CN106777828B - Internal and external wave multiplication integrated design method with controllable wall surface pressure - Google Patents

Internal and external wave multiplication integrated design method with controllable wall surface pressure Download PDF

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CN106777828B
CN106777828B CN201710061160.0A CN201710061160A CN106777828B CN 106777828 B CN106777828 B CN 106777828B CN 201710061160 A CN201710061160 A CN 201710061160A CN 106777828 B CN106777828 B CN 106777828B
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waverider
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air inlet
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CN106777828A (en
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施崇广
李怡庆
尤延铖
周驯黄
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Xiamen University
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Abstract

An internal and external waverider integrated design method with controllable wall surface pressure relates to a hypersonic aerocraft in a near space. The projection of the leading edge capture profile on the design cross-section and the desired pressure profile are specified according to design requirements. And designing the projection of the front edge capturing molded line on a top view, and solving the corresponding compression molded line by using an inverse characteristic line method according to given pressure distribution. And obtaining the compression molded surface integrating the inner and outer waverider in the corresponding axisymmetric outer compression flow field or axisymmetric inner contraction flow field through coordinate transformation according to the compression molded line and the included angle between the tangent plane and the symmetric surface. And designing the projection of the outlet section of the three-dimensional inward turning air inlet channel and the projection of the lip of the three-dimensional inward turning air inlet channel on the design section, and obtaining the three-dimensional configuration of the lip of the three-dimensional inward turning air inlet channel according to the shock wave relation. And carrying out geometric construction on the internal and external waverider integrated aircraft on the basis of the compression molded surface.

Description

Internal and external wave multiplication integrated design method with controllable wall surface pressure
Technical Field
The invention relates to a hypersonic aerocraft in a near space, in particular to an internal and external waverider integrated design method with controllable wall surface pressure.
Background
The development of the adjacent space aircraft relates to national safety and peaceful space utilization, and is one of the focuses of the international competition for space-capturing technology at present. The world's strong countries, represented by The United states and Russia, have been vigorously developing their hypersonic flight development programs (Joseph, M.H, James S.M. Richard C.M., The X-51A Scramjet Engine flight optimization Program,15thAIAA International Space Planes and hypersonic systems and Technologies Conference, 2008). Since the last 60 years, a great deal of research fully shows that the integrated design of an aircraft and a propulsion system is the key to realizing hypersonic flight, and the integration of an aircraft body and the propulsion system is the integration of an aircraft and an air inlet channel. From the current research hotspots and trends, the design of an external waverider aircraft and the research of a three-dimensional internal contraction air inlet channel become recognized advanced design methods and leading technologies in two fields.
Air intake ducts are a major component in the propulsion system of hypersonic aircraft. It is located in the front of the aircraft, and is directly connected with the front body of the hypersonic aircraft, and plays the role of compressing incoming flow and providing high-energy airflow as much as possible for the downstream. Through long-term development, a series of hypersonic air inlet forms are proposed, which mainly comprise: the two-dimensional air inlet, the axial symmetric air inlet and the lateral pressure air inlet are researched according to the design method, the flow characteristic, the working characteristic, the engineering design research and the like of the two-dimensional air inlet, the axial symmetric air inlet and the lateral pressure air inlet. In addition, foreign researchers also provide a series of three-dimensional internally-contracted hypersonic air inlet design ideas and schemes. Such as: streamlining the Busemann Inlet channel proposed by the university of john hopkins f.s.billig et al (Brien, t.f.and colville, j.r.analytical Computation of Leading Edge traversal efficiency on exchanged bulkmann insert Performance, AIAA paper, 2007); the "Funnel" type inlet concept proposed by P.K.Ajay et al of Astrox corporation, USA (Billing, F.S. and Kothari, A.P., Streamline training: Technique for Designing Hypersonic Vehicles, Journal of Propulsion and Power, Vol.16, No.3,2000, pp.465-471); the M.K.Smart et al, the American space and aviation research center, teaches the concept of smoothly converting a Rectangular Inlet to an oval outlet (Smart, M.K.and Trexler, C.A.Mach4Performance of a Fixed-Geometry Hypersonic Inlet with Rectangular-to-elastic Shape Transition,41st AIAAAerospace Sciences Meeting & inhibition, 2002), and the like. In China, scholars such as Yongcheng and the like firstly apply the outer-flow waverider theory to the research of the inner flow of the air inlet, and a three-dimensional inner-contraction hypersonic air inlet called an inner waverider is provided. The numerical simulation and the high enthalpy wind tunnel test prove that: in a design state, the air inlet can capture incoming flow at full flow; in a non-design state, the air inlet channel can obviously improve the working capacity of low Mach number by the automatic overflow of the inlet, thereby having better overall characteristics.
