CN103143461A - Slider type Mach-number-variable spray pipe and wall determination method thereof - Google Patents
Slider type Mach-number-variable spray pipe and wall determination method thereof Download PDFInfo
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- CN103143461A CN103143461A CN2013100461516A CN201310046151A CN103143461A CN 103143461 A CN103143461 A CN 103143461A CN 2013100461516 A CN2013100461516 A CN 2013100461516A CN 201310046151 A CN201310046151 A CN 201310046151A CN 103143461 A CN103143461 A CN 103143461A
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Abstract
The invention provides a slider type Mach-number-variable spray pipe and a wall determination method thereof. The wall determination method of the slider type Mach-number-variable spray pipe comprises according to structural design requirements of the spray pipe, determining partial wall curve as a fixed wall curve, and determining a slider guide rail wall line, a slider wall curve, and a relation curve between a procession distance and an exit Mach number; according to the relation curve between the procession distance and the exit Mach number, using a characteristics method to determine a corresponding wall curve to be solved when the slider is located in a current position; changing the slider position on the slider guide rail to enable a currently designed Mach number value interval to cover all values of the exit Mach number in the relation curve between the procession distance and the exit Mach number, and determining each section of the wall curve to be solved; and determining the wall curve of the spray pipe according to the slider guide rail wall line, a fixed wall curve, the slider wall curve, and each section of the wall curve to be solved. The exit fluid field of the spray pipe determined with the method is high in uniformity, and the exit Mach number can well accord with an exit Mach number given in advance.
Description
Technical field
The present invention relates to the supersonic nozzle design field, determine method in particular to a kind of slide block type change Mach number jet pipe and wall thereof.
Background technology
Supersonic nozzle is widely used in the equipment such as high-speed aircraft, rocket, supersonic wind tunnel, high-energy laser, injection vavuum pump, and the performance of nozzle flow field product confrontation equipment has important impact.Obtain suitable jet pipe wall surface curve by certain designing technique and can greatly improve the nozzle flow field quality, improve equipment performance, save reasearch funds.Supersonic nozzle generally is comprised of contraction section and expansion segment, under certain pressure drove, gas accelerated gradually at contraction section, and reaches the velocity of sound near throat, then continue to accelerate at expansion segment, until at the supersonic flow that goes out the required Mach number of interruption-forming and flow direction angle distribution.
Along with aerodynamic high speed development of modern times and extensive use, become continuously the Mach number jet pipe and have more and more important application prospect.Particularly in the wind-tunnel field, the wind-tunnel of the being furnished with continuous change Mach number jet pipe state such as can the simulated flight device accelerate, slow down, cruise, once experiment is equivalent to tens even up to a hundred experiments of traditional single Mach number jet pipe and the flight environment of vehicle of more approaching reality.
Current two dimension becomes the Mach number jet pipe and mainly adopts relatively ripe flexible plate nozzle (flexible jet pipe) technology.The wall of flexible plate nozzle is the thin plate with certain rigidity, and the shape of thin plate is realized the change of nozzle contour by the position that changes fulcrum, and then obtained different outlet Mach numbers by some point control.But the actuation mechanism of existing flexible plate nozzle is very complicated, and each work Mach number needs a large amount of experiments to carry out the profile adjustment and the school, flow field is surveyed, and the outlet Mach number uniformity is not high.
Another uses less technology is the slide block type jet pipe that monograph " wind-tunnel design principle " (Wu Ronglin, Wang Zhenyu write, publishing house of Beijing Aeronaution College, 1985) provides.This jet pipe is arranged in the moving forward and backward of slide block of contraction section by adjustment, form size different throat section, and make the different jet pipe curve of the common formation of slide block and outer wall.But, existing slide block type jet pipe only by the relational expression constraint jet pipe curve of flow and Mach number, is considered mobile two dimension and three-dimensional feature, and flow field quality can't guarantee, off-design point Mach number unevenness is up to more than 20%-30%, and is very large on the confidence level impact of experimental data.
