CN112298549A - Tilt rotor with bionic wavy leading edge and tilt rotor aircraft - Google Patents
Tilt rotor with bionic wavy leading edge and tilt rotor aircraft Download PDFInfo
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- CN112298549A CN112298549A CN202011197508.7A CN202011197508A CN112298549A CN 112298549 A CN112298549 A CN 112298549A CN 202011197508 A CN202011197508 A CN 202011197508A CN 112298549 A CN112298549 A CN 112298549A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
Abstract
In order to solve among the prior art the rotor that verts can't compromise the efficiency of the mode of cruising and the pulling force problem of the mode of hovering/VTOL, the utility model provides a rotor and the gyroplane that verts with bionical wavy leading edge had both guaranteed the efficiency of rotor under the mode of cruising that verts, can realize again that the rotor that verts is at the pulling force promotion under the mode of hovering/VTOL. Including the rotor blade that verts, the paddle leading edge of rotor blade that verts comprises bionical wavy leading edge and non-bionical wavy leading edge. The utility model provides a pair of rotor and gyroplane verts with bionical wavy leading edge verts, has both guaranteed the rotor efficiency under the mode of cruising that verts, can realize again that the rotor that verts is hovering/pulling force's promotion under the VTOL mode.
Description
Technical Field
The present disclosure relates to the field of tiltrotors, and more particularly, to a tiltrotor and tiltrotor aircraft having a bionic wavy leading edge.
Background
The tilt rotor aircraft is an aircraft integrating the advantages of two aircrafts, namely a fixed-wing aircraft and a helicopter, and two typical working modes of the tilt rotor aircraft are as follows: hover/vertical take-off and landing mode and cruise mode. In a hovering/vertical take-off and landing mode, the tilt rotor paddle is parallel to the ground, and pulling force is provided to overcome the gravity of the aircraft body, so that vertical take-off and landing and hovering are realized; in the cruising mode, the paddle disc is perpendicular to the ground, and mainly provides pulling force to overcome the aerodynamic resistance of the airplane body, so that high-speed cruising is realized. Therefore, the tiltrotor aircraft gets rid of the dependence of the fixed-wing aircraft on the runway, and simultaneously solves the problem that the helicopter cannot cruise at high speed.
In order to meet the requirement of great pulling force required by the hovering/vertical take-off and landing mode of the tilt rotor aircraft and to meet the requirement of high efficiency in the cruise mode, the design of the tilt rotor aircraft still faces significant challenges. The main contradictions of design are: in hover/vertical take-off and landing mode, the blades require large blade disk area, low blade twist and high blade tip speed; while in cruise mode, a small blade disc area, high blade twist and low tip speed are required. In fact, to ensure the efficiency of the tiltrotor in cruise mode, severe problems of flow separation, insufficient drag, etc. often occur in hover/vertical takeoff and landing mode.
At present, the traditional tilt rotor is usually designed in a compromise way based on momentum-blade theory, vortex theory, free wake model and other theories, or obtained after a large amount of CFD calculation optimization. The common methods are: a comprehensive evaluation index for simultaneously evaluating the performance of the rotary wing rotating in the hovering/vertical take-off and landing mode and the cruise mode is introduced, and the comprehensive evaluation index reaches an optimal value, namely partial efficiency of the cruise state is lost through a CFD and optimization algorithm combined method, so that the tension requirement of the rotary wing rotating in the hovering/vertical take-off and landing mode is met. However, the tilt rotor with compromise design or CFD optimization cannot really solve the pneumatic performance bottleneck, and the design idea is still to find a balance between the two flight modes, and the optimal performance cannot be achieved under the two flight modes. Moreover, a large amount of computing resources are consumed to design the tiltrotor by the CFD optimization method, which increases the design cost.
Disclosure of Invention
In order to solve at least one among the above-mentioned technical problem, this disclosure provides a rotor and a gyroplane that verts with bionical wavy leading edge, had both guaranteed the rotor efficiency under the mode of cruising that verts, can realize again that the rotor that verts is at the pulling force promotion under hover/VTOL mode.
The first aspect of this disclosure, the rotor that verts that has bionical wavy leading edge, including the rotor blade that verts, the blade leading edge of rotor blade that verts comprises bionical wavy leading edge and non-bionical wavy leading edge, bionical wavy leading edge is located the exhibition to 60% ~ 100% paddle height within range.
Optionally, the bionic wavy leading edge is located in a range of 60% -85% of the blade height in the span direction.
Optionally, the blade leading edges in the span-wise direction within the range of 60% -85% of the blade height are all the bionic wavy leading edges.
Optionally, the bionic wavy leading edge is located in a range of 60% -80% of the height of the blade in the span direction, and the leading edges of the blade in the range of 60% -80% of the height of the blade in the span direction are all the bionic wavy leading edges.