Although various studies have made significant progress in the field of hypersonic aircraft and hypersonic air inlet duct research, component performance is also constantly being improved. However, to date, no effective method has been found by researchers to control the wall pressure distribution. And the wall pressure plays a crucial role in improving the performance of the aircraft. Meanwhile, scientific research personnel also do not obtain the high-performance integrated device which is suitable for the external waverider aircraft and the three-dimensional internal rotation air inlet channel, so that the combination of the external waverider aircraft and the three-dimensional internal rotation air inlet channel realizes the maximization of the overall performance of the aircraft. Because of the different working requirements, for a long time, integration has been considered to be the design of two high performance components separately, which are coherently superimposed and compromised. But the integration problem is by no means so simple. Mark Lewis, a first scientist of the American military hypersonic program, in the literature (M.Lewis, A hypersonic propulsion aircraft Integration Overview,39th AIAA and ASME and SAE and ASEE Joint propulsion Conference and inhibition, 2003) indicates that although it is easy to design an aircraft with a lift-drag ratio of 7-8, the lift-drag ratio of the existing hypersonic aircraft matched with an engine is only 3.8 at the maximum. The wave-rider air inlet channel also plays a crucial role in improving the performance of the aircraft. Therefore, one of the problems restricting the overall performance of the hypersonic system at present is that an internal and external waverider integrated design method with controllable wall pressure is lacked.
Disclosure of Invention
The invention aims to provide an internal and external wave multiplication integrated design method with controllable wall surface pressure.
The invention comprises the following steps:
1) the projection of the leading edge capture profile on the design cross-section and the desired pressure profile are specified according to design requirements.
2) And designing the projection of the front edge capturing molded line on a top view, and solving the corresponding compression molded line by using an inverse characteristic line method according to given pressure distribution.
3) And obtaining the compression molded surface integrating the inner and outer waverider in the corresponding axisymmetric outer compression flow field or axisymmetric inner contraction flow field through coordinate transformation according to the compression molded line and the included angle between the tangent plane and the symmetric surface.
4) And designing the projection of the outlet section of the three-dimensional inward turning air inlet channel and the projection of the lip of the three-dimensional inward turning air inlet channel on the design section, and obtaining the three-dimensional configuration of the lip of the three-dimensional inward turning air inlet channel according to the shock wave relation.
5) And carrying out geometric construction on the internal and external waverider integrated aircraft on the basis of the compression molded surface.
In step 5), the geometric configuration comprises an upper aircraft surface, a lower aircraft surface, an isolation section rearward and equal straight pull and the like.
The internal and external waverider integrated scheme with controllable wall pressure is provided with an external waverider aircraft and a three-dimensional internal rotation air inlet channel; the three-dimensional inward-turning air inlet is provided with a three-dimensional inward-turning air inlet compression profile, a three-dimensional inward-turning air inlet lip, a three-dimensional inward-turning air inlet shoulder, a three-dimensional inward-turning air inlet isolating section and a three-dimensional inward-turning air inlet transverse overflow port; the external waverider aircraft and the three-dimensional internal rotation air inlet channel depend on a binary plane wedge to guide the wavebands to be connected and transited, the three-dimensional internal rotation air inlet channel profile is flatly rotated at the shoulder of the three-dimensional internal rotation air inlet channel to enter the three-dimensional internal rotation air inlet channel isolation section, and the transverse overflow port is arranged at the transition position where the external waverider aircraft and the three-dimensional internal rotation air inlet channel compression profile are connected.