Summary of the invention
The present invention aims to provide a kind of slide block type change Mach number jet pipe and wall is determined method, and is bad with the flow field quality that solves slide block type change Mach number jet pipe in prior art, the problem that off-design point Mach number unevenness is high.
To achieve these goals, according to an aspect of the present invention, provide a kind of slide block type to become Mach number jet pipe wall and determined method, comprise: step 10: according to the nozzle structure designing requirement, determining section wall curve is as the fixed wall curve, and the relation curve of definite slide block guide rail wall line, the slide block wall curve that matches with this fixed wall curve and slide block precession distance and nozzle exit Mach number; Step 20: according to the slide block precession distance relation curve with the nozzle exit Mach number, wall curve corresponding to be asked when utilizing the method for characteristic curves to determine that slide block is in current location; Step 30: the edge is away from the position of direction change slide block on slide block guide rail of the outlet of jet pipe, make the interval of current design Mach number cover all values of the outlet Mach number in slide block precession distance and nozzle exit Mach number relation curve, determine each section wall curve to be asked; Step 40: determine that according to slide block guide rail wall line, fixed wall curve, the slide block wall curve that matches with this fixed wall curve and each section wall curve to be asked slide block type becomes Mach number jet pipe wall surface curve.
Further, step 10 also comprises: step 11: the end points of the slide block guide rail wall line port of export is determined in designing requirement according to nozzle structure, with slide block mobile one section initial distance on slide block guide rail, the coordinate of the initial point the when coordinate of then determining the subpoint of any point on slide block guide rail wall line on slide block wall curve is zero as the precession distance; Step 12: determine the minimum design Mach number of nozzle exit according to jet pipe work range of Mach numbers, one section jet pipe wall surface curve when adopting the method for characteristic curves to determine minimum design Mach number, and with this jet pipe wall surface curve as the fixed wall curve.
Further, step 12 comprises: step 121: nozzle exit height and nozzle exit area are determined in designing requirement according to nozzle structure, and the end points coordinate in definite fixed wall curve exit; Step 122: find the solution the jet pipe wall surface curve according to slide block guide rail wall line, slide block wall curve and the nozzle exit border employing method of characteristic curves, the end points of this jet pipe wall surface curve upper outlet end is the end points in fixed wall curve exit; Step 123: choose a bit utilizing on the determined jet pipe wall surface curve of the method for characteristic curves, the Mach number of this point is greater than a given Mach number that satisfies the designing requirement of jet pipe supersonic speed, this point on the fixed wall curve away from the end points of the port of export, and with on the end points in the exit of this fixed wall curve and fixed wall curve away from the jet pipe wall surface curve between the end points of the port of export as the fixed wall curve.
Further, step 20 comprises: step 21: determine the nozzle exit flow field parameter according to minimum design Mach number, adopt the method for characteristic curves to determine the backstepping characteristic curve that the fixed wall curve begins away from the end points of an end of outlet according to the nozzle exit flow field parameter; Step 22: adopt the method for characteristic curves to determine transonic speed characteristic curve according to minimum design Mach number; Step 23: according to the backstepping characteristic curve and transonic speed characteristic curve adopt the method for characteristic curves to determine the wall curve to be asked of the jet pipe that minimum design Mach number is corresponding.
Further, step 22 comprises: step 221: the entrance height of jet pipe is determined in designing requirement according to nozzle structure, determines the coordinate of entrance end points of the wall curve of jet pipe subsonic speed section according to the nozzle entry height; Step 222: adopt the Second Order Continuous curve method to find the solution jet pipe subsonic speed section wall curve under the current design Mach number near the coordinate of the end points of nozzle entry end according to jet pipe wall surface curve arrival end point coordinates; Step 223: determine wall curve current to be asked near the coordinate of the end points of nozzle entry end according to current design Mach number and jet pipe subsonic speed section wall curve, the jet pipe subsonic speed section wall curve that the end points of the close nozzle entry end of the entrance end points of the wall curve of jet pipe subsonic speed section and wall curve to be asked intercepts is as the subsonic speed section wall curve under the current design Mach number; Step 224: adopt the CFD method to determine jet pipe subsonic speed section flow field then to determine transonic speed initial value line according to jet pipe subsonic speed section wall curve; Step 225: adopt the saure method to determine transonic speed characteristic curve according to initial value line transonic speed.
