CN105059530A - Sharp vertex osculation tapered wave-rider with controllable sweepback - Google Patents
Sharp vertex osculation tapered wave-rider with controllable sweepback Download PDFInfo
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Abstract
The invention discloses a sharp vertex osculation tapered wave-rider with a controllable sweepback. A whole front edge of the wave-rider is a straight-line section; the angle of the sweepback at the front edge of the straight-line section is controllable at a design phase; a gas capturing curve is composed of one straight-line section and one section of circular arc; the circular arc is located on one side close to a symmetrical plane; and a circular center is an end point located on the symmetrical plane of a flowing capturing tube curve. According to the sharp vertex osculation tapered wave-rider, a stable separation vortex is generated on the upper surface of the front edge of a straight line with the controllable sweepback; and the aerodynamic performance of the upper surface is improved and the volume efficiency of an air vehicle is not sacrificed, so that the design of the upper surface is facilitated very well.
Description
Technical field
The present invention relates to aerodynamic scope, the controlled sharp apex in especially a kind of sweepback angle bores Waverider closely.
Background technology
The aircraft of conventional in layout is when hypersonic flight, and maximum lift-drag ratio and flight Mach number exist following relation:
Wherein M
∞for flight Mach number.From above formula, conventional in layout is when High Mach number, and maximum lift-drag ratio to about 4, namely can only exist " 1ift-drag ratio barrier ".Waverider can break traditions " the 1ift-drag ratio barrier " of layout, for the aircraft maximum lift-drag ratio of Waverider layout and the pass of flight Mach number is:
Above formula illustrates, Waverider layout is when High Mach number, and maximum lift-drag ratio can reach about 6.Waverider why have so good 1ift-drag ratio characteristic be because: this type aircraft shock wave when design point is flown is attached to leading edge completely, similarly is drive to fly on shock surface, is also therefore called " Waverider ".In this flow field, lower surface flowing is attached shock wave restriction and does not reveal to upper surface, and for conventional in layout, the leakage of this upper and lower surface can cause the loss of lift of nearly 25%.
Waverider roughly can be divided into two large classes according to method of designing: positive method of designing and mimetic design method.Positive method of designing refers to tries to achieve basic flow field by certain geometric shape, and then by flowing capture duct (FlowCaptureTube, FCT) with the intersection determination Waverider leading edge of shock wave, last in flow field, carry out streamlined impeller from leading edge obtain Waverider, the Typical Representative of this kind of Waverider is cut by two dimension the cone cut wedge flow field Waverider and obtained by circular cone flow field that wedge flow field obtains to lead Waverider.
Mimetic design method and positive method of designing unlike, do not know the geometric model generating basic flow field in advance, the profile of shock wave of known basic flow field, namely the basic flow field of mimetic design method needs to be solved by profile of shock wave inverse iteration.For general three-dimensional flow field, be larger by the calculated amount of profile of shock wave anti-plug-flow field, be unfavorable for the design of Waverider.For this problem, Sobieczky etc. propose the generation method of closely boring Waverider (OsculatingConeWaverider, OCW), and have carried out large quantity research, its basic ideas use Conical Flow Field to remove approximate arbitrary three-dimensional flow field, enormously simplify calculating.Specific practice is on known profile of shock wave, get a cross-sectional plane, this cross section molded line is called that curve (InletCaptureCurve is caught in air inlet, ICC), then on molded line, construct a series of close cone, by closely boring shock wave and the intersection determination leading edge of flowing capture duct, in close coning tower tray field, from leading edge, finally carrying out streamlined impeller obtain Waverider.
Although generation and the method for designing of Waverider obtain in-depth study, still there is insoluble problem:
Volume efficiency (VE) and 1ift-drag ratio conflicting, must be weighed during design;
Upper surface difficult design, be designed to expanding noodles can improve aeroperformance but will volume efficiency (VE) be reduced, be designed to compressing surface can improve volume efficiency (VE) but can aeroperformance be reduced, be generally designed to free stream interface at present, to aeroperformance and volume efficiency (VE) all without contributing;
Low-speed performance is poor, because only consider the performance of design point during Waverider design, therefore the performance in other fast territory is especially taken off land and transonic flight poor performance.
Viscosity drag is suitable with pressure drag magnitude, must consider viscous effect during design.
