CN114348242A - Variable-drift-diameter duct structure and aircraft - Google Patents

Variable-drift-diameter duct structure and aircraft Download PDF

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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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duct
section
duct section
telescopic rod
rod
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CN114348242B (en
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孙中涛
尹硕
高亚东
王华明
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Nanjing University of Aeronautics and Astronautics
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Abstract

本发明涉及飞行器涵道结构技术领域,具体而言涉及可变通径的涵道结构和飞行器,涵道结构包括:外涵道段和内涵道段,所述外涵道段和内涵道段间隔分布并首尾拼接闭合呈环形,并在内侧形成涵道;涵道支撑结构,连接到所述外涵道段;其中,所述外涵道段能相对于所述内涵道段滑动,所述涵道支撑结构被设置成能驱动相邻的所述外涵道段相互靠近或远离,使所述涵道的通径增加或减小。本发明的涵道结构为可伸缩型,能改变涵道内的通径,涵道类旋翼系统具有了可变通径之后,能够提供丰富可变的升力、推力性能,从而使飞行器具有更高机动性能,适应更为复杂的飞行工况。

Figure 202210101970

The invention relates to the technical field of duct structures for aircraft, in particular to a duct structure with a variable diameter and an aircraft. The duct structure includes: an outer duct section and an inner duct section, and the outer duct section and the inner duct section are distributed at intervals The end-to-end splicing is closed to form a ring, and a duct is formed on the inner side; the duct support structure is connected to the outer duct section; wherein, the outer duct section can slide relative to the inner duct section, and the duct The support structure is arranged to drive adjacent sections of the outer ducts to approach or move away from each other, so as to increase or decrease the diameter of the ducts. The duct structure of the present invention is a retractable type, which can change the diameter in the duct. After the ducted rotor system has a variable diameter, it can provide rich and variable lift and thrust performance, so that the aircraft has higher maneuverability. , adapt to more complex flight conditions.

Figure 202210101970

Description

可变通径的涵道结构和飞行器Variable diameter ducted structure and aircraft

技术领域technical field

本发明涉及飞行器涵道结构技术领域,具体而言涉及可变通径的涵道结构和飞行器。The invention relates to the technical field of duct structures for aircraft, in particular to a duct structure with a variable diameter and an aircraft.

背景技术Background technique

具有涵道结构的飞行器升力装置或动力装置,由于涵道壁对流场的优化,可以获得更高的升力效率或动力性能,已经在旋翼类飞行器和固定翼类飞行器的螺旋桨动力装置上有了广泛的应用。The lift device or power device of an aircraft with a ducted structure can obtain higher lift efficiency or power performance due to the optimization of the flow field of the ducted wall. It has already been used in the propeller power devices of rotary-wing aircraft and fixed-wing aircraft. Wide range of applications.

在工程实践中,具有大直径旋翼的旋翼类飞行器可以获得较大的绝对升力,实现垂直起降、悬停等飞行性能,但是较大的旋翼直径对飞行器的最大平飞速度产生制约,无法获得较高的飞行速度。In engineering practice, rotorcraft with large diameter rotors can obtain larger absolute lift and achieve flight performance such as vertical take-off and landing, hovering, etc. However, the larger diameter of the rotors restricts the maximum level flight speed of the aircraft, which cannot be obtained. higher flight speed.

而螺旋桨类动力装置为了在较高的巡航速度下获得最佳动力性能,其桨叶直径不能太大,因此在低速下的最大拉力有限,使得飞行器难以实现垂直起降等机动飞行动作,必须依赖具有较长滑跑跑道的机场来完成起飞和降落。However, in order to obtain the best power performance at high cruising speed, the propeller-type power plant should not have a large blade diameter, so the maximum pulling force at low speed is limited, making it difficult for the aircraft to achieve vertical take-off and landing maneuvers, which must rely on Airports with longer runways to complete takeoffs and landings.

而现有技术中仅有通过控制涵道尾部通径的方案,其无法适应不同大小的桨叶,也不能实现上述效果,因此,亟需一种能适用多种飞行工况的涵道结构。However, in the prior art, there is only a solution by controlling the diameter of the tail of the duct, which cannot adapt to different sizes of blades, and cannot achieve the above effects. Therefore, a duct structure that can be applied to various flight conditions is urgently needed.

