CN102748135B - Method for designing fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel - Google Patents
Method for designing fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel Download PDFInfo
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- CN102748135B CN102748135B CN 201210264341 CN201210264341A CN102748135B CN 102748135 B CN102748135 B CN 102748135B CN 201210264341 CN201210264341 CN 201210264341 CN 201210264341 A CN201210264341 A CN 201210264341A CN 102748135 B CN102748135 B CN 102748135B
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Abstract
The invention discloses a method for designing a fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel. A basic structure of the adopted two-dimensional mixed-compression type air inlet channel comprises an outer pressing section, an inner pressing section, a throat section, an expanding section and a lip. The lip is of a sharp plate structure with a certain wedge angle. When the air inlet channel is designed, designed starting Mach number is improved appropriately, the lip shape is changed, and the starting mach number is effectively reduced to be lower than a requested value through a certain flow on the premise that the flow requirement of the air inlet channel is met. By means of the method, the requirement for starting performance can be met, contraction ratio of the air inlet channel can be increased in design, and accordingly high back pressure resisting capability and low outlet Mach number are obtained in a wide working range to facilitate efficiently combusted organizations in a combustion chamber. Furthermore, small total pressure loss in the working process of the air inlet channel can be achieved through the change of the lip shape. The method for designing the fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel has good actual application value.
Description
Technical field
The present invention relates to a kind of design method for ramjet engine air inlet, specifically, relate to a kind of design method of fixed how much binary Mixed-Compression Supersonic Inlets.Be specially adapted to the design of inferior burning ramjet intake duct.
Background technique
To work Mach number higher inferior burning ramjet, Ducted rocket for example, the binary mixed compression inlet is simple in structure with it, angle of attack characteristic and lifting resistance characteristic preferably advantage be used as one of intake duct form of extensive employing.
Have disclosed document " wide Mach number rushes the two dimensional inlet design and research admittedly " (Acta Astronautica now, Vol.29, No.5,2008,1577-1582) and the common design method of the fixed how much binary mixed compression inlets of describing in " Optimum Design for 2-D Inlet Working in Condition of Large Angle of Attack " literary compositions such as (AIAA 2009-36,2009) be based on the classical shock strengths such as Oswatitsch and join that ripple theory or isentropic Compression theory carry out.After selected design point and Start mach number, in conjunction with pneumatic principle and certain optimized algorithm, the state based on " shock on lip " completes compression wave system and each crucial geometric parameter design of intake duct.Then rule of thumb, or the correction of numerical simulation finally complete whole Configuration Designs of intake duct.But the binary mixed compression inlet that uses these method designs to obtain can obtain performance preferably near design point, but often is difficult to all obtain performance preferably in wider operating range.
The objective of the invention is by when designing the binary mixed compression inlet, suitably improve its design Start mach number, change in conjunction with the lip shape, sacrifice with certain flow under the prerequisite that meets intake duct flow demand is reduced to Start mach number below required value effectively, during by design, adopt larger contraction ratio to obtain higher anti-back-pressure ability and lower outlet Mach number, utilize the change of lip shape to obtain larger total pressure recovery coefficient simultaneously.
Summary of the invention
For fear of the deficiencies in the prior art part, the present invention proposes a kind of design method of fixed how much binary Mixed-Compression Supersonic Inlets.Its objective is when the design intake duct, suitably will design Start mach number and improve, change its lip shape, by sacrificing certain flow, effectively Start mach number is reduced to below required value under the prerequisite that meets intake duct flow demand.It can not only meet the starting performance requirement of intake duct, and can increase in when design the contraction ratio of intake duct, thereby make its in wider operating range, obtain higher anti-back-pressure ability and lower outlet Mach number be beneficial to firing chamber in the tissue of efficient burning.In addition, the change of lip shape also can bring pitot loss less in the intake duct working procedure.
The technical solution adopted for the present invention to solve the technical problems is: the basic configuration of the binary mixed compression inlet of employing comprises external pressure section, interior pressure section, venturi section, extending section, lip, and lip is the sharp plate structure with certain angle of wedge; It is characterized in that step is as follows:
Step 2. is determined Mach numerical value, will design Start mach number and suitably bring up to certain value, and improvement value is no more than 10% relatively;
Step 3. is according to gas dynamics, pneumatic relation based on after shock wave front, the one-dimensional aerodynamic model is set up in intake duct each oblique shock wave junction when design point is worked of take to lip as threshold state, and is optimized in conjunction with suitable optimized algorithm, completes the wave system design of intake duct;
Step 4. completes determining of binary mixed compression inlet throat height according to the starting maxim of relation of internal compressioninlet;
Step 5. is according to the correction of numerical simulation and complete the Geometric configuration design of pressing section, venturi section and extending section in two dimensional inlet in conjunction with design experiences;
Step 6. suitably cuts off a part or many parts by lip, and the gross area size cut off is decided by the raising degree of the relatively initial required value of design Start mach number, but is no more than 50% of lip plate area; The every part cut off all take the lip leading edge certain a bit or certain 2 be starting point and terminal.
