CN110525679B - Hypersonic embedded waverider design method - Google Patents
Hypersonic embedded waverider design method Download PDFInfo
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- CN110525679B CN110525679B CN201910801998.8A CN201910801998A CN110525679B CN 110525679 B CN110525679 B CN 110525679B CN 201910801998 A CN201910801998 A CN 201910801998A CN 110525679 B CN110525679 B CN 110525679B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
Abstract
The invention provides a hypersonic embedded waverider design method, which is based on a partial decoupling thought. The method provided by the invention breaks through the scope that the fuselage and the wings are required to be subjected to the integrated spanwise design based on the flow field with the same shock wave intensity in the traditional design method, and the fuselage is taken as a high-volume component, and the wings are taken as high-lift-drag-ratio components, so that the fuselage can be designed based on the shock wave with higher intensity, and even the design of a waverider is not considered. And the wings construct an embedded waverider reference flow field based on the fuselage flow field to carry out the design of the waverider. The design method of the invention can obtain the aerodynamic layout of the hypersonic flight vehicle which simultaneously considers high volume ratio and high lift-drag ratio.
Description
Technical Field
The invention belongs to the field of design of hypersonic aircrafts, and particularly relates to a hypersonic embedded waverider design method.
Background
The layout of the waverider is a layout form of a hypersonic aircraft which can enable shock waves to be attached to a front edge, enable high-pressure gas after the waves to be located below an engine body and avoid leakage, and compared with the layouts of a wing body assembly, a lifting body and the like, the layout has a higher lift-drag ratio, so that the layout has received great attention of researchers in various countries.
Since Nonweiler proposed the concept of waverider in 1959, various methods for designing waverider have been proposed. Generally, the basic idea of the conventional design method of the waverider is to construct a basic body, obtain a shock wave flow field generated by the basic body under the design condition, and then obtain the shape of the waverider by using methods such as streamline tracing and the like in the shock wave flow field. According to the difference of basic bodies, the existing wave-multiplying body design method mainly comprises wedge-shaped flow field wave-multiplying bodies, conical flow field wave-multiplying bodies, wedge-outer cone/inner cone mixed flow field wave-multiplying bodies, fixed/variable wedge angle wave-multiplying bodies and other design methods.
The traditional design method of the waverider is a method for carrying out integrated design on the fuselage and the wings in the spanwise direction in the basic flow field with the same shock wave intensity. The fuselage and the wings are simultaneously obtained in the shock flow field of a given basic body, and the overall appearance is generally a flat body. Although the wave rider body profile has a high lift-to-drag ratio, the flat body profile results in a low volume fraction. In fact, from the perspective of pneumatic design, the high lift-drag ratio requires that the external shape of the aircraft has a smaller object angle, and a larger object angle is desired for a high volume ratio, and there is a contradiction between the two, and the traditional design method of the waverider adopts an integrated design concept, so that the obtained external shape is difficult to solve the contradiction of the sizes of the object angles, and thus, the high volume ratio and the high lift-drag ratio are difficult to be considered.
In order to solve the contradiction between the high volume ratio and the high lift-drag ratio of the waverider, an improvement idea is provided. Tpeak et al disclose a design method of waverider using a reference flow field of a tip-wound Von Karman curve revolved body in the patent, "a design method of waverider based on a reference flow field of a tip-wound Von Karman curve revolved body", CN104192302A ", the basic idea is to modify the basic body shape and obtain a waverider using a conventional design method of the waverider, so that the waverider has a higher volume ratio than a conventional cone guided waverider. In essence, the method is still the traditional integrated multiplier design method. In addition, the patent of willow et al discloses a method for designing a large-volume high-lift-ratio ridge osculating pyramid wave-rider, CN106428620A, which combines a conventional osculating pyramid wave-rider with a tapered volume.
It can be seen from the analysis of the conventional design method of the wave-rider and the design methods in the two publications that the existing design method of the wave-rider is designed in the whole machine shape in the shock wave flow field generated by the basic body, the basic body is only used for generating the shock wave flow field and is independent of the shape of the wave-rider, and the shape of the wave-rider is obtained by tracing the flow lines in the flow field. The previous analysis shows that the traditional design method of the waverider has inherent contradiction in the integrated design idea of the spanwise direction, and is difficult to consider high volume ratio and high lift-drag ratio.