现有技术文献:Prior art literature:

专利文献1:CN107031850A-能变几何形状涵道风扇及相关方法Patent Document 1: CN107031850A - Ducted Fan with Variable Geometry and Related Methods

发明内容SUMMARY OF THE INVENTION

针对现有技术中涵道结构的缺陷与不足,本发明目的在于,能控制涵道的通径,以提供丰富可变的升力和推力性能,能适应更为复杂的飞行工况。Aiming at the defects and deficiencies of the duct structure in the prior art, the purpose of the present invention is to control the diameter of the duct to provide rich and variable lift and thrust performance, and to adapt to more complex flight conditions.

本发明第一方面提出一种可变通径的涵道结构,包括:A first aspect of the present invention proposes a duct structure with a variable diameter, including:

外涵道段和内涵道段,所述外涵道段和内涵道段间隔分布并首尾拼接闭合呈环形,并在内侧形成涵道;The outer bypass section and the inner channel section, the outer bypass section and the inner channel section are distributed at intervals, spliced and closed end to end in a ring shape, and a bypass channel is formed on the inner side;

涵道支撑结构,连接到所述外涵道段;a duct support structure connected to the outer duct section;

其中,所述外涵道段能相对于所述内涵道段滑动,所述涵道支撑结构被设置成能驱动相邻的所述外涵道段相互靠近或远离,使所述涵道的通径减小或增加。Wherein, the outer duct section can slide relative to the inner duct section, and the duct supporting structure is configured to drive the adjacent outer duct sections to approach or move away from each other, so that the passage of the duct decrease or increase in diameter.

优选的,所述涵道支撑结构包括双层轴以及设置在所述双层轴外壁的多个伸缩杆,每个所述伸缩杆的第二端连接到对应的所述外涵道段的内壁,所述伸缩杆被设置成具有拉伸位置和压缩位置,当所述伸缩杆处于拉伸位置时,所述涵道的通径面积最大,当所述伸缩杆处于压缩位置时,所述涵道的通径面积最小。Preferably, the duct support structure includes a double-layer shaft and a plurality of telescopic rods arranged on the outer wall of the double-layer shaft, and the second end of each of the telescopic rods is connected to the inner wall of the corresponding outer duct section , the telescopic rod is set to have a stretched position and a compressed position. When the telescopic rod is in the stretched position, the diameter area of the duct is the largest. When the telescopic rod is in the compressed position, the culvert has the largest diameter. The path area of the channel is the smallest.

优选的,所述伸缩杆在伸长位置时的长度为R,所述伸缩杆在压缩位置时的长度为r,所述外涵道段的内侧壁面曲率为r,所述内涵道段的内侧壁面曲率为R,所述伸缩杆的长度范围为R-r,所述涵道的通径面积范围为πR2-πr2Preferably, the length of the telescopic rod in the extended position is R, the length of the telescopic rod in the compressed position is r, the curvature of the inner wall surface of the outer duct section is r, and the inner side of the inner duct section is r The curvature of the wall surface is R, the length of the telescopic rod is in the range of Rr, and the diameter of the duct is in the range of πR 2 -πr 2 .

优选的,当所述涵道处于最小面积时,所述外涵道段首尾相接,形成的通道截面为圆形,当所述涵道处于最大面积时,所述外涵道段和内涵道段首尾相接,形成的通道截面形状包括间隔分布的曲率为R的圆弧和曲率为r的圆弧。Preferably, when the duct is in the smallest area, the outer duct sections are connected end to end, and the formed channel has a circular cross-section. When the duct is in the largest area, the outer duct section and the inner duct The segments are connected end to end, and the formed channel cross-sectional shape includes a circular arc with a curvature R and a circular arc with a curvature r distributed at intervals.

优选的,所述伸缩杆在伸长位置时的长度为R,所述伸缩杆在压缩位置时的长度为r,所述涵道的最大面积和最小面积的比为2:1,其中R:r为

Figure BDA0003492738360000021
1,所述外涵道段至少为八个。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, where R: r is
Figure BDA0003492738360000021
1. The number of the outer bypass passages is at least eight.