Optionally, the bionic wavy leading edge is located in a range of 70% -75% of the blade height in the span direction.
Optionally, the blade leading edges in the span-wise direction within the range of 70% -75% of the blade height are all the bionic wavy leading edges.
Optionally, the amplitude of the bionic wavy front edge is 5% -15% of the chord length of the local chlorophyll.
Optionally, the amplitude of the bionic wavy leading edge is 10% of the chord length of the local chlorophyll.
Optionally, the wavelength of the bionic wavy leading edge is one half of the average value of the chord lengths of the leaf elements within the height range of the blade where the bionic leading edge is located.
In a second aspect of the present disclosure, a tiltrotor aircraft includes a tiltrotor rotor having a biomimetic, undulating leading edge as described in any of the first aspects of the present disclosure.
The beneficial effects of the implementation of the present disclosure are as follows: tilt gyroplane including hover/hang down state and the two kinds of states of state of cruising, the technical scheme of this application has the particularity of two kinds of states to tilting gyroplane, through set up bionical wavy leading edge on tilting the rotor, the control paddle is at the big separation that flows of hover/hang down state, both guarantee the efficiency of rotor under the mode of cruising and can realize hovering/pulling force's promotion under the mode of VTOL, overcome tilting the rotor and can't compromise the efficiency of the mode of cruising and the pulling force's of the mode of hovering/VTOL problem.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
Fig. 1 is a schematic structural view of a tiltrotor rotor with a biomimetic contoured leading edge in an embodiment of the present disclosure;
fig. 2 is a graph comparing the pull force of an original tiltrotor rotor and a tiltrotor rotor with a bionic wavy leading edge under cruise conditions in an embodiment of the present disclosure;
FIG. 3 is a torque comparison plot of an original tiltrotor rotor versus a tiltrotor rotor having a biomimetic, undulating leading edge under cruise conditions in an embodiment of the present disclosure;
FIG. 4 is a graph of the surface friction and static pressure profile of an original tiltrotor rotor under a forward flight condition in an embodiment of the present disclosure;
FIG. 5 is a friction force profile and a static pressure profile of a surface of a tiltrotor rotor with a biomimetic contoured leading edge under a forward flight condition in an embodiment of the present disclosure;
FIG. 6 is a graph comparing pull force for a typical pitch condition for a pristine tiltrotor rotor with a biomimetic wavy leading edge in an embodiment of the present disclosure;
FIG. 7 is a graph comparing torque for a typical pitch operating condition for a pristine tiltrotor rotor and a tiltrotor rotor having a biomimetic, undulating leading edge in an embodiment of the present disclosure;
FIG. 8 is a plot of surface friction and static pressure of an original tiltrotor rotor during a heave condition in an embodiment of the present disclosure;
fig. 9 is a surface friction force curve and a static pressure distribution diagram of a tiltrotor with a bionic wavy leading edge under a drooping condition in the embodiment of the disclosure.
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to fig. 1, the tilt rotor with a bionic wavy leading edge comprises a tilt rotor blade 1, wherein the blade leading edge of the tilt rotor blade 1 is composed of a bionic wavy leading edge 2 and a non-bionic wavy leading edge 3.
Tilt gyroplane both including hover/hang down the state and including the state of cruising, technical scheme in this embodiment has the particularity of two kinds of states to the gyroplane that verts, through set up bionical wavy leading edge 2 on the rotor that verts, control paddle is at the big separation that flows of hover/hang down the state, can guarantee the efficiency of rotor under the mode of cruising and can realize the promotion of pulling force under hover/the mode of VTOL again, overcome and vert the rotor and can't compromise the efficiency of the mode of cruising and the pulling force's of hover/the mode of VTOL problem. Simultaneously, the tiltrotor that has bionical wavy leading edge in this application, its design need not to consume a large amount of computing resources, and manufacturing cost is also lower.
In an optional implementation method, the bionic wavy leading edge 2 is located in the range of 60% -100% of the height of the blade in the span direction, when the tilt rotor is in a vertical/hovering working condition, as the pitch is increased, the tip lutein is firstly in a deep stall state, the flow separation is initially induced at the blade tip and gradually expands towards the middle of the blade, and in order to reduce the damage of the bionic leading edge to the flow structure at the root part and the middle part of the blade, the bionic leading edge is not loaded below the 60% of the blade height in the embodiment mode.
In an optional embodiment, the bionic wavy leading edge 2 is located in the range of 60% -85% of the height of the blade in the span direction, and the part of the tilt rotor blade 1 above the 85% of the blade height is rapidly shortened due to the chord length of the blade, so that the bionic wavy leading edge 2 is not significant when being arranged, the bionic wavy leading edge 2 is located in the range of 60% -85% of the blade height in the span direction, the arrangement of the bionic wavy leading edge 2 can be reduced on the premise of ensuring the effect, and the production difficulty is reduced.
