CN110589010A - Hypersonic large-loading-space waverider design method - Google Patents
Hypersonic large-loading-space waverider design method Download PDFInfo
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Abstract
The invention discloses a design method of a wave rider in a hypersonic large loading space, and belongs to the technical field of aircraft design. According to the invention, firstly, a 'reflection shock wave dependent region' is added on a reference flow field adopted by the traditional cone-guided wave body design method, an FCC curve is divided into two parts, the cone-guided wave body design method and the streamline tracking air inlet design method are respectively adopted, and smooth transition is realized on the aspects of geometric shape and aerodynamic characteristics of the two parts. The method can flexibly design the corresponding reference flow field according to the design target, obviously improve the loading space of the wave carrier on the premise of ensuring that the pneumatic performance in the design state is equivalent to that of the traditional cone guided wave carrier design method, convert the special-shaped structure which is generated by the traditional cone guided wave carrier design method and is not beneficial to engineering use into the rectangular-like structure which is easier to use, and improve the engineering use value of the wave carrier.
Description
The technical field is as follows:
the invention discloses a design method of a waverider in a hypersonic large loading space, belonging to the technical field of designing hypersonic aircrafts.
Background art:
the conventional waverider theory itself can be divided into a wedge-guided theory, a cone-guided theory, a osculating cone theory, an osculating axisymmetric theory, an osculating flow field theory, and a recently developed method for generating waveriders using a three-dimensional flow field. Due to the design method of excellent aerodynamic performance and flexibility and rapidness of the waverider in the design state, the recent hypersonic flight vehicles mostly adopt waverider layouts.
The main focus of the conventional design of the waverider by applying the theories is to improve the pneumatic performance of the waverider, and the main focus can be divided into the performance of improving a design point, the performance of improving a wide speed range, the performance of improving the design point under the condition of hypersonic non-equilibrium flow and the performance of considering both the heat-proof characteristic and the design point, so that a plurality of new waverider concepts are generated. For these objectives, the current design methods can be divided into two categories, one category is to realize the objectives by splicing the flow field and designing the molded line by using the traditional wave multiplier design theory, and the other category includes concepts such as "full wave multiplier", "von karman curve multiplier", and "double wave multiplier", "nose cone passivation wave multiplier", "star wave multiplier", which integrally design the inner and outer flows. The other type is that the existing wave multiplier is used as an initial model by utilizing an optimization algorithm, optimization iteration is carried out according to a multi-constraint target, the design is carried out by using a genetic algorithm, an ant colony algorithm and a related algorithm of an artificial intelligence field, but the optimization space of the optimization iteration algorithm is limited, so that the performance of the initial model generally limits the performance of a final design result. Furthermore, the increase in loading space is more limited than aerodynamic performance, since it is ensured that the aircraft is still waverider at the design state. Recently, researchers have designed the shape of the line connecting the centers of curvature of the shock curve to increase the volume ratio of the wave multiplier, but the increase of the generated wave multiplier in the loading space is still limited.
In summary, the main concern of the conventional wave multiplier is the improvement of the aerodynamic performance of the wave multiplier, and the common disadvantages of the wave multiplier are that the volume ratio is low, and the cross section is of a special-shaped structure, so that the available space is further reduced, and the application range of the wave multiplier is greatly limited, so that it is necessary to develop a design method of the wave multiplier with a hypersonic large loading space.
The invention content is as follows:
the invention provides a hypersonic large-loading space waverider design method, which comprises the steps of firstly adding a 'reflection shock wave dependent region' on a reference flow field adopted by a traditional cone guided waverider design method, dividing an FCC curve into two parts, respectively adopting a cone guided waverider design method and a streamline tracking air inlet design method, and realizing smooth transition of the two parts in the aspects of geometric shape and aerodynamic characteristics. The method can flexibly design the corresponding reference flow field according to the design target, obviously improve the loading space of the wave carrier on the premise of ensuring that the pneumatic performance in the design state is equivalent to that of the traditional cone guided wave carrier design method, convert the special-shaped structure which is generated by the traditional cone guided wave carrier design method and is not beneficial to engineering use into the rectangular-like structure which is easier to use, and improve the engineering use value of the wave carrier.
The invention provides a design method of a waverider with high supersonic speed and large loading space, which comprises the following steps:
the method comprises the following steps: given the geometry of the shock curve ICC, which constrains the width and height of the waverider, according to design objectives.