优选的,所述外涵道段和内涵道段均为两端开放的空心结构,所述内涵道段的两端边沿设有向外凸出的凸起部,所述外涵道段的两端边沿设有向内延伸的遮挡部,使外涵道段在内涵道段外壁滑动时不会脱出。Preferably, the outer duct section and the inner duct section are both hollow structures with open ends, the edges of both ends of the inner duct section are provided with bulges protruding outward, and the two ends of the outer duct section are provided with protruding portions. The end edge is provided with an inwardly extending shielding part, so that the outer duct section will not come out when the outer wall of the inner duct section slides.

优选的,所述外涵道段和内涵道段的截面形状相同,使所述外涵道段能套设在所述内涵道段的外壁,所述外涵道段和内涵道段的曲率比为所述涵道最大面积和最小面积时的半径比。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 and the inner duct section is the same is the ratio of the radius of the maximum area to the minimum area of the duct.

优选的,所述伸缩杆包括内杆和外杆,所述外杆套设在所述内杆的外壁,所述内杆和外杆的截面为流线型。Preferably, the telescopic rod includes 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 streamlined.

优选的,所述双层轴包括内轴和外轴,所述内轴转动连接在所述外轴的内壁,所述伸缩杆固定在所述外轴的外壁。Preferably, the double-layer shaft includes 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.

本发明第二方面提出一种飞行器,包括上述方案中的可变通径的涵道结构。A second aspect of the present invention provides an aircraft including the variable-diameter duct structure in the above solution.

与现有技术相比,本发明的优点在于:Compared with the prior art, the advantages of the present invention are:

本发明的涵道结构为可伸缩型,能改变涵道内的通径,涵道类旋翼系统具有了可变通径之后,能够提供丰富可变的升力、推力性能,从而使飞行器具有更高机动性能,适应更为复杂的飞行工况。The duct structure of the present invention is a retractable type, which can change the diameter in the duct. After the ducted rotor system has a variable diameter, it can provide rich and variable lift and thrust performance, so that the aircraft has higher maneuverability. , adapt to more complex flight conditions.

不同的涵道通径对应不同的飞行状态,可以减少燃油消耗,提高燃油经济性,使飞行器的最大航程和续航时间得到提升。Different duct paths correspond to different flight states, which can reduce fuel consumption, improve fuel economy, and increase the maximum range and endurance of the aircraft.

附图说明Description of drawings

附图不意在按比例绘制。在附图中,在各个图中示出的每个相同或近似相同的组成部分可以用相同的标号表示。为了清晰起见,在每个图中,并非每个组成部分均被标记。现在,将通过例子并参考附图来描述本发明的各个方面的实施例,其中: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 the same reference numeral. For clarity, not every component is labeled in every figure. Embodiments of various aspects of the present invention will now be described by way of example and with reference to the accompanying drawings, wherein:

图1是本发明所示的可变通径的涵道结构处于最大通径状态的结构示意图;Fig. 1 is the structural representation that the duct structure of the variable diameter shown in the present invention is in the state of maximum diameter;

图2是本发明所示的可变通径的涵道结构处于最小通径状态的结构示意图;Fig. 2 is the structural representation that the duct structure of the variable diameter shown in the present invention is in the minimum diameter state;

图3是本发明所示的可变通径的涵道结构处于最大通径状态的正视图;Fig. 3 is the front view of the duct structure of the variable diameter shown in the present invention in the state of maximum diameter;

图4是本发明所示的可变通径的涵道结构处于最小通径状态的正视图;Fig. 4 is the front view of the duct structure of the variable diameter shown in the present invention in the minimum diameter state;

图5是本发明所示的可变通径的涵道结构处于最大通径状态的截面结构示意图。FIG. 5 is a schematic cross-sectional structure diagram of the variable-diameter duct structure shown in the present invention in a state of maximum diameter.

具体实施方式Detailed ways

为了更了解本发明的技术内容,特举具体实施例并配合所附图式说明如下。In order to better understand the technical content of the present invention, specific embodiments are given and described below in conjunction with the accompanying drawings.

如背景技术所述的,飞行器在较大直径的旋翼时能获得较大升力,但是飞行速度被制约,较小直径的桨叶具有较高的速度,但是升力有限,因此本发明的目的在于提出一种适应不同直径桨叶的涵道结构,以改善桨叶的流场,可提供更丰富的升力、推力性能。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. A blade with a smaller diameter has a higher speed, but the lift force is limited. A ducted structure adapted to blades of different diameters to improve the flow field of the blades and provide richer lift and thrust performance.