Disclosure of Invention
The invention provides a hypersonic embedded waverider design method based on a partial decoupling design idea. Because the traditional spanwise integrated design method has internal contradiction, the invention respectively designs the fuselage and the wings of the aircraft, the fuselage ensures high volume ratio, and the design can be carried out by adopting the traditional pointed cone shape and the like; the wings ensure high lift-drag ratio, and a wave-rider design method is still adopted during design. However, unlike the conventional method, the flow field on which the wave-rider design is based is not the shock wave flow field generated by the conventional basic body, but is based on the shock wave flow field generated by the fuselage. By the method, the wing can be ensured to have good wave-rider characteristics.
Compared with the traditional method, the method provided by the invention breaks through the category that the fuselage and the wings are designed based on the flow field with the same shock wave intensity in the traditional design method, the fuselage is regarded as a high-volume component, and the wings are regarded as high-lift-drag ratio components, so that the fuselage can be designed based on the shock wave with higher intensity, and even the design of the waverider is not considered; and the wings construct an embedded waverider reference flow field based on the fuselage flow field to carry out the design of the waverider. In essence, the present invention differs from conventional design methods in the functionality of the basic body. The basic body is not part of the final shape in the conventional method, but is a part of the final shape in the method proposed by the present invention. The member may be a member having no waverider characteristics or a member having waverider characteristics. Therefore, the design method provided by the invention can obtain the aerodynamic layout of the hypersonic aircraft which simultaneously considers high volume ratio and high lift-drag ratio or other characteristics.
The specific technical scheme of the invention is as follows:
a hypersonic embedded waverider design method comprises the following steps:
(1) firstly, designing the appearance of a machine body according to the volume ratio or other requirements;
(2) the machine body is used as a basic body, a winding flow field of the basic body is obtained by numerical simulation, and the winding flow field is used as a basic flow field of the embedded wave-multiplying body;
(3) selecting a proper embedded wave-multiplying body front edge line, wherein the front edge line is intersected with a machine body, generating streamlines passing through discrete points on the front edge line in a basic body circumfluence flow field by using a streamline tracing technology, cutting the streamlines at a specified flow direction position, and generating the upper surface of the embedded wave-multiplying body by taking the cut streamlines as molded lines;
(4) giving the distribution of object plane angles of the lower surface near the leading edge line, and arranging the lower surface molded lines meeting the wave multiplication conditions along the leading edge line so as to generate the lower surface of the embedded wave multiplier;
(5) since a given leading edge line intersects the fuselage, the resulting embedded waverider also intersects the fuselage, which combine to form the aircraft profile.
Further, the leading edge line is a curve or a discrete point column.
Further, the front edge line is a single-section straight line or a multi-section straight line.
Further, the embedded wave rider is a wing.
Further, the fuselage outer shape may be an elongated body outer shape having no waverider characteristics, or an outer shape having waverider characteristics.
Further, the lower surface profile line wedge angle in the step (4) meets the object plane angle of the wave rider condition.
Further, the lower surface molded line wedge angle delta in the step (4)lsIs 6 deg..
Further, the design plane of the lower surface molded line meeting the wave-rider condition in the step (4) is a vertical plane parallel to the incoming flow velocity direction.
Compared with the prior art, the invention has the following beneficial effects:
(1) compared with the traditional design method of the waverider, the design concept of partial decoupling is adopted, so that the high volume rate requirement and the high lift-drag ratio characteristic of the aircraft can be considered at the same time. The basic body in the design method of the invention is the aircraft fuselage, and the design can be carried out according to the volume fraction requirement when the appearance is given.
(2) The invention adopts a streamline tracing technology to generate the upper surface of the waverider. Compared with the traditional method, the method adopts the streamline tracing technology to generate the upper surface in the shock wave flow field generated by the basic body, and can avoid the adverse effect on the lift-drag ratio caused by the additional shock wave generated on the upper surface of the waverider.
(3) The invention adopts a mode of arranging the lower surface molded lines meeting the waverider conditions along the leading edge line to generate the lower surface of the waverider. In the traditional method, a streamline tracking technology is adopted, and a streamline in a shock wave flow field is tracked from a leading edge line to the downstream to serve as a lower surface profile of a waverider. Compared with the traditional method, the design margin of the invention is larger, the molded line of the lower surface of the wave rider can be designed at will within the range of meeting the wave rider condition, and the invention is more favorable for realizing the requirement of high lift-drag ratio or simultaneously considering the requirements of other aspects.
Drawings
Fig. 1 is a schematic external view of the fuselage of the present invention.
FIG. 2 is a schematic view of the position of the leading edge line of the airfoil of the present invention.
FIG. 3 is a schematic diagram of the present invention of generating an upper surface of an airfoil using a streamline tracing method.