Step two: the geometric characteristics of a first section of FCC curve on the upper surface of the waverider are given according to design targets, and the section of curve restrains the shape of a leading edge line of the waverider. And designing a second section of FCC curve by taking the end point of the section of curve and selecting one point on the shock wave curve ICC as two end points, wherein the two sections of FCC curves ensure that the intersection points are tangent to form an upper surface curve of the wave multiplier together. Tracking from an FCC curve to the upstream and the downstream along the direction of free flow to obtain a free flow surface, and intersecting the free flow surface with a shock wave curved surface of a designed flow field to obtain a leading edge line of a wave-multiplying body;
step three: and designing the post-wave reference flow field according to the incoming flow Mach number, the laser angle, the wall surface pressure distribution rule or the wall surface shape. The reference flow field is divided into three parts, namely a front edge shock wave dependent area, a main compression area and a reflection shock wave dependent area. The first two parts are designed by a characteristic line method for giving an incoming flow Mach number, a leading edge compression angle and a wall pressure distribution rule of a leading edge shock wave dependent area and a main compression area, and the second part is designed by directly giving wall shapes of the leading edge shock wave dependent area and the main compression area and calculating a reference flow field by using a flow Mach number. The third part is a reflected shock wave dependent area, wherein the initial position of the reflected shock wave needs to be given, the generation rule of the reflected shock wave is given, a reflected shock wave curve is generated, and then the reflected shock wave dependent area is calculated.
Step four: and tracing the streamline from the point on the leading edge line of the wave multiplier to the downstream in the designed reference flow field to obtain the lower surface shape of the wave multiplier. Wherein the tracking of the point on the leading edge line corresponding to the first segment of the FCC curve to the location of the reflected shock stops, and the tracking of the point on the leading edge line corresponding to the second segment of the FCC curve to the location of the end of the reflected shock dependent region stops.
The upper surface of the waverider can be flexibly changed according to design objectives.
The invention has the advantages that: on the premise that the pneumatic performance of the designed waverider in the design state is equivalent to that of the traditional method, the loading space of the designed waverider is obviously larger than that of the traditional design method, the special-shaped structure of the traditional layout is optimized into a similar rectangular structure, the available space is further increased, and the application value of the waverider is improved.
Description of the drawings:
FIG. 1 is a schematic diagram of FCC curve and ICC curve design in a hypersonic large loading space waverider design method
FIG. 2 is a schematic diagram of a reference flow field structure in a hypersonic large loading space waverider design method
FIG. 3 is a three-dimensional view of a waverider designed by the new method in the example
FIG. 4 is a three-dimensional view of a waverider designed by the conventional cone-guiding method in an embodiment
FIG. 5a is the pressure distribution diagram of the waverider designed by the new method in the example
FIG. 5b is a pressure distribution diagram of a wave multiplier designed by the conventional cone guiding method in the embodiment
FIG. 6a is a pressure distribution diagram of the cross section of the waverider designed by the novel method in the embodiment at the position 6.482% in the axial direction of the fuselage
FIG. 6b is a pressure distribution diagram of the cross section of the waverider in the case of the conventional conical waveguide design at 6.482% of the axial direction of the fuselage
FIG. 7a is a pressure distribution diagram of the cross section of the waverider designed by the novel method in the embodiment at the position 65.165% in the axial direction of the fuselage
FIG. 7b is a pressure distribution diagram of the cross section of the waverider in the case of the conventional conical waveguide design at 65.165% of the axial direction of the fuselage
FIG. 8a is a pressure distribution diagram of the cross section of the waverider designed by the novel method in the embodiment at the position 87.735% in the axial direction of the fuselage
FIG. 8b is a pressure distribution diagram of the cross section of the waverider in the case of the conventional conical waveguide design at 87.735% of the axial direction of the fuselage
FIG. 9 is a graph showing the lift curves of the waverider using the new method and the conventional cone-guiding method in the example
FIG. 10 is a resistance curve diagram of a wave multiplier designed by the new method and the conventional cone-guiding method in the embodiment
FIG. 11 is a graph of lift-to-drag ratio of waverider using the new method and the conventional cone-guiding method in the example
In the figure:
1. a first portion of the FCC curve for the new process; 2. a second portion of the FCC curve for the new process; an ICC curve; 4. FCC curve for cone-guide method; 5. leading edge shock wave dependent region of the reference flow field in the new method; 6. a main compression zone of the reference flow field in the new method; 7. in the new method, a reflection shock wave dependent region of a reference flow field; 8. reflecting shock waves of a reference flow field in the new method; 9. leading edge shock waves of a reference flow field in the new method; 10. a centerbody of a reference flow field in the new method; 11. position of FCC and ICC curves in a new method
The specific implementation mode is as follows:
the present invention will be described in detail below with reference to the accompanying drawings and examples.