Referring to fig. 1, H is the blade height, a is the spanwise 60% blade height, B is the spanwise 85% blade height, and the range from a to B is the spanwise 60% -85% blade height range.
In an alternative embodiment, the bionic wavy leading edge is located in a span-wise range of 60% to 80% of the blade height. Further, preferably, the front edges of the blades in the span-wise 60% -80% of the height range of the blades are all bionic wavy front edges.
In an alternative embodiment, the biomimetic contoured leading edge is located in the span-wise 70% to 75% blade height range. Further, preferably, the front edges of the blades in the range of 70% -75% of the blade height in the span direction are all bionic wavy front edges.
In an alternative embodiment, the amplitude of the bionic wave front is 5% -15% of the chord length of the native leaflet, and the amplitude of the bionic wave front 2 is 10% of the chord length of the native leaflet, see fig. 1. The local chlorophyll chord length refers to the chord length of the prototype tilt rotor at the corresponding position.
In an alternative embodiment, referring to fig. 1, the wavelength of the bionic wavy leading edge 2 is half of the average value of the chord lengths of the chlorophyll within the blade height range where the bionic leading edge is located.
The application also discloses a tilt rotor aircraft which comprises the tilt rotor with the bionic wavy leading edge 2.
The following is an analysis of an example of a tiltrotor with a biomimetic contoured leading edge 2 of the present application. The original design parameters of a certain type of tilt rotor are shown in table 1:
table 2 original tilt rotor design parameter table
| Design parameters | Value of parameter |
| Cruising speed | 45m/s |
| Cruising tension | 200N |
| Number of |
3 |
| Wing profile | Clark Y |
| Radius of wheel hub | 0.025m |
| Blade radius | 0.35m |
| Rotational speed | 6300rpm |
Loading the bionic wavy leading edge 2 according to the original design parameters to form the tilting rotor with the bionic wavy leading edge 2 as shown in fig. 1, specifically, performing numerical simulation in numeca FINETM/Turbo, and comparing aerodynamic characteristics of the tilting rotor with the bionic wavy leading edge 2 with those of the original tilting rotor as follows:
fig. 2 and fig. 3 are aerodynamic characteristic comparison diagrams of an original tilt rotor and a tilt rotor with a bionic wavy leading edge 2 under a cruising condition, wherein fig. 2 is a tension comparison diagram of the original tilt rotor and the tilt rotor with the bionic wavy leading edge under the cruising condition, and fig. 3 is a torque comparison diagram of the original tilt rotor and the tilt rotor with the bionic wavy leading edge under the cruising condition, wherein mod refers to the tilt rotor with the bionic wavy leading edge 2, and ori refers to the original tilt rotor;
as can be seen from FIGS. 2 and 3, in the design state of the cruise condition (when the incoming flow is 45 m/s), the two tensile forces are basically consistent, and the torques are basically consistent, so that the efficiency is not lost in the cruise state.
Referring to fig. 4 and 5, fig. 4 is a surface friction line and a static pressure distribution diagram of an original tilt rotor under a forward flight condition; FIG. 5 is a surface friction line and a static pressure distribution diagram of a tilt rotor with a bionic wavy leading edge 2 under a forward flight condition;
as can be seen from fig. 4 and 5, in the cruise state at the design point, the static pressure distribution of the tiltrotor with the bionic wavy leading edge 2 is substantially the same as that of the original tiltrotor, and although the peak section and the valley section change according to the radius of the leading edge, the flow at the respective leading edge positions changes correspondingly, that is, the peak section of the tiltrotor with the bionic wavy leading edge 2 has the highest mach number lower than that of the original section, and the valley section increases the leading edge mach number due to the flow acceleration, but this only results in the redistribution of the pressure coefficient at the leading edge position, and does not affect the overall tension; meanwhile, the friction line loaded on the blade surface of the bionic wavy leading edge 2 is slightly bent, does not evolve serious backflow or transverse flow, and hardly changes the flow state of the blade. To sum up, the bionic wavy leading edge 2 in the application can not lose the efficiency of the cruise state of the tilt rotor, and the important significance is realized on ensuring the voyage and the economy of the tilt rotor aircraft.