结合图1-4所示,本发明目第一方面提出一种可变通径的涵道结构,可用于具有可变直径要求的旋翼、螺旋桨、风扇等飞行器升力或动力装置中。主要包括外涵道段5和内涵道段4,如图1-2所示,外涵道段5和内涵道段4间隔的分布并首尾拼接闭合呈环形,并在内侧形成涵道。1-4, the first aspect of the present invention proposes a variable diameter duct structure, which can be used in aircraft lift or power devices such as rotors, propellers, and fans with variable diameter requirements. It mainly includes the outer duct section 5 and the inner duct section 4. As shown in Figure 1-2, the distribution of the interval between the outer duct section 5 and the inner duct section 4 is spliced and closed in a ring shape, and a duct is formed on the inside.

进一步的,涵道支撑结构连接到外涵道段5,并且外涵道段5能相对于内涵道段4滑动,涵道支撑结构被设置成能驱动相邻的外涵道段5相互靠近或远离,如此,使涵道的通径减小或增加。Further, the duct support structure is connected to the outer duct section 5, and the outer duct section 5 can slide relative to the inner duct section 4, and the duct support structure is arranged to drive the adjacent outer duct sections 5 to approach each other or away, so that the diameter of the duct is reduced or increased.

如图1所示,当相邻的外涵道段5相互远离时,涵道的通径增加,如此,可容纳较大直径的桨叶,获得较大的升力,能满足垂直起降的需求。如图2所示,当相邻的外涵道段5相互靠近时,涵道的通径减小,如此,可容纳较小直径的桨叶,获得较快的速度,能满足快速飞行的需求。As shown in Fig. 1, when the adjacent outer duct sections 5 are far away from each other, the diameter of the duct increases, so that a larger diameter blade can be accommodated, a larger lift force can be obtained, and a vertical take-off and landing requirement can be met. . As shown in Figure 2, when the adjacent outer duct sections 5 are close to each other, the diameter of the duct decreases, so that smaller diameter blades can be accommodated, faster speed can be obtained, and the requirement of fast flight can be met. .

结合图5所示,外涵道段5和内涵道段4具有符合流体力学原理的涵道壁切面形状,具有涵道类结构的空气动力学属性,从而为内部旋翼或螺旋桨结构提供改善流场的作用。As shown in Figure 5, the outer duct section 5 and the inner duct section 4 have a duct wall section shape that conforms to the principle of fluid mechanics, and have the aerodynamic properties of a duct-like structure, thereby providing an improved flow field for the internal rotor or propeller structure. effect.

具体的,涵道由沿周向间隔分布的外涵道段5和内涵道段4组成,每个外涵道段5和内涵道段4都具有完整的涵道切面形状,使沿涵道切面方向流过的气流可以获得良好的空气动力学特性。其中,外涵道段5形面略大于内涵道段4,可以套在内涵道段4外侧。Specifically, the duct is composed of an outer duct section 5 and an inner duct section 4 distributed at intervals along the circumferential direction, and each of the outer duct section 5 and the inner duct section 4 has a complete duct section shape, so that the duct section along the duct section Good aerodynamics can be achieved by the airflow passing in the direction. Among them, the outer duct section 5 is slightly larger than the inner duct section 4, and can be set on the outside of the inner duct section 4.

涵道壁结构段组合成整体涵道时,外涵道段5与内涵道段4间错排布,当外涵道段5与内涵道段4全部展开时,涵道获得最大通径,此时动力装置可以获得最大拉力,对应垂直起降、悬停等飞行状态;当涵道壁收缩,外涵道段5逐渐套叠在内涵道段4外侧,涵道通径逐渐缩小,此过程可以实现无级变化;直到内涵道段4全部收于外涵道段5内侧时,涵道获得最小通径,此时动力装置可以适应最大飞行速度,对应巡航等飞行状态。When the structural sections of the duct wall are combined into a whole duct, the outer duct section 5 and the inner duct section 4 are staggered. When the outer duct section 5 and the inner duct section 4 are all unfolded, the duct has the maximum diameter. When the power device can obtain the maximum pulling force, it corresponds to the flight states such as vertical take-off and landing, hovering, etc.; when the duct wall shrinks, the outer duct section 5 gradually overlaps the outer side of the inner duct section 4, and the duct diameter gradually shrinks. To achieve stepless change; until the inner section 4 is all closed inside the outer section 5, the duct obtains the minimum diameter, at this time the power unit can adapt to the maximum flight speed, corresponding to the flight state such as cruise.