Further, step 30 comprises: step 31: with slide block Moving Unit precession distance on slide block guide rail, determine the current design Mach number according to slide block precession distance with nozzle exit Mach number relation curve; Step 32: determine the nozzle exit flow field parameter according to the current design Mach number, adopt the method for characteristic curves to find the solution the backstepping characteristic curve according to the exit flow field parameter, the initial point of backstepping characteristic curve is that fixed wall is near the end points of slide block one end; Step 33: according to the current design Mach number, adopt the method for characteristic curves to determine transonic speed characteristic curve of jet pipe; Step 34: according to transonic speed characteristic curve and backstepping characteristic curve adopt the method for characteristic curves to determine wall curve current to be asked.
Further, the method for characteristic curves comprises estimates step and the step of correction, proofreaies and correct the step and proofreaies and correct according to estimating the result in step.
According to a further aspect in the invention, provide a kind of slide block type to become the Mach number jet pipe, slide block type becomes the wall of Mach number jet pipe and determines that by above-mentioned slide block type change Mach number jet pipe wall method is definite.
according to a further aspect in the invention, provide a kind of slide block type to become the Mach number jet pipe, comprise slide block guide rail, be arranged on movably the slide block on slide block guide rail, the first wall be connected wall, connecting wall is connected between slide block guide rail and the first wall, two both sides that connect on the width that wall lays respectively at slide block guide rail, the first wall comprises fixed wall and wall to be asked, fixed wall obtains after extending according to the fixed wall curve, wait asking wall to utilize definite the obtaining of the method for characteristic curves apart from the relation curve with the nozzle exit Mach number according to the slide block precession after asking wall to extend.
Use technical scheme of the present invention and can be achieved as follows technique effect: according to the nozzle structure designing requirement, determine the relation curve of slide block guide rail wall line, fixed wall curve, the slide block wall curve that matches with this fixed wall curve and slide block precession distance and nozzle exit Mach number; Wall curve corresponding to be asked when utilizing the method for characteristic curves to determine that slide block is in current location according to the slide block precession apart from the relation curve with the nozzle exit Mach number; Each section wall curve to be asked is progressively determined in the position of change slide block on slide block guide rail; Determine that according to fixed wall curve, the slide block wall curve that matches with this fixed wall curve and each section wall curve to be asked slide block type becomes the wall of Mach number jet pipe.This method is directly given the relation curve of fixed slider precession distance with the nozzle exit Mach number, rather than verify correlation curve afterwards, simplified computational process, the employing method of characteristic curves is determined the wall curve under each Mach number, the position relationship that guarantees nozzle exit Mach number and slide block meets given relation curve, the definite slide block of definite method of the present invention becomes the flexible controlling organization that the Mach number jet pipe does not relate to complexity simultaneously, simple in structure, it is convenient to control, and has also overcome the flow field problem of non-uniform of traditional one dimension design jet pipe.
Description of drawings
The accompanying drawing that consists of a part of the present invention is used to provide a further understanding of the present invention, and illustrative examples of the present invention and explanation thereof are used for explaining the present invention, do not consist of improper restriction of the present invention.In the accompanying drawings:
Fig. 1 shows slide block type of the present invention and becomes the schematic diagram that Mach number jet pipe wall is determined fixed wall curve, slide block guide rail and the slide block wall curve of method;
Fig. 2 shows according to slide block type of the present invention and becomes the schematic diagram that Mach number jet pipe wall is determined the first paragraph wall curve to be asked that method forms;
Fig. 3 shows according to slide block type according to the present invention and becomes the schematic diagram of method for solving that Mach number jet pipe wall is determined the transonic speed characteristic curve of method;
Fig. 4 shows according to slide block type of the present invention and becomes the schematic diagram that Mach number jet pipe wall is determined method formation second segment wall curve to be asked;
Fig. 5 shows according to slide block type of the present invention and becomes the schematic diagram that Mach number jet pipe wall is determined the 3rd section wall curve to be asked of method formation; And
Fig. 6 shows according to slide block type according to the present invention and becomes the schematic diagram of solution procedure that Mach number jet pipe wall is determined the characteristic curve equation of method.