Summary of the invention
The object of the invention is to propose the close cone Waverider that a kind of leading edge sweep is controlled, upper surface adopts free stream interface, the whole leading edge of this Waverider is straight line section, and the sweepback angle of this linear portion leading edge can be controlled at design phase.This Waverider can effectively utilize its swept effect to produce the stable separated vorticcs similar with delta wing at upper surface, and under the prerequisite not reducing volume efficiency (VE), improve the lift of Waverider, this characteristic is also very favourable to the low-speed performance of Waverider.
For achieving the above object, the present invention adopts following technical scheme:
The controlled sharp apex in a kind of sweepback angle bores Waverider closely, the whole leading edge of described Waverider is straight line section, the angle at the sweepback angle of described linear portion leading edge is controlled at design phase, gas is caught curve and is made up of straight line section and one section of circular arc, circular arc is positioned near plane of symmetry side, and the center of circle is the end points that flowing capture duct curve is positioned on the plane of symmetry.
The controlled sharp apex in sweepback angle bores a generation method for Waverider closely, comprises the following steps:
Step one, according to design needs, given cruise Mach number, flying height and fuselage length;
Step 2, determine sweepback angle, according to the upper limit at cruise Mach number determination Waverider sweepback angle, then need selection rational sweepback angle according to design;
Step 3, determine Angle of Shock Waves, first by the variation range of the upper limit determination Angle of Shock Waves at cruise Mach number and sweepback angle, then need selection rational Angle of Shock Waves according to design;
Step 4, given flowing capture duct curved surface, this curved surface by its bottom Waverider the drop shadow curve in the plane capture duct curve that flows determine, for ensureing to obtain straight line leading edge, this curve adopts a linear portion in a certain angle with horizon, and its length can be determined by fuselage length and sweepback angle;
Step 5, given air inlet catch curve, this curve is made up of straight line section and one section of circular arc, circular arc is positioned near plane of symmetry side, the center of circle is the end points that flowing capture duct curve is positioned on the plane of symmetry, linear portion is positioned at away from plane of symmetry side, and its one end is connected with circular arc, and point of connection place ensures that first derivative is continuous, the other end is connected with the outer end points of flowing capture duct curve, and at two, this point of connection place, linear portion is in a certain angle;
Step 6, determine osculating plane, air inlet being caught curve discrete is series of discrete point, does normal by each discrete point, by normal and to catch Curves in a series of planes of plane perpendicular to air inlet be exactly osculating plane;
Step 7, in each osculating plane, determine the subpoint of close conic node, for arc section, in certain osculating plane, the subpoint of conic node is the center of circle of this arc section closely;
Step 8, in each osculating plane, catch by the subpoint of Angle of Shock Waves, closely conic node and air inlet the summit that corresponding discrete point on curve determines cone closely;
Step 9, according to Angle of Shock Waves and cruise Mach number, by solving the close coning tower tray field that Taylor-Maccoll equation obtains in each osculating plane;
Step 10, in each osculating plane, determine the leading edge point of Waverider, this is determined by the intersection point of flowing capture duct and shock surface;
Step 11, the leading edge point determined with step 10 in each osculating plane carry out streamlined impeller for starting point in circular cone flow field, follow the trail of to air inlet and catch Curves in plane, gained all streamline compositions Waverider lower surface;
Step 12, the leading edge point determined with step 10 in each osculating plane carry out streamlined impeller for starting point in Free Flow Field, follow the trail of to air inlet and catch Curves in plane, gained all streamline compositions Waverider upper surface;
Step 13, provided by circular cone flow field under specified altitude assignment and fuselage length, utilize reference temperature method and the dull and stereotyped force of cohesion method of calculating of compression to provide the 1ift-drag ratio of Waverider without viscosity flow field information, and calculate volume efficiency (VE).
In technique scheme, in certain osculating plane in described step 8, the subpoint of conic node is determined by the intersection point of straight line and osculating plane inter normal closely.
In technique scheme, the described straight-line pass circular arc center of circle, and the line that corresponding discrete point on curve is caught in subpoint and air inlet has intersection point with flowing capture duct curve.