进一步的,结合图3-4所示,涵道支撑结构包括双层轴以及设置在双层轴外壁的多个伸缩杆3,每个伸缩杆3的第二端连接到对应的外涵道段5的内壁,伸缩杆3被设置成具有拉伸位置和压缩位置,当伸缩杆3处于拉伸位置时,涵道的通径面积最大,当伸缩杆3处于压缩位置时,涵道的通径面积最小。Further, as shown in FIGS. 3-4, the duct support structure includes a double-layer shaft and a plurality of telescopic rods 3 arranged on the outer wall of the double-layer shaft, and the second end of each telescopic rod 3 is connected to the corresponding outer duct section. 5, the telescopic rod 3 is set to have a stretched position and a compressed position. When the telescopic rod 3 is in the stretched position, the diameter area of the duct is the largest. When the telescopic rod 3 is in the compressed position, the diameter of the duct is the largest. The smallest area.

具体的,伸缩杆3在伸长位置时的长度为R,伸缩杆3在压缩位置时的长度为r,外涵道段的内侧壁面曲率51为r,内涵道段的内侧壁面曲率52为R,伸缩杆3的长度范围为R-r,涵道的通径面积范围为πR2-πr2Specifically, 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 length of the telescopic rod 3 is in the range of Rr, and the diameter of the duct is in the range of πR 2 -πr 2 .

优选的,结合图3-4所示,当涵道处于最小面积时,外涵道段5首尾相接,形成的通道截面为圆形,当涵道处于最大面积时,外涵道段5和内涵道段4首尾相接,形成的通道截面形状包括间隔分布的曲率为R的圆弧和曲率为r的圆弧。Preferably, as shown in Figures 3-4, when the duct is in the smallest area, the outer duct section 5 is connected end to end, and the formed channel cross-section is circular. When the duct is in the largest area, the outer duct section 5 and The inner channel sections 4 are connected end to end, and the formed channel cross-sectional shape includes a circular arc with a curvature R and a circular arc with a curvature r distributed at intervals.

在可选的实施例中,针对可变直径的旋翼系统的工作要求,可变通径涵道结构需要提供的涵道内通径变化率需达到1:2,即分段涵道壁全部打开状态下的涵道内通径截面积是涵道壁完全收缩状态下的2倍。因此,对应的伸缩内撑杆的伸缩范围要求即为

Figure BDA0003492738360000041
In an optional embodiment, according to the working requirements of the variable-diameter rotor system, the variable-diameter duct structure needs to provide a duct diameter change rate of 1:2, that is, the duct when the segmented duct walls are fully opened. The cross-sectional area of the inner diameter of the channel is twice that of the fully retracted state of the duct wall. Therefore, the telescopic range requirement of the corresponding telescopic inner strut is
Figure BDA0003492738360000041

在其他的实施例中,若要实现更大通径的截面积变化率,可增加套接层数,例如三层,或者四层,但是随着涵道段之间的尺寸差异增大,在全部展开的情况下,对气动影响较大,因此,优选的,涵道段包括两层,内涵道段和外涵道段。In other embodiments, in order to achieve a larger rate of change in the cross-sectional area of the diameter, the number of socket layers can be increased, such as three layers or four layers, but as the size difference between the duct sections increases, all the In the case of unfolding, it has a great influence on the aerodynamics. Therefore, preferably, the duct section includes two layers, the inner duct section and the outer duct section.

进一步的,外涵道段的数量优选为更多,分段越多,越趋近于标准圆形,对气动性能更有利,但结构复杂度增加,内撑杆数量相应增加,对整体结构实现不利。相反,分段数量越少,结构越简单,但圆度越差。综合考虑结构实现与气动性能,当前选用8段结构。Further, the number of outer bypass sections is preferably larger, and the more segments, the closer to a standard circle, which is more beneficial to the aerodynamic performance, but the structural complexity increases, and the number of inner struts increases correspondingly, which is beneficial to the overall structure. unfavorable. Conversely, the smaller the number of segments, the simpler the structure, but the worse the roundness. Taking structural realization and aerodynamic performance into consideration, an 8-segment structure is currently selected.