The invention has the beneficial effects as follows:
(1) under the prerequisite that meets intake duct flow demand, lip is sheared certain area, can in the intake duct starting process, Start mach number be reduced the extra overflow by the lip indentation, there effectively, meets the starting capability requirement of intake duct.
(2) will design Start mach number suitably improves, can obtain larger intake duct contraction ratio, not only can improve the anti-back-pressure ability of intake duct in identical work range of Mach numbers, and can reduce the outlet Mach number of intake duct, be conducive to burn more efficiently in firing chamber inner tissue.
(3) because lip is sheared the rear extra overflow increased, the shock strength in the intake duct compression process can weaken to some extent, thereby total pressure recovery coefficient is increased, and the lifting that higher stagnation pressure is the motor overall performance provides condition.
(4) flow loss of lip shearing indentation, there is no more than 3% in the intake duct starting process, and in the operating range of whole intake duct, maximum is no more than 8%, belongs to tolerance interval.
(5) lip alteration of form method is simple, on the intake duct basic configuration basis that only need to complete in design, lip is carried out to a little change, and machining easily realizes.
The accompanying drawing explanation
Design method below in conjunction with drawings and embodiments to a kind of fixed how much binary Mixed-Compression Supersonic Inlets of the present invention is described in further detail.
The basic configuration that Fig. 1 is binary mixed compression inlet of the present invention.
The plan view that Fig. 2 is binary mixed compression inlet of the present invention.
Fig. 3 is the binary mixed compression inlet plan view that method design that the present invention proposes obtains.
Fig. 4 is the lip schematic diagram after shape for a change.
In figure:
1. the interior pressure of external pressure section 2. section 3. venturi section 4. extending section 5. lips
Embodiment
Consult Fig. 1, Fig. 2, Fig. 3, Fig. 4, the fixed how much binary Mixed-Compression Supersonic Inlets of the present invention comprise external pressure section 1, interior pressure section 2, venturi section 3, extending section 4, lip 5, and lip 5 is interior parts of pressing section, is the sharp plate structure with certain angle of wedge.
The binary Mixed-Compression Supersonic Inlet need be selected the rational design point of intake duct used, be caught flow and Start mach number according to the trajectory requirement of its aircraft when design, and determines accordingly catching highly and geometric widths of intake duct; The Design of Inlet point that the present embodiment is chosen is: flying height 10km, design Mach number 3.0; Catch flow 4kg/s; Start mach number 2.2.It is 150mm that the present embodiment is selected the width of intake duct accordingly, and catching is highly 72mm.When adopting the design method design intake duct of the fixed how much binary Mixed-Compression Supersonic Inlets of the present invention, will design Start mach number and suitably bring up to certain value, improvement value is no more than 10% relatively; The present embodiment will design Start mach number and bring up to 2.35 from 2.2, thereby make Start mach number improve 7%.Utilize gas dynamics, pneumatic relation based on after shock wave front, the one-dimensional aerodynamic model is set up in intake duct each oblique shock wave junction when design point is worked of take to lip as threshold state, and be target in conjunction with genetic algorithm to the maximum with the inlet total pres sure recovery coefficient and be optimized, obtaining total compression angle and the compression angle at different levels of two dimensional inlet, compression angles at different levels are respectively 17.5 °, 8.1 °, 9.4 °, 8.3 °, 9.2 °.After completing basic wave system design, according to the starting maxim of relation of internal compressioninlet, complete determining of binary mixed compression inlet throat height; In the present embodiment, the venturi height of intake duct is 36mm, and total contraction ratio of intake duct is 2.2.Complete the Geometric configuration design of pressing section 2, venturi section 3 and extending section 4 in two dimensional inlet according to the correction of numerical simulation and in conjunction with design experiences; Venturi section 3 length to height ratios of choosing intake duct in the present embodiment are 2.0, and the one-sided angle of flare of extending section 4 is 3 degree, and divergence ratio is 2.0.After completing basic Geometric configuration design, inlet lip 5 is suitably cut off to certain area or many parts, the gross area size cut off is decided by the raising degree of the relatively initial required value of design Start mach number, but is no more than 50% of lip plate area; The every part cut off all take the lip leading edge certain a bit or certain 2 be starting point and terminal.The present embodiment is sheared according to lip 5 shapes in Fig. 4, cuts off two gables, makes lip 5 form the isosceles triangle that drift angles are 120 degree, and the two-part that cut off are all usingd respectively the mid point of lip 5 leading edges and end points as starting point and terminal.Design completing fixed how much binary mixed compression inlets, obtain its performance by numerical simulation.