Fig. 4 is a schematic diagram of a fuselage and embedded waverider wing assembly of the present invention.
Fig. 5 shows a calculation result of the designed lift-to-drag ratio at mach number 5.0 in example 1 of the present invention.
FIG. 6 is a schematic view of a profile designed for a wing span exceeding the bow shock range of the fuselage.
Reference numerals:
1-leading edge line, 2-dividing line, 3-trailing edge line
Detailed Description
The invention will be described in more detail with reference to the following figures and examples, but the scope of the invention is not limited thereto.
Example 1
The aerodynamic layout design of the embedded wave-rider aircraft is developed by taking the incoming flow Mach number of 5.0 and the attack angle of 4 degrees as the design state.
First, the fuselage outline is given as the basic body. Since the fuselage mainly considers the high volume rate characteristic, the fuselage shape is typically an elongated body shape, the fuselage cross-sectional shape is a closed curve with a supercircle, the fuselage head side is a tangent oval, and the designed fuselage shape is as shown in fig. 1. Then, an embedded wave rider leading edge line is given, the leading edge line is a single-section straight line, and water located at the half height of the bodyIn-plane. The sweepback angle of the leading edge line is 60 degrees, the distance from the most forward point to the top point of the head of the airplane body is 4.3D, and D is the diameter of the airplane body. Only the situation that the embedded wave rider is completely positioned in the shock wave flow field of the head of the fuselage is considered, and the maximum expansion position of the leading edge line is the local shock wave expansion position zs0.95 times of. The positional relationship of the leading edge line to the fuselage is shown in fig. 2.
The upper surface of the embedded multiplicative wing is obtained by taking streamlines along the leading edge in the fundamental flow field and making up the flow surface, as shown in fig. 3. In order to increase the wing area, the wing adopts a trapezoidal plane shape. Wherein the chord length of the wing root is equal to the projection length of the leading edge line in the longitudinal axis direction of the fuselage, and the tip ratio of the given wing (the ratio of the chord length of the wing tip to the chord length of the wing root) is 0.4. Meanwhile, the upper wing surface is divided into a front part and a rear part, and the interface of the upper wing surface is a vertical plane where the connecting line of the chord midpoint of the wing root and the chord midpoint of the wing tip is located; the front half is created by the flow surface passing the leading edge line and the back half is the curved surface formed by the boundary line (intersection of flow surface and interface surface) and the wing trailing edge line (obtained by designing the lower wing surface).
The design plane of the profile arrangement on the lower surface of the wing is a vertical plane parallel to the incoming flow velocity direction, and then the profile wedge angle is designed in the design plane, which is equivalent to directly giving the object plane angle of the lower wing surface. In fact, the design plane may take other forms, such as a vertical plane perpendicular to the leading edge line as the design plane. In this embodiment, the lower airfoil profile wedge angle δ is givenlsAt 6 deg., then the lower airfoil surface can be produced. The lower airfoil trailing edge line, after being obtained, may together with the upper airfoil boundary line constitute the rear half of the upper airfoil. The resulting waverider airfoil is shown in fig. 4, and each section (airfoil) of the airfoil in the spanwise direction is triangular.
The designed profile was numerically simulated to obtain curves of the lift-drag ratio of the designed profile with and without adhesion as a function of the angle of attack, respectively, as shown in fig. 5. It can be seen that the full machine sticking lift to drag ratio is at a maximum of about 4.02 at an angle of attack of 8 deg., and the no sticking lift to drag ratio is at a maximum of about 4.91 at an angle of attack of 6 deg.. The lift-drag ratio of the wing reaches the maximum at 4 degrees under both sticky and non-sticky conditions, the sticky maximum lift-drag ratio is about 6.01, and the non-sticky maximum lift-drag ratio is about 7.35.
Example 2
The design method is characterized in that the incoming flow Mach number is 5.0, the attack angle is 4 degrees, the situation that the wing span is larger than the range of the nose shock wave of the fuselage is considered, namely, part of the wings are located in the range of the nose shock wave of the fuselage, and part of the wings are located outside the range of the nose shock wave of the fuselage, and the design of the embedded type wave-rider wing is carried out.
The fuselage adopted the fuselage profile obtained in example 1. The leading edge line of the wave-rider wing is two linear segments which are swept back in sections. Wherein, the sweepback angle of the inner straight-line segment close to the fuselage is 65 degrees, and the whole straight-line segment is positioned in the flow field behind the shock wave of the fuselage head; the sweep angle of an outer straight line segment far away from the fuselage is 52 degrees, and the straight line segment crosses the head of the fuselage in the spanwise direction to enter free incoming flow.