外涵道段5和内涵道段4的截面形状相同,使外涵道段5能套设在内涵道段4的外壁,且外涵道段5和内涵道段4的曲率比为涵道最大面积和最小面积时的半径比,如此,保证内涵道段4能缩到外涵道段5内。The cross-sectional shape of the outer bypass section 5 and the inner channel section 4 is the same, so that the outer bypass section 5 can be set on the outer wall of the inner channel section 4, and the curvature ratio of the outer bypass section 5 and the inner channel section 4 is the largest. The ratio of the radius of the area to the minimum area, so as to ensure that the inner channel section 4 can be retracted into the outer bypass channel section 5.

进一步的,外涵道段5和内涵道段4均为两端开放的空心结构,内涵道段4的两端边沿设有向外凸出的凸起部42,外涵道段5的两端边沿设有向内延伸的遮挡部52,使外涵道段5在内涵道段4外壁滑动时不会脱出。Further, the outer duct section 5 and the inner duct section 4 are both hollow structures with open ends, the edges of both ends of the inner duct section 4 are provided with bulges 42 that protrude outward, and both ends of the outer duct section 5 are provided with protruding portions 42. The edge is provided with a shielding portion 52 extending inward, so that the outer duct section 5 will not come out when the outer wall of the inner duct section 4 slides.

进一步的,伸缩杆3包括内杆32和外杆31,外杆31套设在内杆32的外壁,内杆32和外杆31的截面为流线型。内杆32和外杆31具有流线型外形,采用套管式伸缩结构,由电动推杆驱动,通过控制多个伸缩杆3内的电动推杆并联,实现各个杆件的同步伸缩操作。Further, the telescopic rod 3 includes 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 cross-sections of the inner rod 32 and the outer rod 31 are streamlined. The inner rod 32 and the outer rod 31 have a streamlined shape, adopt a sleeve type telescopic structure, and are driven by electric push rods.

具体的,内杆32外伸,驱动外涵道段5展开,内涵道段4逐渐露出,涵道通径变大;内杆32收缩,驱动外涵道段5收缩,内涵道段4收于外涵道段5内部,涵道通径变小。伸缩杆3的可伸缩长度范围为:R-r。Specifically, the inner rod 32 extends outward, driving the outer duct section 5 to expand, the inner duct section 4 is gradually exposed, and the duct diameter becomes larger; the inner rod 32 shrinks, driving the outer duct section 5 to shrink, and the inner duct section 4 is closed at Inside the outer duct section 5, the duct diameter becomes smaller. The telescopic length range of the telescopic rod 3 is: R-r.

结合图5所示,双层轴包括内轴1和外轴2,内轴1转动连接在外轴2的内壁,伸缩杆3固定到外轴2的外壁。如此,能对外涵道段5形成支撑。内轴1用于安装桨叶,当桨叶旋转产生动力。5 , the double-layer shaft includes 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, the outer bypass section 5 can be supported. The inner shaft 1 is used to install the blades, and when the blades rotate, power is generated.

本发明第二方面提出一种飞行器,包括上述方案中的可变通径的涵道结构。A second aspect of the present invention provides an aircraft including the variable-diameter duct structure in the above solution.

例如,飞行器是倾转旋翼飞行器。倾转旋翼飞行器使用横列式安装的两套(或4套)旋翼系统,旋翼系统通过倾转轴,可以90度倾转工作,使旋翼可以在垂直向上和向前两种工作状态下自由切换,从而使飞行器同时具有直升机的垂直起降工作模式和定翼机的螺旋桨驱动前飞模式。可变通径涵道系统的加入,可以极大改善倾转旋翼飞行器在两种工作模式下的旋翼气动效率,使飞行性能和燃料经济性都得到提升。For example, the aircraft is a tiltrotor aircraft. The tilt-rotor aircraft uses two sets (or four sets) of rotor systems installed in a row. The rotor system can tilt 90 degrees through the tilt axis, so that the rotor can be freely switched between the vertical upward and forward working states, thereby The aircraft has the vertical take-off and landing working mode of the helicopter and the propeller-driven forward flight mode of the fixed-wing aircraft at the same time. The addition of the variable diameter duct system can greatly improve the rotor aerodynamic efficiency of the tilt-rotor aircraft in the two working modes, so that the flight performance and fuel economy are improved.