For convenient contrast, selected design main points and the initial start Mach number for the present embodiment, use identical method design to obtain a binary mixed compression inlet, except total compression angle and compression angle at different levels (14.5 °, 7.3 °, 7.2 °, 6.9 °, 7.6 °, total contraction ratio 2.0) outside difference, other geometric configuration parameter is chosen identical value, and numerical simulation obtains the results are shown in chart:
Can find out from top chart, have a critical mach number, when the incoming flow Mach number, during higher than this critical mach number, the binary mixed compression inlet that the method design that adopts the present invention to propose obtains is more excellent than the inlet characteristic that adopts the conventional method design to obtain; During lower than it, the former performance is slightly poor.This critical mach number generally is greater than the design Start mach number after raising, and, for different performance index, this critical mach number is different.
But, the intake duct starting Mach number that adopts the inventive method design to obtain in the present embodiment is only 2.1, still lower than required value 2.2, illustrate and also there is very large room for promotion, make this critical mach number approach and newly get fixed Start mach number 2.35 as far as possible, thereby make intake duct obtain more excellent performance in wider work range of Mach numbers.
Therefore, the design method that the present invention proposes can be under the prerequisite that meets intake duct flow demand, improve the design Start mach number, by changing the lip shape, sacrifice certain flow and obtain the ability that the more excellent starting performance of binary mixed compression inlet, total pressure recovery coefficient, outlet velocity and flame resistant form back-pressure, actual application value is preferably arranged.
Claims (1)
1. the design method of fixed how much binary Mixed-Compression Supersonic Inlets, the basic configuration of the binary mixed compression inlet of employing comprises external pressure section, interior pressure section, venturi section, extending section, lip, lip be with the sharp plate structure of the angle of wedge necessarily; It is characterized in that step is as follows:
Step 1. is selected parameter, according to the trajectory demand of different aircraft, selectes the rational design point of intake duct used, catches flow and Start mach number, and determine accordingly catching highly and geometric widths of intake duct;
Step 2. is determined Mach numerical value, will design Start mach number and suitably bring up to certain value, and improvement value is no more than 10% relatively;
Step 3. is according to gas dynamics, pneumatic relation based on after shock wave front, the one-dimensional aerodynamic model is set up in intake duct each oblique shock wave junction when design point is worked of take to lip as threshold state, and is optimized in conjunction with suitable optimized algorithm, completes the wave system design of intake duct;
Step 4. completes determining of binary mixed compression inlet throat height according to the starting maxim of relation of internal compressioninlet;
Step 5. is according to the correction of numerical simulation and complete the Geometric configuration design of pressing section, venturi section and extending section in two dimensional inlet in conjunction with design experiences;
Step 6. suitably cuts off a part or many parts by lip, and the gross area size cut off is decided by the raising degree of the relatively initial required value of design Start mach number, but is no more than 50% of lip plate area; The every part cut off all take the lip leading edge certain a bit or certain 2 be starting point and terminal.
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| CN102996253B (en) * | 2012-12-31 | 2015-03-04 | 中国人民解放军国防科学技术大学 | Supersonic air intake duct and wall face determination method of supersonic air intake duct |
| US9896219B2 (en) * | 2015-02-20 | 2018-02-20 | The Boeing Company | Flow inlet |
| US9964038B2 (en) * | 2015-03-16 | 2018-05-08 | The Boeing Company | Supersonic caret inlet system leading edge slat for improved inlet performance at off-design flight conditions |
| CN104975950B (en) * | 2015-06-16 | 2017-09-29 | 南京航空航天大学 | The binary hypersonic inlet of wall pressure distribution is specified to determine method |
| CN105069221B (en) * | 2015-08-04 | 2016-05-11 | 中国航天空气动力技术研究院 | For the critical Calculation Methods for Performance of Supersonic Inlet optimal design |
| CN105156212B (en) * | 2015-10-09 | 2017-08-29 | 西北工业大学 | A kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet |
| CN105351100B (en) * | 2015-10-29 | 2017-06-09 | 西北工业大学 | A kind of rocket based combined cycle engine inlets distance piece structure design |
| CN108088679B (en) * | 2016-11-23 | 2019-08-13 | 北京机电工程研究所 | Two dimensional inlet experimental rig |
| CN107061011B (en) * | 2017-06-02 | 2019-01-04 | 南京航空航天大学 | Low extrernal resistance hypersonic inlet |
| CN107091157B (en) * | 2017-06-05 | 2018-07-27 | 南京航空航天大学 | It is a kind of to determine geometry binary hypersonic inlet and design method |
| CN108592085B (en) * | 2018-03-09 | 2020-10-16 | 西北工业大学 | Variable geometry supersonic combustion chamber |
| CN110160792B (en) * | 2018-11-15 | 2020-12-25 | 北京机电工程研究所 | Dynamic simulation test method for power system |
| CN112177797B (en) * | 2020-09-16 | 2021-11-05 | 西北工业大学 | Solid rocket engine without spray pipe |
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