The invention has the following advantages:
the internal and external waverider integrated aircraft with controllable wall surface pressure generated by the invention simultaneously considers the performance of the external waverider aircraft and the three-dimensional internal rotation air inlet channel, and realizes the control of the wall surface pressure of the waverider. Wherein, the external waverider aircraft has higher lift drag characteristic. The air inlet channel is a three-dimensional inward-rotation air inlet channel, the pressure of the wall surface of the wave rider is controlled, the full-flow capture of incoming flow is guaranteed, the thrust of the engine is increased, and meanwhile the outflow resistance is reduced; and the overflow can be automatically adjusted under the condition of low Mach number, so that the working Mach number range of the air inlet channel is widened. The natural transition of the inner waverider part and the outer waverider part is realized by the aid of the plane wedge guided waverider transition section with infinite curvature radius, the total performance of the waverider device with the high lift-drag ratio is guaranteed not to be sacrificed due to coupling with an air inlet device, and accordingly the work of the air inlet is excellently finished under the condition that the lift-drag ratio is not reduced.
Drawings
Fig. 1 is a front view of a compression profile of an internal and external wave multiplication integrated scheme with controllable wall pressure.
FIG. 2 is a top view of the flow direction pressure distribution and compression profile of the internal and external waverider integrated scheme with controllable wall pressure.
FIG. 3 is a schematic diagram of the solution of the inverse eigen-curve method.
Fig. 4 is a schematic bottom view of an internal and external waverider integration scheme with controllable wall pressure.
FIG. 5 is a schematic view of a half-section structure of an internal and external waverider integration scheme with controllable wall pressure.
Fig. 6 is a schematic diagram of the overall structure of the internal and external waverider integrated scheme with controllable wall pressure.
The labels in the figure are: 1 represents a symmetrical section of an internal and external waverider integrated scheme with controllable wall surface pressure, 2 represents a projection of a three-dimensional internal rotation air inlet channel front edge capture molded line on a design section, 3 represents a projection of an external waverider front edge capture molded line on the design section, 4 represents a binary plane waverider section, 5 represents a local curvature center of an external waverider shock curve, 6 represents an external waverider section, 7 represents a discrete point of the front edge capture molded line on the design plane, 8 represents a local curvature center of an internal waverider shock curve, 9 represents an internal waverider section, 10 represents an external waverider lower surface molded line, 11 represents a three-dimensional internal rotation air inlet channel compression molded line, 12 represents an external waverider compression molded line, 13 represents a three-dimensional internal rotation air inlet channel compression molded line, 14 represents an external waverider compression molded line, 15 represents a flow direction pressure distribution of the internal and external waverider integrated scheme with controllable wall surface, 16 represents a two-dimensional plane compression section, 17 represents a compression profile of an external waverider flow direction section on an external waverider section osculating plane 6, 18 represents a compression profile of a three-dimensional internal rotation air inlet flow direction section on an internal waverider section osculating plane 9, 19 represents a three-dimensional internal rotation air inlet transverse overflow port, 20 represents a three-dimensional internal rotation air inlet lip, 21 represents a three-dimensional internal rotation air inlet shoulder profile, 22 represents a three-dimensional internal rotation air inlet isolation section, 23 represents a three-dimensional internal rotation air inlet isolation section outlet, 24 represents an external waverider aircraft and a three-dimensional internal rotation air inlet front edge, 25 represents an external waverider aircraft, and A represents A1And A2At the corresponding point of the pressure distribution curve 15, B represents B1And B2At the corresponding point of the pressure distribution curve 15, C represents C1And C2D represents D at the corresponding point of the pressure distribution curve 15AAnd DCAt the corresponding point, A, of the pressure distribution curve 151And A2Representing the starting point of the compression molded line of the three-dimensional inward turning air inlet channel and B1And B2Representing the starting point of the two-dimensional plane-by-band compression molded line, C1And C2Representing external waverider compression profilesStarting point, DARepresenting the end point of the compression molded line of the three-dimensional inward-turning air inlet channel, DCAnd E represents the intersection point of the characteristic line of the right row in the outer compression axial symmetric flow field and the shock wave, and F represents the intersection point of the characteristic line of the right row in the inner compression axial symmetric flow field and the shock wave.