The invention provides a hypersonic large-loading space waverider design method, which comprises the steps of firstly adding a 'reflection shock wave dependent region' on a reference flow field adopted by a traditional cone guided waverider design method, dividing an FCC curve into two parts, respectively adopting a cone guided waverider design method and a streamline tracking air inlet design method, and realizing smooth transition of the two parts in the aspects of geometric shape and aerodynamic characteristics. The method can flexibly design the corresponding reference flow field according to the design target, obviously improve the loading space of the wave carrier on the premise of ensuring that the pneumatic performance in the design state is smaller than the difference between the traditional cone guided wave carrier design method, convert the special-shaped structure which is generated by the traditional cone guided wave carrier design method and is not beneficial to engineering use into the rectangular-like structure which is easier to use, and improve the engineering use value of the wave carrier.
The design method of the waverider with the hypersonic large loading space combines with the figures 1 and 2, and comprises the following steps:
the method comprises the following steps: the geometry of the shock curve ICC (curve 3) is given according to design objectives, which constrains the width and height of the waverider.
Step two: the geometric characteristics of the first segment of FCC curve (curve 1) on the upper surface of the waverider are given according to the design target, and the segment of curve restricts the height and the width of the loading space of the waverider. And designing a second section of FCC curve (curve 2) by taking the end point of the section of curve and selecting one point on the shock wave curve ICC as two end points, wherein the two sections of FCC curves ensure that the intersection points are tangent to form an upper surface curve of a wave multiplier together. Tracking from the FCC curve to the upstream and the downstream to obtain a free flow surface, and intersecting with the shock wave curved surface of the designed flow field to obtain a front edge line of a wave multiplier.
Step three: and designing the post-wave reference flow field according to the incoming flow Mach number, the laser angle, the wall surface pressure distribution rule or the wall surface shape. The reference flow field is divided into three parts, namely a front edge shock wave dependent area 5, a main compression area 6 and a reflection shock wave dependent area 7. The first two parts are designed by a characteristic line method for giving an incoming flow Mach number, a leading edge compression angle and a wall pressure distribution rule of a leading edge shock wave dependent area 5 and a main compression area 6, and the second part is designed by directly giving wall shapes of the leading edge shock wave dependent area 5 and the main compression area 6 and calculating a reference flow field by a flow Mach number. The third part is a reflected shock wave dependent region 7, the reflected shock wave 8 is formed by reflecting a front edge shock wave 9 on a central body 10, the initial position of the reflected shock wave 8 is determined by the height parameter R of the reference flow field and the structure of the reference flow field, the generation rule of the reflected shock wave 8 is given on the basis, a reflected shock wave curve 8 is generated, and then the reflected shock wave dependent region 7 is calculated. The starting point of the reflected shock wave 8 is the position 11 of the FCC curve and the ICC curve, the reference flow field of the traditional cone-guide-multiplier wave body design method is cut off at the position 11, and the new method still has a designed part after the position.
Step four: and tracing the streamline from the point on the leading edge line of the wave multiplier to the downstream in the designed reference flow field to obtain the lower surface shape of the wave multiplier. Wherein the point on the leading edge line corresponding to the first segment of the FCC curve (curve 1) is traced to the end of the reflected shock 8 and the point on the leading edge line corresponding to the second segment of the FCC curve (curve 2) is traced to the end of the reflected shock dependent region 7.
The invention has the advantages that: on the premise that the pneumatic performance of the designed waverider in the design state is equivalent to that of the traditional method, the loading space of the designed waverider is obviously larger than that of the traditional design method, the special-shaped structure of the traditional layout is optimized into a similar rectangular structure, the available space is further increased, and the application value of the waverider is improved.
This description is not intended to be exhaustive or to limit the invention to the precise forms disclosed.
Application example:
1. the design height is 40km (namely, the atmospheric parameter at the height is used as the design parameter), the design Mach number Ma is 12.0, the compression angle delta is 1 DEG, and the pressure distribution of the leading edge shock wave dependent area and the main compression area takes a continuous function p0(0.0002x +1), where p is the static pressure of the reference flow field wall, p0The static pressure after the front edge point wave is obtained, and x is the axial position of the reference flow field. The first FCC curve (curve 1) is a circle with R being 2200mm, and the expression of the second FCC curve (curve 2) is y being-0.0076 x2+10.9640x-6040.4934, wherein y and x are shown in fig. 1, the unit is mm, the comparative example adopts the design method of cone-guide wave-multiplying body, and the expression of FCC curve (curve 4) is that y is-0.0011 x22200, where y and x are shown in fig. 1, and the equation is in mm, and the ICC curves (curve 3) of the two wavemultiplying bodies each take a circle with R being 4000mm, and both share a reference flow field, except that the lower surface of the comparative example uniformly tracks the reflected shock wave 8, while the first stage of the new method is thatThe lower surface corresponding to the FCC curve traces the reflected shock 8, and the lower surface corresponding to the second FCC curve traces the reflected shock dependent region 7. Fig. 3 is a three-dimensional view of a waverider designed by the new method, and fig. 4 is a three-dimensional view of a comparative example designed by the cone-guided method.
