the outer duct sections are slidable relative to the inner duct sections, the duct support structure being arranged to drive adjacent outer duct sections towards or away from each other, causing the diameter of the duct to decrease or increase.
2. The variable-diameter ducted structure according to claim 1, wherein the ducted support structure includes a double-shaft and a plurality of telescoping rods disposed at an outer wall of the double-shaft, a second end of each telescoping rod being connected to an inner wall of the corresponding outer ducted section, the telescoping rods being disposed to have a stretched position and a compressed position, a through-diameter area of the ducted being the largest when the telescoping rods are in the stretched position and the through-diameter area of the ducted being the smallest when the telescoping rods are in the compressed position.
3. The variable-diameter ductal structure according to claim 2, wherein the length of the telescopic rod in the extended position isR, the length of the telescopic rod in the compression position is R, the curvature of the inner side wall surface of the outer duct section is R, the curvature of the inner side wall surface of the inner duct section is R, the length range of the telescopic rod is R-R, and the drift diameter area range of the duct is pi R2-πr2。
4. The variable-diameter duct structure according to claim 3, wherein the outer duct section is connected end to form a channel section having a circular shape when the duct is at a minimum area, and the outer duct section and the inner duct section are connected end to form a channel section shape including arcs of curvature R and arcs of curvature R which are spaced apart when the duct is at a maximum area.
5. The variable-diameter ductal structure according to claim 2, wherein the length of the telescopic rod in the extended position is R, the length of the telescopic rod in the compressed position is R, and the ratio of the maximum area to the minimum area of the ductal is 2:1, where R: r is
The number of the outer duct sections is at least eight.
6. The variable-diameter culvert structure according to any one of claims 1-5, wherein the outer culvert section and the inner culvert section are both hollow structures with two open ends, the two end edges of the inner culvert section are provided with convex parts protruding outwards, and the two end edges of the outer culvert section are provided with shielding parts extending inwards, so that the inner culvert section cannot be separated when the outer wall of the outer culvert section slides.
7. The variable-diameter duct structure according to any one of claims 1 to 5, wherein the cross-sectional shapes of the outer duct section and the inner duct section are the same, so that the outer duct section can be sleeved on the outer wall of the inner duct section, and the curvature ratio of the outer duct section and the inner duct section is the radius ratio of the duct at the maximum area and the minimum area.
8. The variable-diameter duct structure according to claim 2, wherein the telescopic rod comprises an inner rod and an outer rod, the outer rod is sleeved on the outer wall of the inner rod, and the cross sections of the inner rod and the outer rod are streamline.
9. The variable-diameter ducted structure according to claim 2, wherein the double-layered shaft includes an inner shaft and an outer shaft, the inner shaft is rotatably connected to an inner wall of the outer shaft, and the telescopic rod is fixed to an outer wall of the outer shaft.
10. An aircraft comprising a variable-diameter ducted structure according to any one of claims 1 to 9.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210101970.5A CN114348242B (en) | 2022-01-27 | 2022-01-27 | Duct structure and aircraft of variable latus rectum |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210101970.5A CN114348242B (en) | 2022-01-27 | 2022-01-27 | Duct structure and aircraft of variable latus rectum |
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| CN114348242B CN114348242B (en) | 2023-05-23 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024006584A3 (en) * | 2022-07-01 | 2024-02-08 | Xagon Solutions Inc. | Adaptive duct fan with individually controlled slats |
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