In sum, owing to have employed technique scheme, beneficial effect concrete manifestation of the present invention is as follows:
The arc section on curve is caught in air inlet and the center of circle of this arc section of capture duct curve negotiating that flows guarantees that this type Waverider head is sharp apex;
The straight line that is projected as that the linear portion on curve is caught in air inlet, the capture duct curve that flows is straight line and close conic node ensure that this type Waverider leading edge is straight line leading edge, and controlled;
The Waverider aspect obtained is identical with delta wing, and can produce at upper surface when flying and stablize separated vorticcs, thus improve the lift efficiency of this type Waverider, this point is particularly important when low-speed operations;
The present invention stablizes separated vorticcs by the straight line leading edge that sweepback angle is controlled in upper surface generation, and the aeroperformance that improve upper surface does not but sacrifice the volume efficiency (VE) of aircraft, and this is very favorable to the design of upper surface.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is free view of the present invention;
Fig. 2 is birds-eye view and the geometric relationship schematic diagram of Fig. 1;
Fig. 3 is back view and the geometric relationship schematic diagram of Fig. 1;
Fig. 4 be Fig. 2, Fig. 3 back view basis on indicate the schematic diagram of discrete point, normal and close conic node subpoint;
Fig. 5 is that close conic node solves schematic diagram;
Wherein: 1 is Waverider lower surface, 2 is that curve is caught in air inlet, and 3 is shock surfaces.
Detailed description of the invention
The present invention installs following steps and implements:
One, according to design needs, given cruise Mach number, flying height and fuselage length;
Two, determine sweepback angle, first by the upper limit at cruise Mach number determination Waverider sweepback angle, then need selection rational sweepback angle according to design;
Three, determine Angle of Shock Waves, first by the variation range of the upper limit determination Angle of Shock Waves at cruise Mach number and sweepback angle, then need selection rational Angle of Shock Waves according to design;
Four, given flowing capture duct curved surface, this curved surface by its bottom Waverider the drop shadow curve in the plane capture duct curve that flows determine, for ensureing to obtain straight line leading edge, this curve adopts a linear portion in a certain angle with horizon, and its length can be determined by fuselage length and sweepback angle;
Five, curve is caught in given air inlet, this curve is made up of straight line section and one section of circular arc, circular arc is positioned near plane of symmetry side, the center of circle is the end points that flowing capture duct curve is positioned on the plane of symmetry, linear portion is positioned at away from plane of symmetry side, and its one end is connected with circular arc, and point of connection place ensures that first derivative is continuous, the other end is connected with the outer end points of flowing capture duct curve, and at two, this point of connection place, linear portion is in a certain angle;
Six, determine osculating plane, air inlet being caught curve discrete is series of discrete point, does normal by each discrete point, by normal and to catch Curves in a series of planes of plane perpendicular to air inlet be exactly osculating plane;
Seven, in each osculating plane, determine the subpoint of close conic node, for arc section, in certain osculating plane, the subpoint of conic node is the center of circle of this arc section closely; For linear portion, because its radius of curvature is infinitely great, and will ensure to obtain straight line leading edge, so the subpoint of close conic node is determined by the intersection point of a particular line and osculating plane inter normal in certain osculating plane, this particular line must pass through the circular arc center of circle, and ensures that the line that corresponding discrete point on curve is caught in subpoint and air inlet has intersection point with flowing capture duct curve;
Eight, in each osculating plane, catch by the subpoint of Angle of Shock Waves, closely conic node and air inlet the summit that corresponding discrete point on curve determines cone closely;
Nine, according to Angle of Shock Waves and cruise Mach number, by solving the close coning tower tray field that Taylor-Maccoll equation obtains in each osculating plane, because all identical of Angle of Shock Waves and the cruise Mach number of all close cones calculates once;
Ten, in each osculating plane, determine the leading edge point of Waverider, this point is determined by the intersection point of flow capture duct and shock surface (being a line in osculating plane);
11, the leading edge point determined with step 10 in each osculating plane carries out streamlined impeller for starting point in circular cone flow field, follows the trail of to air inlet and catches Curves in plane, gained all streamline compositions Waverider lower surface;
12, the leading edge point determined with step 10 in each osculating plane carries out streamlined impeller for starting point in Free Flow Field, follows the trail of to air inlet and catches Curves in plane, gained all streamline compositions Waverider upper surface;
What 13, provided by circular cone flow field utilizes the force of cohesion method of calculating of reference temperature method and compression flat board to provide the 1ift-drag ratio of Waverider without viscosity flow field information under specified altitude assignment and fuselage length, and calculates volume efficiency (VE).