Fig. 5a and 5b are three-dimensional pressure distribution diagrams of the results of calculation under the condition that the design height of two waverider is 40km and the design mach number Ma is 12.0 and no adhesion exists, and fig. 6a and 6b, fig. 7a and 7b, and fig. 8a and 8b are pressure distribution diagrams of the two waveriders at selected cross sections (the positions of the pressure distribution diagrams are 6.482%, 65.165% and 87.735% of the axial direction of the fuselage respectively) under the same condition. Fig. 9, 10, and 11 are curves of the variation of lift, resistance, and lift-to-drag ratio of two kinds of waverider with the angle of attack, respectively, and it can be seen that the waverider designed by the new method has larger lift and resistance under different angle of attack conditions than the comparative example, the lift-to-drag ratio at the design point (zero degree angle of attack) is 10.6, which is slightly less than 10.816 of the comparative example, the lift and resistance laws of the two are similar when viewed as a whole, the lift-to-drag ratio curves are highly overlapped, and the aerodynamic performance is equivalent.
The volume ratio of the multiplier designed by the new method is 0.097, and the volume is 12.304m3The volume ratio of the multiplier wave body designed in the comparative example is 0.078, and the volume is 8.134m3. Compared with the design result of the traditional method, the volume rate of the new method design result is improved by 24.359%, and the volume is improved by 51.315%.
In conclusion, on the premise that the pneumatic performance is equivalent in the design state, the novel method has a larger loading space and a stronger engineering application prospect.
Claims (4)
1. A design method of a wave rider with high supersonic speed and large loading space is characterized by comprising the following steps:
a 'reflection shock wave dependent region' is added on a reference flow field adopted by a traditional cone-guided wave-rider design method, an FCC curve is divided into two parts, a cone-guided wave-rider design method and a streamline tracking air inlet design method are respectively adopted, when a wave-rider lower surface is generated, part of the streamline tracking of the cone-guided wave-rider design method is adopted to track to a reflection shock wave position, part of the streamline tracking air inlet design method is adopted to finish the 'reflection shock wave dependent region', smooth transition is realized on the aspects of geometric shape and aerodynamic characteristics of the two parts, and a free flow surface is adopted when the wave-rider upper surface is generated.
2. The method for designing the waverider in hypersonic large loading space according to claim 1, wherein: comprises the following steps of (a) carrying out,
the method comprises the following steps: according to the design target, the geometric characteristics of a shock wave curve ICC are given, and the curve restrains the width and the height of a waverider;
step two: the geometric characteristics of a first section of FCC curve on the upper surface of the waverider are given according to design targets, and the section of curve restrains the shape of a leading edge line of the waverider. And designing a second section of FCC curve by taking the end point of the section of curve and selecting one point on the shock wave curve ICC as two end points, wherein the two sections of FCC curves ensure that the intersection points are tangent to form an upper surface curve of a wave multiplier together. Tracking from an FCC curve to the upstream and the downstream along the direction of free flow to obtain a free flow surface, and intersecting the free flow surface with a shock wave curved surface of a designed flow field to obtain a front edge line of a wave-multiplying body;
step three: designing a reference flow field according to the incoming flow Mach number, the shock wave angle and the wall surface pressure distribution rule or the wall surface shape;
step four: carrying out streamline tracing tracking on a point on a front edge line of the waverider to the downstream in a designed reference flow field to obtain the shape of the lower surface of the waverider;
step five: the upper surface shape is traced from a point on the leading edge line of the waverider downstream in the free stream direction.
3. The method for designing the waverider in hypersonic large loading space according to claim 2, wherein: the third step is specifically as follows: and designing the post-wave reference flow field according to the incoming flow Mach number, the laser angle, the wall surface pressure distribution rule or the wall surface shape. The reference flow field is divided into three parts, namely a front edge shock wave dependent area, a main compression area and a reflection shock wave dependent area. The first two parts are designed by a characteristic line method for giving an incoming flow Mach number, a leading edge compression angle and a wall pressure distribution rule of a leading edge shock wave dependent area and a main compression area, and the second part is designed by directly giving wall shapes of the leading edge shock wave dependent area and the main compression area and calculating a reference flow field by using a flow Mach number. The third part is a reflected shock wave dependent area, wherein the initial position of the reflected shock wave needs to be given, the generation rule of the reflected shock wave is given, a reflected shock wave curve is generated, and then the reflected shock wave dependent area is calculated.