Detailed Description
The following examples will further illustrate the present invention with reference to the accompanying drawings.
Referring to fig. 1 to 6, the internal and external waverider integrated design method with controllable wall pressure mainly comprises the following implementation steps:
(1) and the projection of the leading edge capture profile on the design section and the required pressure distribution are specified according to the design requirements. The projection of the front edge capturing molded line on the design section is divided into an external multiplication wave band and an internal multiplication wave band which respectively correspond to a curve 3 and a curve 2, the curvature of each discrete point on the curve and the curvature center are solved, and the external multiplication wave band and the internal multiplication wave band are transited through a binary plane multiplication wave band 16 with the curvature of infinity. Taking the external multiplication wave band as an example, the discrete points 7 are connected with the corresponding curvature centers 5 to obtain osculating axes, the osculating axes are stretched along the direction vertical to the straight surface to obtain osculating planes 6, and similarly, the discrete points are connected with the corresponding curvature centers 8 to obtain osculating axes, and the osculating axes are stretched along the direction vertical to the straight surface to obtain the internal multiplication wave band osculating planes 9. When the curvature is infinite, a binary plane-multiplied-band tangential plane 4 is obtained. The flow direction pressure distribution 15 can adopt a design such as a quadratic curve or a cubic curve, and the control of the wall surface pressure distribution is realized by changing the pressure distribution curve 15 in the flow direction section. In which the pressure in the transverse direction is the same for both inner and outer waverider, i.e. in transverse direction A1A2The wall surface pressure is A point pressure and the transverse direction is B1B2The wall surface pressure between the two is B point pressure.
(2) And designing the projection of the leading edge capturing molded line on a top view, and solving the corresponding compression molded line by using an inverse characteristic line method according to given pressure distribution. The solving process is divided into an external multiplication wave band and an internal multiplication wave band, and the external compression basic flow field and the internal compression basic flow field are respectively corresponding to the axial symmetry. The outer multiplied band is illustrated by section 6, and the inner multiplied band is illustrated by section 9. According to the external multiplication wave band secret section 6The pressure distribution curve CD, combined with the inflow parameters and the curvature of the osculating plane, and the right-hand characteristic line EDCsFor the boundary condition of the characteristic line, as shown in fig. 3(a), the compressed profile 17 (compressed profile C) is obtained by solving using the inverse characteristic line method1sDCs) And a corresponding axisymmetric outer compression flow field; similarly, according to the pressure distribution curve AD corresponding to the inner multiplied band tangential plane 9, the incoming flow parameters and the curvature of the tangential plane are combined, and the left-line characteristic line FD is usedAsFor the boundary condition of the characteristic line, as shown in fig. 3(b), the compressed profile 18 (compressed profile a) in the osculating plane 9 is obtained by solving using the inverse characteristic line method1sDAs) And a corresponding axisymmetrically inward convergent flow field.
(3) Firstly, according to the included angle α of the symmetric section 1 of the internal and external waverider integrated scheme with controllable external waverider section 6 and wall surface pressure, in the corresponding axisymmetric external compression flow field, the compression molded line C is utilized to compress the compressed molded line C1sDCsCalculating the coordinate (x, y) of each point to obtain the compressed profile 14 (i.e. the compressed profile C) in the osculating plane 61DC) The three-dimensional coordinates (x, ysin α, ycos α) of each point are added, then the close in-plane compression molded lines of the external waverider are combined to obtain the external waverider compression molded surface 12, and similarly, according to the included angle β between the tangent plane 9 and the symmetric plane 1, the compression molded line A is utilized in the corresponding axisymmetric internal contraction flow field1sDAsCalculating the coordinates (x, y) of each point to obtain the compressed profile 13 (i.e. the compressed profile A) in the osculating plane 91DA) And combining the inner-multiplied wave band intimate in-plane compression profiles by the three-dimensional coordinates (x, ysin β, ycos β) of each point to obtain the three-dimensional inner-turning air inlet compression profile 11.