The specific embodiment
Hereinafter also describe in conjunction with the embodiments the present invention in detail with reference to accompanying drawing.Need to prove, in the situation that do not conflict, embodiment and the feature in embodiment in the application can make up mutually.
In the present invention, the Mach number of supersonic speed section is greater than 1.2, and the Mach number of subsonic speed section is less than 0.8, and transonic speed the Mach number of section is between 0.8 to 1.2.
The value of unit precession distance is selected by the constraint of expansion ratio to the vertical range on slide block wall curve away from the end points of outlet one end by the fixed wall curve.
According to embodiments of the invention, slide block type becomes the wall of Mach number jet pipe and determines by the following method.
At first, to the relation curve X-Ma of fixed slider precession distance with the nozzle exit Mach number, according to the nozzle structure designing requirement, determine slide block guide rail wall line 1-2, slide block wall curve according to the nozzle structure designing requirement.
Referring to Fig. 1, slide block precession distance and the relation curve X-Ma of nozzle exit Mach number that satisfies as required determines the minimum design Mach number of jet pipe, adopts the method for characteristic curves to determine the fixed wall curve 3-4 of jet pipe under minimum design Mach number according to slide block guide rail wall line 1-2 and slide block wall curve.
Definite step of fixed wall curve 3-4 is: at first, nozzle exit height and nozzle exit position are determined in designing requirement according to nozzle structure, and then the parameter on the coordinate of the end points 3 of the coordinate of the end points 1 of the port of export on definite slide block guide rail wall line 1-2, the fixed wall curve 3-4 port of export and outlet border and outlet border, the parameter that wherein exports the border comprises outlet Mach number, back pressure etc.; The distance of end points between the end points 1 of the port of export on the subpoint on slide block guide rail wall line 1-2 and slide block guide rail wall line 1-2 of slide block wall curve end determined in designing requirement according to nozzle structure, and with this distance as initial distance, with slide block mobile one section initial distance on slide block guide rail, and on definite slide block wall curve, any point is as precession distance reference point, and the coordinate of the subpoint of this reference point on slide block guide rail wall line 1-2 is the coordinate of zero initial point as slide block precession distance; In the present embodiment, determine that slide block wall curve terminal point (being the end points of close nozzle exit end on slide block wall curve) is reference point, take the coordinate of coordinate as the precession distance as zero initial point of the subpoint of slide block wall curve terminal point on slide block guide rail wall line 1-2.Secondly, adopt the definite jet pipe wall surface curve that is set out by the end points 3 of the fixed wall curve port of export of the method for characteristic curves according to slide block guide rail wall line 1-2, slide block wall curve and outlet Mach number, at this moment, the minimum design Mach number of determining in the designing requirement of outlet Mach 2 ship nozzle structure.Then, designing requirement determines that fixed wall curve 3-4 goes up the coordinate away from the end points 4 of the port of export according to nozzle structure, the jet pipe wall surface curve of having asked that the end points 3 of this end points 4 and the fixed wall curve 3-4 port of export intercepts is fixed wall curve 3-4, and the value of the Mach number on this end points 4 should be greater than a set-point, this set-point makes jet pipe begin to be the supersonic speed section to the nozzle section between nozzle exit from end points 4, and this set-point is 1.05 in the present embodiment.
As shown in Figure 2, after the fixed wall curve 3-4 of the jet pipe of determining minimum design Mach number, can be according to the slide block precession distance relation curve X-Ma with the nozzle exit Mach number, the wall curve 4-t corresponding to be asked when to be in the precession distance be zero position that utilizes the method for characteristic curves to determine slide block.