Referring to fig. 6 and 7, fig. 6 and 7 are graphs comparing aerodynamic characteristics of an original tiltrotor and a tiltrotor with a bionic wavy leading edge under a typical pitch condition (a 21-degree pitch hover/vertical take-off mode), wherein fig. 6 is a graph comparing drag force of the original tiltrotor and the typical pitch condition with the bionic wavy leading edge, and fig. 7 is a graph comparing torque of the original tiltrotor and the tiltrotor with the bionic wavy leading edge under the typical pitch condition;
as can be seen from fig. 6 and 7, in the hover/vertical take-off mode, the tilt rotor loaded with the bionic wavy leading edge 2 can greatly increase the pulling force. Especially at a forward flight speed of 20m/s, loading the biomimetic contoured leading edge 2 increases the pulling force from 567N to 579N.
FIG. 4 is a diagram of the surface friction line and static pressure distribution of the original tilt rotor under the vertical working condition; fig. 5 is a surface friction line and a static pressure distribution diagram of a tilt rotor with a bionic wavy leading edge under a forward flight condition.
Fig. 8 is a surface friction force line and a static pressure distribution diagram of an original tilt rotor wing under a vertical working condition, and fig. 9 is a surface friction force line and a static pressure distribution diagram of a tilt rotor wing with a bionic wavy leading edge under a vertical working condition, wherein a large-scale flow separation has occurred on the surface of the prototype tilt rotor wing, and a separation point has reached a front edge of a lutein. Flow attachment is maintained over a peak section chord length of more than 60%, and the separation point is greatly retarded rearwardly, which also ensures sufficient acceleration of flow at the leading edge. The flow deterioration of the trough cross section is improved, the separation area at the leading edge is reduced, and the forward flow is maintained in a part of the chord-wise middle area, but the flow is separated again at the trailing edge. And the friction force line of the blade surface is integrally inspected to know that when the flow separation envelope curve of the prototype tilting rotor blade in the range of 60% of the length close to the blade tip reaches the position of the front edge, the flow topology of the blade loaded with the bionic wavy front edge in the area loaded with the bionic wavy front edge is obviously improved, and the flow of the blade with the peak section in the range of 50% of chord length on average presents the characteristic of downstream. In conclusion, the tilting rotor wing with the bionic wavy leading edge can restrain large flow separation under the hovering working condition through the bionic wavy leading edge, and the flow state is improved, so that the pulling force of the hovering working condition is improved.
From the bionic angle, the novel design idea of loading the bionic wavy leading edge is extracted, the reasonable bionic wavy leading edge is loaded on the original tilt rotor blade, the efficiency of the tilt rotor in a cruise mode is guaranteed, the tension is greatly improved in a hovering/vertical take-off and landing mode, and specific test data can be shown in table 2.
TABLE 2
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.
Claims (10)
1. The tilt rotor with the bionic wavy leading edge is characterized by comprising tilt rotor blades, wherein the blade leading edges of the tilt rotor blades are composed of the bionic wavy leading edge and a non-bionic wavy leading edge.
2. The tiltrotor rotor with a biomimetic contoured leading edge according to claim 1, wherein the biomimetic contoured leading edge is located in a span-wise range of 60% to 85% blade height.
3. A tiltrotor rotor with a biomimetic contoured leading edge according to claim 2, wherein the blade leading edges in a span-wise range of 60% to 85% of blade height are the biomimetic contoured leading edges.
4. The tiltrotor rotor with a biomimetic contoured leading edge according to claim 1, wherein the biomimetic contoured leading edge is located in a span-wise range of 60% to 80% of blade height, and the blade leading edges in a span-wise range of 60% to 80% of blade height are the biomimetic contoured leading edges.
5. The tiltrotor rotor with a biomimetic contoured leading edge according to claim 1, wherein the biomimetic contoured leading edge is located in a span-wise range of 70% to 75% blade height.
6. A tiltrotor rotor with a biomimetic contoured leading edge according to claim 5, wherein the blade leading edges in a span-wise range of 70% to 75% of blade height are the biomimetic contoured leading edges.
7. The tiltrotor rotor with a biomimetic contoured leading edge according to claim 1, wherein the amplitude of the biomimetic contoured leading edge is 5% -15% of a native chord length.
8. The tiltrotor rotor with a biomimetic contoured leading edge according to claim 7, wherein an amplitude of the biomimetic contoured leading edge is 10% of a native chord length.
9. The tiltrotor rotor with a biomimetic contoured leading edge according to claim 1, wherein the wavelength of the biomimetic contoured leading edge is one half of an average of chord lengths of the blading over a blade height range over which the biomimetic leading edge is located.
10. A tiltrotor aircraft comprising a tiltrotor rotor having a biomimetic contoured leading edge according to any of claims 1-9.
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| CN202011197508.7A CN112298549A (en) | 2020-10-30 | 2020-10-30 | Tilt rotor with bionic wavy leading edge and tilt rotor aircraft |
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Cited By (1)
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Application publication date: 20210202 |