在可选的实施例中,飞行汽车。随着四旋翼飞行器的控制技术逐渐成熟,面向民用的旋翼类飞行汽车成为可能。但是在通用使用场景下的飞行汽车,其安全性是较为突出的问题。在旋翼外侧设置涵道系统,既可以起到安全防护作用,又可以改善旋翼气动特性。可变通径涵道系统,为飞行汽车升力系统提供了面向不同场景的涵道气动环境,分别应对垂直起降和跨越巡飞等不同使用要求。In an alternative embodiment, a flying car. With the gradual maturity of the control technology of the quadrotor aircraft, the civil-oriented rotary-wing flying car becomes possible. However, the safety of flying cars in general use scenarios is a more prominent problem. A duct system is set on the outside of the rotor, which can not only play a role in safety protection, but also improve the aerodynamic characteristics of the rotor. The variable diameter duct system provides a ducted aerodynamic environment for different scenarios for the lift system of the flying car, which can respectively meet different usage requirements such as vertical take-off and landing and spanning cruise.

结合以上实施例,本发明的涵道结构为可伸缩型,能改变涵道内的通径,涵道类旋翼系统具有了可变通径之后,能够提供丰富可变的升力、推力性能,从而使飞行器具有更高机动性能,适应更为复杂的飞行工况。In combination with the above embodiments, the duct structure of the present invention is a retractable type, which can change the diameter in the duct. After the ducted rotor system has a variable diameter, it can provide rich and variable lift and thrust performance, so that the aircraft can be improved. It has higher maneuverability and adapts to more complex flight conditions.

不同的涵道通径对应不同的飞行状态,可以减少燃油消耗,提高燃油经济性,使飞行器的最大航程和续航时间得到提升。Different duct paths correspond to different flight states, which can reduce fuel consumption, improve fuel economy, and increase the maximum range and endurance of the aircraft.

虽然本发明已以较佳实施例揭露如上,然其并非用以限定本发明。本发明所属技术领域中具有通常知识者,在不脱离本发明的精神和范围内,当可作各种的更动与润饰。因此,本发明的保护范围当视权利要求书所界定者为准。Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which the present invention pertains can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, the protection scope of the present invention should be determined according to the claims.

Claims (10)