The steps include: to determine the nozzle exit flow field parameter according to minimum design Mach number, adopt the method for characteristic curves to find the solution backstepping characteristic curve 4-5 according to exit flow field parameter, slide block guide rail wall line 1-2, slide block wall curve and fixed wall curve 3-4, the starting point of this backstepping characteristic curve 4-5 is away from the end points 4 of an end of outlet on the fixed wall curve.
In conjunction with referring to Fig. 3, the entrance height of jet pipe is determined in designing requirement according to nozzle structure, thereby determines the coordinate of end points a of wall curve of the nozzle entry end of subsonic speed section; Adopt the Second Order Continuous curve method or adopt bicubic curve method or other methods of finding the solution jet pipe subsonic speed section wall curve such as Vickers curve method or SPL method to determine jet pipe subsonic speed section wall curve according to end points a; Determine the coordinate of the nozzle throat point t under minimum design Mach number according to slide block wall curve, jet pipe subsonic speed section wall curve and throat's sonic line shape, the subsonic speed section curve that end points a and throat's point t intercept is the subsonic speed section wall curve under the minimum design Mach number of jet pipe; Adopt the CFD method to determine jet pipe subsonic speed section flow field then to determine transonic speed initial value line according to subsonic speed section wall curve, according to this transonic speed the initial value line adopt the saure method to determine transonic speed characteristic curve t-6.
Adopt the method for characteristic curves to find the solution wall curve 4-t to be asked under minimum design Mach number according to transonic speed characteristic curve t-6 and backstepping characteristic curve 4-5.Wherein transonic speed the intersection point 5 of the intersection point 6 of characteristic curve t-6 and slide block wall curve and backstepping characteristic curve 4-5 and slide block wall curve can be same point, also can be two different points.
Referring to Fig. 4, after first paragraph wall curve the to be asked 4-t of the jet pipe of determining minimum design Mach number, can be with slide block along slide block guide rail wall alignment jet pipe upstream Moving Unit precession distance, also namely to the direction Moving Unit distance near nozzle entry, the value of this unit precession distance is selected by the constraint of expansion ratio to the vertical range on slide block wall curve away from the end points 3 of outlet one end by the fixed wall curve.Current design Mach number when determining that with nozzle exit Mach number relation curve X-Ma slide block is in current location according to the precession distance.
The new fixed wall curve 3-t that first paragraph wall curve to be asked 4-t and fixed wall curve 3-4 form, according to new fixed wall curve 3-t and nozzle exit point 3 place's current design Mach numbers, utilize the method for characteristic curves, determine new backstepping characteristic curve t-5 ', determine the entrance height of jet pipe according to current design Mach number and nozzle structure designing requirement, thereby determine the coordinate of end points a ' of arrival end of the wall curve of jet pipe subsonic speed section; Adopt Second Order Continuous curve method or other methods of finding the solution the new subsonic speed section wall curve of jet pipe to determine the subsonic speed section wall curve that jet pipe is new according to end points a '; Determine the coordinate of the nozzle throat point t ' under corresponding with it current design Mach number according to slide block wall curve and new subsonic speed section wall curve, the jet pipe subsonic speed section wall curve that intercepts according to end points a ' and throat's point t ' is as the jet pipe subsonic speed section wall curve under the current design Mach number, adopt the CFD method to determine new jet pipe subsonic speed section flow field according to new subsonic speed section wall curve, then determine new transonic speed initial value line, adopt the saure method to determine new transonic speed characteristic curve t '-6 ' according to new transonic speed initial value line.
Adopt the method for characteristic curves to find the solution wall curve t-t ' to be asked under the current design Mach number according to new transonic speed characteristic curve t '-6 ' and new backstepping characteristic curve t-5 '.
Participate in Fig. 5, at second segment wall curve the to be asked t-t ' that determines jet pipe afterwards, can be again with slide block along slide block guide rail wall alignment upstream Moving Unit precession distance, also namely to the direction Moving Unit precession distance near nozzle entry, and definite new current design Mach number and new fixed wall curve 3-t ', and definite new backstepping characteristic curve t '-5 " and new transonic speed characteristic curve t "-6 ", adopt the method for characteristic curves to find the solution wall curve t ' to be asked-t ".