(4) And designing the projection of the outlet section of the three-dimensional inward turning air inlet channel and the projection of the lip of the three-dimensional inward turning air inlet channel on the design section, and obtaining the three-dimensional configuration of the lip of the three-dimensional inward turning air inlet channel according to the shock wave relation. The three-dimensional inward-turning inlet channel isolation section outlet section 23 is designed to be similar to a rectangle, an outer waverider and an inner waverider of a shock wave curve multiplied by the three-dimensional inward-turning inlet channel develop downstream along the compression molded surface 11, and the three-dimensional configuration of the three-dimensional inward-turning inlet channel lip 20 is obtained by intersecting with a projection of the three-dimensional inward-turning inlet channel lip on the design section along a surface developed along a flow direction.
(5) And carrying out geometric construction on the internal and external waverider integrated aircraft based on the compression profiles (such as the aircraft upper surface front edge capturing profile 24, the aircraft lower surface profile 10, the backward equal straight pull extension of the isolation section and the like). The internal and external waverider integrated device with controllable wall surface pressure in a designed flight state is obtained.
The internal and external waverider integrated scheme with controllable wall pressure realizes the integration of two high-performance devices while keeping the advantages of an external waverider and a three-dimensional internal rotation air inlet channel, and controls the distribution of the wall pressure, thereby improving the overall performance of an aircraft and a propulsion system.
As shown in fig. 6, the internal and external waverider integrated solution with controllable wall pressure includes an external waverider aircraft 25 and a three-dimensional internal turning inlet, and the three-dimensional internal turning inlet is composed of a three-dimensional internal turning inlet compression surface 11, a three-dimensional internal turning inlet lip 20, a three-dimensional internal turning inlet shoulder profile 21, a three-dimensional internal turning inlet isolation section 22, and a three-dimensional internal turning inlet transverse overflow port 19. And the three-dimensional adversion intake duct can realize inside waverider. The external waverider aircraft 25 and the three-dimensional internal rotation air inlet channel are connected and transited by means of the binary wedge transfer wave band 16, the three-dimensional internal rotation air inlet channel profile 11 is flatly transferred at the shoulder profile 21 of the three-dimensional internal rotation air inlet channel and enters the three-dimensional internal rotation air inlet channel isolation section 22, the lip 20 of the three-dimensional internal rotation air inlet channel is determined by the position of the incident shock wave reflection point of the three-dimensional internal rotation air inlet channel under the design condition, and the transverse overflow port 19 of the three-dimensional internal rotation air inlet channel exists at the connection transition position of the external waverider aircraft 25 and the.

Claims (1)

1. The method for integrally designing the internal and external waverider with controllable wall surface pressure is characterized by comprising the following steps of:
1) the projection of the front edge capturing molded line on the design section and the required pressure distribution are designated according to the design requirements, and the pressure distribution is designed by adopting a quadratic curve or a cubic curve;
2) designing the projection of the front edge capturing molded line on a top view, and solving corresponding external waverider and internal waverider compression molded lines by using an external flow and internal flow inverse characteristic line method according to given pressure distribution;
3) according to the compression molded line and the included angle between the tangent plane and the symmetrical plane, obtaining an internal and external waverider integrated compression molded surface in a corresponding axisymmetric external compression flow field or axisymmetric internal contraction flow field through coordinate transformation;
4) designing the outlet section of the three-dimensional inward turning air inlet channel and the projection of the lip of the three-dimensional inward turning air inlet channel on the designed section, and obtaining the three-dimensional configuration of the lip of the three-dimensional inward turning air inlet channel according to the shock wave relation;
5) carrying out geometric construction on the internal and external waverider integrated aircraft on the basis of the compression molded surface; the geometrical configuration comprises an upper surface of the aircraft, a lower surface of the aircraft, an isolation section and the like which stretch backwards in a straight pull mode.
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CN111460571B (en) * 2019-01-02 2023-07-21 中国航发商用航空发动机有限责任公司 Construction method and construction device for molded line of intermediate case component and computer readable storage medium
CN110182380B (en) * 2019-05-24 2022-09-02 南昌航空大学 Hypersonic speed internal and external flow integrated design method based on typical internal rotation air inlet channel
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