Cruise Mach number M is specified in step one
∞, flying height H and fuselage length L, the length of fuselage length linear portion OV as shown in Figure 2;
In step 2, Waverider sweepback angle λ as shown in Figure 2, determined by following formula by the upper limit:
λ<90°-sin
-1(1M
∞)
In step 3, the variation range of Angle of Shock Waves β is determined by following formula:
sin
-1(1M
∞)<β<90°-λ
Flowing capture duct curve in step 4 is as shown in the linear portion OE in Fig. 3, and be θ with horizon angle, its length s can be determined by following formula:
Air inlet in step 5 catches curve as shown in the segment of curve RAE in Fig. 3, and RA is arc section, and AE is linear portion, and some O is the center of circle of circular arc R A, and this curve can be calculated by following formula with the angle γ of flowing capture duct curve:
γ＝θ+sin
-1(tanλ·tanβ)
The length l of straightness accuracy AE can be calculated by following formula:
The radius r of circular arc R A can be calculated by following formula:
Discrete point in step 6 is as shown in " ◇ " in Fig. 4, and normal as shown in phantom in figure 4;
The subpoint of the close conic node in step 7 is as shown in the "○" in Fig. 4;
Close conic node in step 8 is as shown in the M point in Fig. 5, and this point is the summit of cone closely in the osculating plane of OFR place, and this position can be determined by the length of OM line segment, and the length of OM line segment is determined by the length of Angle of Shock Waves and OR line segment, and computing formula is as follows:
Close conic node in other osculating plane all uses same procedure to calculate.
Volume efficiency (VE) in step 13 adopts as given a definition:
Wherein S
pfor the plan area of Waverider.
Specifically be implemented as follows:
Setting flying condition is: 30 kilometers of height, the cruise Mach number of 6 Mach, and setting fuselage length is 20 meters, generates Waverider with this understanding and the vortex lift of its upper surface is described.
One, calculating the upper limit at sweepback angle according to cruise Mach number is 80.4 °, and it is 75 ° that this example gets sweepback angle;
Two, determine that Angle of Shock Waves is between 9.6 ° to 15 ° according to cruise Mach number and sweepback angle, this example gets 12 °;
Three, determine flowing capture duct curve, get 0 ° with horizontal angle, calculating this length of curve is 5.36 meters;
Four, determine that curve is caught in air inlet, calculating its linear portion with flowing capture duct curve angle is 52.5 °, and the length of linear portion is 8.80 meters, and the radius of circular arc is 6.76 meters;
Five, catching curve to air inlet carries out discrete, obtains discrete point, and by discrete point determination osculating plane, in each osculating plane, determines close conic node;
Six, be 6 Mach by Taylor-Maccoll equation solution free stream Mach number, Angle of Shock Waves is the circular cone flow field of 12 °;
Seven, calculate Waverider leading edge curve, be made up of the intersection point of the Conical Shock Wave in flowing capture duct and each osculation plane;
Eight, in each osculating plane, with the point on the Waverider leading edge curve calculated for starting point, streamlined impeller is done respectively in circular cone flow field and Free Flow Field, the stream interface of the streamline composition in circular cone flow field is the lower surface of Waverider, the stream interface of the streamline composition in Free Flow Field is the upper surface of Waverider, generates profile as shown in Figure 1;
Nine, the performance of Waverider is estimated: 1ift-drag ratio is 6.58, and volume efficiency (VE) is 0.2221;
Ten, upper surface vortex lift checking, use computational fluid mechanics instrument at 30 kilometers, when Mach number 6, calculate the Waverider flow field that the angle of attack is 0 °, 4 ° and the 6 ° angle of attack respectively, can find out 4 ° time, there is obvious meiobar in upper surface, when 6 °, this low pressure effect is more obvious.
The present invention is not limited to aforesaid detailed description of the invention.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (4)
1. the sharp apex that a sweepback angle is controlled bores Waverider closely, it is characterized in that the whole leading edge of described Waverider is straight line section, the angle at the sweepback angle of described linear portion leading edge is controlled at design phase, gas is caught curve and is made up of straight line section and one section of circular arc, circular arc is positioned near plane of symmetry side, and the center of circle is the end points that flowing capture duct curve is positioned on the plane of symmetry.