Repeat successively above-mentioned steps, until the value of current design Mach number covers the value of all Mach numbers in whole precession distance and nozzle exit Mach number relation curve X-Ma.Wall curve to be asked according to each section, fixed wall curve, slide block guide rail line and slide block wall curve are determined the wall curve of jet pipe.
Find the solution the process of a characteristic curve unit as shown in Figure 6.
The process of finding the solution a characteristic curve unit is as follows:
Suppose two point (x on known curve
1, r
1, M
1, θ
1), (x
2, r
2, M
2, θ
2), need to find the solution thirdly (x
3, r
3, M
3, θ
3) time, can utilize process shown in Figure 6 to find the solution.
In solution procedure, at first according to estimating the step to thirdly finding the solution, then the value of finding the solution is proofreaied and correct, to proofread and correct coordinate thirdly afterwards, Mach number and flow direction angle.
Estimate to go on foot and comprise:
First find the solution (x
3, r
3),
μ
1=sin
-1(1/M
1)
μ
2＝sin
-1(1/M
2)
h
1=tan[θ
1+μ
1]
h
2=tan[θ
2-μ
2]
Have according to difference equation:
r
3-r
1=h
1(x
3-x
1)
r
3-r
2=h
2(x
3-x
2)
Two formulas are subtracted each other and can be got:
r
1-r
2={h
2-h
1}x
3+x
1h
1-x
2h
2
Try to achieve coordinate thirdly
The below finds the solution the compatibility relation formula:
Order:
Have:
g
1(M
3-M
1)-(θ
3-θ
1)-f
1=0
g
2(M
3-M
2)+(θ
3-θ
2)-f
2=0
Thereby obtain Mach number and the flow direction angle at place, position thirdly:
θ
3=g
1(M
3-M
1)+θ
1-f
1
μ
3=sin
-1(1/M
3)
In above-mentioned formula, M1 is the Mach number at place, first position, and μ 1 is the Mach angle at place, first position, and θ 1 is the flow direction angle at place, first position, x1 is the abscissa at place, first position, r1 is the ordinate at place, first position, and γ is the specific heat at constant pressure of gas and the specific heat ratio of specific heat at constant volume, and M is local Mach number and M〉1, δ is the pattern of flow parameter, for two-dimensional flow δ=0, Three-dimensional Axisymmetric δ=1 of flowing, r ≠ 0.
M2 is the Mach number at place, second point position, and μ 2 is the Mach angle at place, second point position, and θ 2 is the flow direction angle at place, second point position, and x2 is the abscissa at place, second point position, and r2 is the ordinate at place, second point position.
M3 is the Mach number at position place thirdly, and μ 3 be the Mach angle at place, position thirdly, and θ 3 be the flow direction angle at place, position thirdly, and x3 is the abscissa located of position thirdly, and r3 is the ordinate located of position thirdly.
Solve the coordinate, Mach number and flow direction angle at place, position thirdly in estimating the step after, the coefficient of equation or parameter are averaged repeat to estimate the computational process in step, thirdly Mach number and flow direction angle are proofreaied and correct.This parameter or coefficient mean value can be found the solution by the Mach number thirdly of trying to achieve and flow direction angle, order
M wherein
1' be first the Mach number mean value after proofreading and correct, M
2' Mach number mean value for second point after proofreading and correct, then with M
1' and M
2' the value substitution estimate and proceed in the step to find the solution, until the correction of a final proof step thirdly Mach number of trying to achieve with estimate the thirdly Mach number M that tries to achieve in the step
3Location of equal, the final Mach number after the Mach 2 ship at the place, thirdly present position of this moment is proofreaied and correct.In like manner, thirdly the flow direction angle at position place also can go on foot acquisition final flow direction angle by correction.
according to embodiments of the invention, provide a kind of slide block type to become the Mach number jet pipe, comprise slide block guide rail, be arranged on movably the slide block on slide block guide rail, the first wall be connected wall, connecting wall is connected between slide block guide rail and the first wall, two both sides that connect on the width that wall lays respectively at slide block guide rail, the first wall comprises fixed wall and wall to be asked, fixed wall obtains after extending according to the fixed wall curve, wait asking wall to utilize definite the obtaining of the method for characteristic curves apart from the relation curve with the nozzle exit Mach number according to the slide block precession after asking wall to extend.