4. The method for designing the waverider in hypersonic large loading space according to claim 2, wherein: the fourth step is specifically as follows: and tracing the streamline from the point on the leading edge line of the wave multiplier to the downstream in the designed reference flow field to obtain the lower surface shape of the wave multiplier. Wherein the tracking of the point on the leading edge line corresponding to the first segment of the FCC curve to the reflected shock stops and the tracking of the point on the leading edge line corresponding to the second segment of the FCC curve to the end of the reflected shock dependent region stops.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111460580A (en) * | 2020-03-26 | 2020-07-28 | 中国航天空气动力技术研究院 | Method for expanding volume of waverider by using cubic polynomial |
| CN112949199A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power waverider |
| CN113032894A (en) * | 2021-02-24 | 2021-06-25 | 东方空间技术(山东)有限公司 | Double-cone fairing-shaped wire optimization design method based on Von Karman wire |
| CN116341120A (en) * | 2023-05-19 | 2023-06-27 | 中国航天空气动力技术研究院 | Method for determining waverider characteristic dependence area |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2558498C2 (en) * | 2013-12-24 | 2015-08-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Московский государственный университет леса" (ФГБОУ ВПО "МГУЛ") | Construction of optimum airfoil for hypersonic aircraft |
| CN105667811A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft |
| RU2595354C1 (en) * | 2015-05-21 | 2016-08-27 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Hypersonic aircraft body and method of making same |
| CN106250607A (en) * | 2016-07-27 | 2016-12-21 | 中国航天空气动力技术研究院 | Double sweepback Waverider method for designing based on non-homogeneous B spline curve |
| WO2019091057A1 (en) * | 2017-11-09 | 2019-05-16 | 中国航天空气动力技术研究院 | Osculating cone theory-based fixed-plane waverider design method |
| CN110182380A (en) * | 2019-05-24 | 2019-08-30 | 南昌航空大学 | Based on the hypersonic inside and outside flow integrated design method for rotating into air flue in typical case |
-
2019
- 2019-09-09 CN CN201910847267.7A patent/CN110589010B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2558498C2 (en) * | 2013-12-24 | 2015-08-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Московский государственный университет леса" (ФГБОУ ВПО "МГУЛ") | Construction of optimum airfoil for hypersonic aircraft |
| RU2595354C1 (en) * | 2015-05-21 | 2016-08-27 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Hypersonic aircraft body and method of making same |
| CN105667811A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft |
| CN106250607A (en) * | 2016-07-27 | 2016-12-21 | 中国航天空气动力技术研究院 | Double sweepback Waverider method for designing based on non-homogeneous B spline curve |
| WO2019091057A1 (en) * | 2017-11-09 | 2019-05-16 | 中国航天空气动力技术研究院 | Osculating cone theory-based fixed-plane waverider design method |
| CN110182380A (en) * | 2019-05-24 | 2019-08-30 | 南昌航空大学 | Based on the hypersonic inside and outside flow integrated design method for rotating into air flue in typical case |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111460580A (en) * | 2020-03-26 | 2020-07-28 | 中国航天空气动力技术研究院 | Method for expanding volume of waverider by using cubic polynomial |
| CN111460580B (en) * | 2020-03-26 | 2023-07-28 | 中国航天空气动力技术研究院 | Method for expanding waverider volume by using cubic polynomial |
| CN113032894A (en) * | 2021-02-24 | 2021-06-25 | 东方空间技术(山东)有限公司 | Double-cone fairing-shaped wire optimization design method based on Von Karman wire |
| CN113032894B (en) * | 2021-02-24 | 2023-01-03 | 东方空间技术(山东)有限公司 | Double-cone fairing shape line optimization design method based on Feng Ka door-shaped line |
| CN112949199A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power waverider |
| CN112949199B (en) * | 2021-03-15 | 2024-02-02 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power wave body |
| CN116341120A (en) * | 2023-05-19 | 2023-06-27 | 中国航天空气动力技术研究院 | Method for determining waverider characteristic dependence area |
| CN116341120B (en) * | 2023-05-19 | 2023-08-11 | 中国航天空气动力技术研究院 | Method for determining waverider characteristic dependence area |
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