1.一种可变通径的涵道结构,其特征在于,包括:1. a duct structure of variable diameter, is characterized in that, comprises: 外涵道段和内涵道段,所述外涵道段和内涵道段间隔分布并首尾拼接闭合呈环形,并在内侧形成涵道;The outer bypass section and the inner channel section, the outer bypass section and the inner channel section are distributed at intervals, spliced and closed end to end in a ring shape, and a bypass channel is formed on the inner side; 涵道支撑结构,连接到所述外涵道段;a duct support structure connected to the outer duct section; 其中,所述外涵道段能相对于所述内涵道段滑动,所述涵道支撑结构被设置成能驱动相邻的所述外涵道段相互靠近或远离,使所述涵道的通径减小或增加。Wherein, the outer duct section can slide relative to the inner duct section, and the duct supporting structure is configured to drive the adjacent outer duct sections to approach or move away from each other, so that the passage of the duct decrease or increase in diameter. 2.根据权利要求1所述的可变通径的涵道结构,其特征在于,所述涵道支撑结构包括双层轴以及设置在所述双层轴外壁的多个伸缩杆,每个所述伸缩杆的第二端连接到对应的所述外涵道段的内壁,所述伸缩杆被设置成具有拉伸位置和压缩位置,当所述伸缩杆处于拉伸位置时,所述涵道的通径面积最大,当所述伸缩杆处于压缩位置时,所述涵道的通径面积最小。2. The duct structure with variable diameter according to claim 1, wherein the duct support structure comprises a double-layer shaft and a plurality of telescopic rods arranged on the outer wall of the double-layer shaft, each of the The second end of the telescopic rod is connected to the inner wall of the corresponding outer duct section, the telescopic rod is set to have a stretched position and a compressed position, when the telescopic rod is in the stretched position, the ducted The path area is the largest, and when the telescopic rod is in the compressed position, the path area of the duct is the smallest. 3.根据权利要求2所述的可变通径的涵道结构,其特征在于,所述伸缩杆在伸长位置时的长度为R,所述伸缩杆在压缩位置时的长度为r,所述外涵道段的内侧壁面曲率为r,所述内涵道段的内侧壁面曲率为R,所述伸缩杆的长度范围为R-r,所述涵道的通径面积范围为πR2-πr23. The variable diameter duct 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 length of the telescopic rod in the compressed position is r. The curvature of the inner side wall of the outer duct section is r, the curvature of the inner side wall of the inner duct section is R, the length of the telescopic rod is Rr, and the diameter area of the duct is πR 2 -πr 2 . 4.根据权利要求3所述的可变通径的涵道结构,其特征在于,当所述涵道处于最小面积时,所述外涵道段首尾相接,形成的通道截面为圆形,当所述涵道处于最大面积时,所述外涵道段和内涵道段首尾相接,形成的通道截面形状包括间隔分布的曲率为R的圆弧和曲率为r的圆弧。4. The duct structure with variable diameter according to claim 3, characterized in that, when the duct is in the smallest area, the outer duct sections are connected end to end, and the formed channel cross section is circular, and when When the duct is at the maximum area, the outer duct section and the inner duct section are connected end to end, and the formed channel cross-sectional shape includes spaced arcs with a curvature of R and arcs with a curvature of r. 5.根据权利要求2所述的可变通径的涵道结构,其特征在于,所述伸缩杆在伸长位置时的长度为R,所述伸缩杆在压缩位置时的长度为r,所述涵道的最大面积和最小面积的比为2:1,其中R:r为
Figure FDA0003492738350000011
所述外涵道段至少为八个。
5 . The variable diameter duct 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 length of the telescopic rod in the compressed position is r. 6 . The ratio of the maximum area to the minimum area of the duct is 2:1, where R:r is
Figure FDA0003492738350000011
There are at least eight external bypass sections.
6.根据权利要求1-5任意一项所述的可变通径的涵道结构,其特征在于,所述外涵道段和内涵道段均为两端开放的空心结构,所述内涵道段的两端边沿设有向外凸出的凸起部,所述外涵道段的两端边沿设有向内延伸的遮挡部,使内涵道段在外涵道段外壁滑动时不会脱出。6. The duct structure with variable diameter according to any one of claims 1-5, wherein the outer duct section and the inner duct section are hollow structures with open ends, and the inner duct section is a hollow structure with open ends. The two end edges of the outer duct section are provided with outwardly protruding protrusions, and the two ends of the outer duct section are provided with inwardly extending shielding parts, so that the inner duct section will not come out when the outer wall of the outer duct section slides. 7.根据权利要求1-5任意一项所述的可变通径的涵道结构,其特征在于,所述外涵道段和内涵道段的截面形状相同,使所述外涵道段能套设在所述内涵道段的外壁,所述外涵道段和内涵道段的曲率比为所述涵道于最大面积和最小面积时的半径比。7. The duct structure with variable diameter according to any one of claims 1-5, wherein the outer duct section and the inner duct section have the same cross-sectional shape, so that the outer duct section can be sleeved It is arranged on the outer wall of the inner channel section, and the curvature ratio of the outer channel section and the inner channel section is the radius ratio of the channel at the maximum area and the minimum area. 8.根据权利要求2所述的可变通径的涵道结构,其特征在于,所述伸缩杆包括内杆和外杆,所述外杆套设在所述内杆的外壁,所述内杆和外杆的截面为流线型。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 inner rod The cross-section of the outer rod is streamlined. 9.根据权利要求2所述的可变通径的涵道结构,其特征在于,所述双层轴包括内轴和外轴,所述内轴转动连接在所述外轴的内壁,所述伸缩杆固定在所述外轴的外壁。9 . The variable diameter duct structure according to claim 2 , wherein 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 shaft The rod is fixed to the outer wall of the outer shaft. 10.一种飞行器,其特征在于,包括权利要求1-9任意一项所述的可变通径的涵道结构。10. An aircraft, characterized in that it comprises the variable diameter duct structure according to any one of claims 1-9.
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