From above description, can find out, the above embodiments of the present invention have realized following technique effect: slide block type becomes the wall of Mach number jet pipe according to the nozzle structure designing requirement, determine slide block guide rail wall line, fixed wall curve, the slide block wall curve that matches with this fixed wall curve and slide block precession apart from the relation curve of nozzle exit Mach number; Wall curve corresponding to be asked when utilizing the method for characteristic curves to determine that slide block is in current location according to the slide block precession apart from the relation curve with the nozzle exit Mach number; Each section wall curve to be asked is progressively determined in the position of change slide block on slide block guide rail; Determine that according to fixed wall curve, the slide block wall curve that matches with this fixed wall curve and each section wall curve to be asked slide block type becomes the wall of Mach number jet pipe.This method is directly given the relation curve of fixed slider precession distance with the nozzle exit Mach number, rather than verify correlation curve afterwards, simplified computational process, the employing method of characteristic curves is determined the wall curve under each Mach number, the position relationship that guarantees nozzle exit Mach number and slide block meets given relation curve, the definite slide block of definite method of the present invention becomes the flexible controlling organization that the Mach number jet pipe does not relate to complexity simultaneously, simple in structure, it is convenient to control, and has also overcome the flow field problem of non-uniform of traditional one dimension design jet pipe.
The above is only the preferred embodiments of the present invention, is not limited to the present invention, and for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (9)
1. a slide block type change Mach number jet pipe wall is determined method, it is characterized in that, comprising:
Step 10: according to the nozzle structure designing requirement, determining section wall curve is as the fixed wall curve, and the relation curve of definite slide block guide rail wall line, the slide block wall curve that matches with this fixed wall curve and slide block precession distance and nozzle exit Mach number;
Step 20: according to the slide block precession distance relation curve with the nozzle exit Mach number, wall curve corresponding to be asked when utilizing the method for characteristic curves to determine that slide block is in current location;
Step 30: the edge is away from the position of direction change slide block on slide block guide rail of the outlet of jet pipe, make the interval of current design Mach number cover all values of the outlet Mach number in the relation curve of slide block precession distance and nozzle exit Mach number, determine each section wall curve to be asked;
Step 40: determine that according to slide block guide rail wall line, fixed wall curve, the slide block wall curve that matches with this fixed wall curve and each section wall curve to be asked slide block type becomes Mach number jet pipe wall surface curve.
2. slide block type change Mach number jet pipe wall according to claim 1 is determined method, it is characterized in that, described step 10 also comprises:
Step 11: the end points of the slide block guide rail wall line port of export is determined in designing requirement according to nozzle structure, with slide block mobile one section initial distance on slide block guide rail, the coordinate of the initial point the when coordinate of then determining the subpoint of any point on slide block guide rail wall line on slide block wall curve is zero as the precession distance;
Step 12: determine the minimum design Mach number of nozzle exit according to jet pipe work range of Mach numbers, one section jet pipe wall surface curve when adopting the method for characteristic curves to determine minimum design Mach number, and with this jet pipe wall surface curve as the fixed wall curve.
3. slide block type change Mach number jet pipe wall according to claim 2 is determined method, it is characterized in that, described step 12 comprises:
Step 121: nozzle exit height and nozzle exit area are determined in designing requirement according to nozzle structure, and the end points coordinate in definite fixed wall curve exit;
Step 122: find the solution the jet pipe wall surface curve according to slide block guide rail wall line, slide block wall curve and the nozzle exit border employing method of characteristic curves, the end points of this jet pipe wall surface curve upper outlet end is the end points in fixed wall curve exit;
Step 123: choose a bit utilizing on the determined jet pipe wall surface curve of the method for characteristic curves, the Mach number of this point is greater than a given Mach number that satisfies the designing requirement of jet pipe supersonic speed, this point on the fixed wall curve away from the end points of the port of export, and with on the end points in the exit of this fixed wall curve and fixed wall curve away from the jet pipe wall surface curve between the end points of the port of export as the fixed wall curve.