2. the sharp apex that a kind of sweepback angle according to claim 1 is controlled bores the generation method of Waverider closely, it is characterized in that comprising the following steps:
Step one, according to design needs, given cruise Mach number, flying height and fuselage length;
Step 2, determine sweepback angle, according to the upper limit at cruise Mach number determination Waverider sweepback angle, then need selection rational sweepback angle according to design;
Step 3, determine Angle of Shock Waves, first by the variation range of the upper limit determination Angle of Shock Waves at cruise Mach number and sweepback angle, then need selection rational Angle of Shock Waves according to design;
Step 4, given flowing capture duct curved surface, this curved surface by its bottom Waverider the drop shadow curve in the plane capture duct curve that flows determine, for ensureing to obtain straight line leading edge, this curve adopts a linear portion in a certain angle with horizon, and its length can be determined by fuselage length and sweepback angle;
Step 5, given air inlet catch curve, this curve is made up of straight line section and one section of circular arc, circular arc is positioned near plane of symmetry side, the center of circle is the end points that flowing capture duct curve is positioned on the plane of symmetry, linear portion is positioned at away from plane of symmetry side, and its one end is connected with circular arc, and point of connection place ensures that first derivative is continuous, the other end is connected with the outer end points of flowing capture duct curve, and at two, this point of connection place, linear portion is in a certain angle;
Step 6, determine osculating plane, air inlet being caught curve discrete is series of discrete point, does normal by each discrete point, by normal and to catch Curves in a series of planes of plane perpendicular to air inlet be exactly osculating plane;
Step 7, in each osculating plane, determine the subpoint of close conic node, for arc section, in certain osculating plane, the subpoint of conic node is the center of circle of this arc section closely;
Step 8, in each osculating plane, catch by the subpoint of Angle of Shock Waves, closely conic node and air inlet the summit that corresponding discrete point on curve determines cone closely;
Step 9, according to Angle of Shock Waves and cruise Mach number, by solving the close coning tower tray field that Taylor-Maccoll equation obtains in each osculating plane;
Step 10, in each osculating plane, determine the leading edge point of Waverider, this is determined by the intersection point of flowing capture duct and shock surface;
Step 11, the leading edge point determined with step 10 in each osculating plane carry out streamlined impeller for starting point in circular cone flow field, follow the trail of to air inlet and catch Curves in plane, gained all streamline compositions Waverider lower surface;
Step 12, the leading edge point determined with step 10 in each osculating plane carry out streamlined impeller for starting point in Free Flow Field, follow the trail of to air inlet and catch Curves in plane, gained all streamline compositions Waverider upper surface;
Step 13, provided by circular cone flow field under specified altitude assignment and fuselage length, utilize reference temperature method and the dull and stereotyped force of cohesion method of calculating of compression to provide the 1ift-drag ratio of Waverider without viscosity flow field information, and calculate volume efficiency (VE).
3. the sharp apex that a kind of sweepback angle according to claim 2 is controlled bores the generation method of Waverider closely, it is characterized in that the subpoint of conic node closely in certain osculating plane in described step 8 is determined by the intersection point of straight line and osculating plane inter normal.
4. the sharp apex that a kind of sweepback angle according to claim 3 is controlled bores the production method of Waverider closely, it is characterized in that the described straight-line pass circular arc center of circle, and the line that corresponding discrete point on curve is caught in subpoint and air inlet there is intersection point with flowing capture duct curve.
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| CN105674811A (en) * | 2016-03-07 | 2016-06-15 | 晋西工业集团有限责任公司 | Guided rocket missile with wave-rider structure |
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| CN106394874A (en) * | 2016-10-19 | 2017-02-15 | 中国航天空气动力技术研究院 | Wave rider of dual sweepback layout |
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| CN107298162A (en) * | 2017-07-03 | 2017-10-27 | 中国空气动力研究与发展中心计算空气动力研究所 | Waverider is bored in a kind of double sweepback of sharp apex with changeover portion closely |
| CN107253521A (en) * | 2017-07-03 | 2017-10-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Waverider is bored in a kind of double sweepback in curve head with changeover portion closely |
| CN107253521B (en) * | 2017-07-03 | 2019-12-24 | 中国空气动力研究与发展中心计算空气动力研究所 | Curve head double-sweepback osculating wave multiplier with transition section |
| 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 |
| CN109250144A (en) * | 2018-09-30 | 2019-01-22 | 中国人民解放军国防科技大学 | Method for designing osculating cone waverider with directly controllable sweepback angle and upper/lower dihedral angles |
| CN109250144B (en) * | 2018-09-30 | 2020-07-07 | 中国人民解放军国防科技大学 | Method for designing osculating cone waverider with directly controllable sweepback angle and upper/lower dihedral angles |
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| CN105059530B (en) | 2016-09-28 |
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