The upper and lower airfoil surfaces of the wing are produced in the same manner as in example 1. For the upper airfoil surface, the streamline is tracked in the head shock wave of the fuselage and in the free incoming flow respectively and forms a flow surface, and the flow surface is the front half part of the upper airfoil surface. For the lower airfoil surface, still taking the vertical plane parallel to the incoming flow velocity direction as the design plane, the lower airfoil surface profile wedge angle delta is givenlsAt 6 deg., thereby creating a lower airfoil. Meanwhile, the rear half of the upper airfoil surface is obtained by connecting the boundary line of the upper airfoil surface and the rear edge line of the lower airfoil surface. The resulting profile is shown in fig. 6.
The design method provided by the invention takes the basic body as a part of the aircraft in the design of the embedded wave-rider, so that the part can be designed to meet the requirements of high volume ratio and the like, and the requirement of high lift-drag ratio is met by the wave-rider part, thereby realizing high volume ratio and high lift-drag ratio.
The foregoing are only some embodiments of the invention. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the inventive concept thereof, and these changes and modifications can be made without departing from the spirit and scope of the invention.
Claims (6)
1. A hypersonic embedded waverider design method comprises the following steps:
(1) firstly, designing the appearance of a machine body according to the volume ratio; (2) taking the machine body as a basic body, obtaining a winding flow field of the basic body by utilizing numerical simulation, and taking the winding flow field as a basic flow field of the embedded wave-multiplying body; (3) selecting a proper embedded wave-multiplying body leading edge line, wherein the leading edge line is intersected with the machine body, generating streamlines passing through discrete points on the leading edge line in a basic body flow-surrounding field by using a streamline tracking technology, cutting off the streamlines at a specified flow direction position, and generating the upper surface of the embedded wave-multiplying body by taking the cut streamlines as molded lines; (4) giving the distribution of object plane angles of the lower surface near the leading edge line, and arranging the lower surface molded lines meeting the wave multiplication conditions along the leading edge line so as to generate the lower surface of the embedded wave multiplier; (5) because the given leading edge line is intersected with the fuselage, the generated embedded wave multiplier is also intersected with the fuselage, and the embedded wave multiplier and the fuselage are combined into the appearance of the aircraft;
the front edge line is a single-section straight line or a multi-section straight line.
2. The design method of claim 1, wherein the embedded waverider is an airfoil.
3. The design method according to claim 1, wherein the body profile in step (1) is an elongated body profile having no waverider characteristics or an elongated body profile having waverider characteristics.
4. The design method according to claim 1, wherein the lower surface profile wedge angle in the step (4) is an object surface angle satisfying a wave-rider condition.
5. The design method according to claim 1, wherein the lower surface profile line wedge angle δ in step (4)lsIs 6 deg..
6. The design method according to claim 1, wherein the design plane of the lower surface profile satisfying the wave-rider condition in the step (4) is a vertical plane parallel to the incoming flow velocity direction.
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| CN111994264B (en) * | 2020-07-15 | 2021-10-15 | 中国科学院力学研究所 | Hypersonic aircraft and design method thereof |
| CN111907731B (en) * | 2020-08-19 | 2022-03-04 | 中国航天空气动力技术研究院 | Wing rudder surface variable parameter experiment simulation method |
| CN114044163B (en) * | 2021-10-27 | 2023-02-10 | 南京航空航天大学 | Inverted wave carrier head and supersonic rocket sled with same |
| CN114771862A (en) * | 2022-03-26 | 2022-07-22 | 中国空气动力研究与发展中心空天技术研究所 | Modular design method for hypersonic cruise aircraft |
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| US6634594B1 (en) * | 2002-05-03 | 2003-10-21 | The Boeing Company | Hypersonic waverider variable leading edge flaps |
| CN103049597B (en) * | 2012-11-27 | 2016-04-20 | 中国人民解放军国防科学技术大学 | The boundary-passivated Waverider of mutative scale and passivating method thereof |
| CN103010454A (en) * | 2012-11-27 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Wave rider aircraft with redundant pneumatic distribution and control method thereof |
| CN107140180B (en) * | 2017-05-17 | 2019-07-23 | 北京航空航天大学 | Hypersonic rider double-vane aerodynamic arrangement |
| CN107336842B (en) * | 2017-06-07 | 2020-05-26 | 北京航空航天大学 | Hypersonic wave-rider canard aerodynamic layout method |
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