4. slide block type change Mach number jet pipe wall according to claim 2 is determined method, it is characterized in that, described step 20 comprises:
Step 21: determine the nozzle exit flow field parameter according to minimum design Mach number, adopt the method for characteristic curves to determine the backstepping characteristic curve that the fixed wall curve begins away from the end points of an end of outlet according to the nozzle exit flow field parameter;
Step 22: adopt the method for characteristic curves to determine transonic speed characteristic curve according to minimum design Mach number;
Step 23: according to the backstepping characteristic curve and transonic speed characteristic curve adopt the method for characteristic curves to determine the wall curve to be asked of the jet pipe that minimum design Mach number is corresponding.
5. slide block type change Mach number jet pipe wall according to claim 4 is determined method, it is characterized in that, described step 22 comprises:
Step 221: the entrance height of jet pipe is determined in designing requirement according to nozzle structure, determines the coordinate of entrance end points of the wall curve of jet pipe subsonic speed section according to the nozzle entry height;
Step 222: adopt the Second Order Continuous curve method to find the solution jet pipe subsonic speed section wall curve under the current design Mach number near the coordinate of the end points of nozzle entry end according to jet pipe wall surface curve arrival end point coordinates;
Step 223: determine wall curve current to be asked near the coordinate of the end points of nozzle entry end according to current design Mach number and jet pipe subsonic speed section wall curve, the jet pipe subsonic speed section wall curve that the end points of the close nozzle entry end of the entrance end points of the wall curve of jet pipe subsonic speed section and wall curve to be asked intercepts is as the subsonic speed section wall curve under the current design Mach number;
Step 224: adopt the CFD method to determine jet pipe subsonic speed section flow field then to determine transonic speed initial value line according to jet pipe subsonic speed section wall curve;
Step 225: adopt the saure method to determine transonic speed characteristic curve according to initial value line transonic speed.
6. slide block type change Mach number jet pipe wall according to claim 5 is determined method, it is characterized in that, described step 30 comprises:
Step 31: with slide block Moving Unit precession distance on slide block guide rail, determine the current design Mach number according to slide block precession distance with nozzle exit Mach number relation curve;
Step 32: determine the nozzle exit flow field parameter according to the current design Mach number, adopt the method for characteristic curves to find the solution the backstepping characteristic curve according to the exit flow field parameter, the initial point of described backstepping characteristic curve is that described fixed wall is near the end points of described slide block one end;
Step 33: according to the current design Mach number, adopt the method for characteristic curves to determine transonic speed characteristic curve of jet pipe;
Step 34: according to transonic speed characteristic curve and backstepping characteristic curve adopt the method for characteristic curves to determine wall curve current to be asked.
7. according to claim 1 to 6, the described slide block type change of any one Mach number jet pipe wall is determined method, it is characterized in that, the described method of characteristic curves comprises estimates step and the step of correction, and described correction step basis is estimated the result in step and proofreaied and correct.
8. a slide block type becomes the Mach number jet pipe, it is characterized in that, described slide block type becomes the wall of Mach number jet pipe and determines that by the described slide block type change of any one in claim 1 to 7 Mach number jet pipe wall method is definite.
9. a slide block type becomes the Mach number jet pipe, it is characterized in that, comprise slide block guide rail, be arranged on movably the slide block on slide block guide rail, the first wall be connected wall, described connection wall is connected between described slide block guide rail and described the first wall, two described connection walls lay respectively at the both sides on the width of described slide block guide rail, described the first wall comprises fixed wall and wall to be asked, described fixed wall obtains after extending according to the fixed wall curve, described wait asking wall to utilize definite the obtaining of the method for characteristic curves apart from the relation curve with the nozzle exit Mach number according to the slide block precession after asking wall to extend.
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