CN106184719B - A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle - Google Patents
A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle Download PDFInfo
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- CN106184719B CN106184719B CN201610810260.4A CN201610810260A CN106184719B CN 106184719 B CN106184719 B CN 106184719B CN 201610810260 A CN201610810260 A CN 201610810260A CN 106184719 B CN106184719 B CN 106184719B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
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Abstract
The present invention provides a kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle, and the purpose for adjusting aircraft torque is realized by no-movable part.The porous flow control apparatus includes the gas vent for being opened in the air admission hole of Vehicle nose and being opened in aircraft tail portion, by the way that the duct progress unicom in aircraft interior is arranged between air admission hole and gas vent.By the head trepanning of aircraft, the high pressure gas after Vehicle nose's bowshock is introduced into inner duct, is sprayed in aircraft tail portion using the high pressure gas of inner duct as the air source of porous jet flow, avoids carrying around extra injection working medium.
Description
Technical field
The present invention relates to hypersonic aircraft technical field, more particularly to it is a kind of be applied to it is hypersonic it is motor-driven reenter it is winged
The porous flow control apparatus of row device.
Background technology
Motor-driven reentry vehicle flight control hypersonic at present is mainly using airvane, body wing flap (Body Flap) etc.
Movable pneumatic face control technology and attitude control engine control of the reactive force (RCS, Reaction Control System) etc. are multiple
Close control technology.Under high altitude conditions, atmospheric density declines rapidly, causes pneumatic face control efficiency relatively low.Airvane rudder simultaneously
Axis, body wing flap leading edge portion hot-fluid are larger, and larger challenge is brought to thermal protection struc ture design.
The one kind of RCS technologies as active flow control technique needs to carry fuel tank or gas cylinder, increase finishes
Structure weight, this brings certain limitation to its reliability application.Simultaneously under the conditions of dense atmosphere, Shock/Boundary-Layer interference is led
The flow separation of cause can reduce pneumatic face control efficiency and RCS control efficiencies, therefore hypersonic flight control problem is to height
The design of supersonic speed maneuverable reentry vehicle brings larger challenge.
Invention content
For the deficiency of the RCS technologies and movable part Pneumatic Control Technology that use in the prior art, the purpose of the present invention
It is to provide a kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle, is realized by no-movable part
Adjust the purpose of aircraft torque.
To achieve the goals above, the technical scheme is that：
A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle, including it is opened in aircraft head
The air admission hole in portion and the gas vent for being opened in aircraft tail portion, by being arranged in aircraft interior between air admission hole and gas vent
Duct carry out unicom.
In the present invention, the air admission hole is 1 or multiple round holes, and the axis of the air admission hole is perpendicular to air admission hole institute
On aircraft fuselage surface.Further, if the quantity that air admission hole opens up is 1, which is opened in aircraft head
Portion stationary point position.If the quantity that air admission hole opens up is multiple, multiple air admission holes are opened in Vehicle nose and along aircraft
Mandrel line is circumferentially to being uniformly distributed.
Air inlet hole number, aperture depend on whole air inlet area.It is opened in all air admission holes formation of Vehicle nose
Whole air inlet area is about the 5%~10% of aircraft fuselage bottom area, and the too small then torque adjusting effect of air inlet area is unknown
Aobvious, air inlet area is excessive, can reduce fuselage interior dischargeable capacity.Air admission hole aperture should be not less than 0.5mm.All air admission holes are equal
It is connected to the duct of aircraft interior.
In the present invention, the gas vent is arranged in each lateral surface of aircraft tail portion.The lateral surface of aircraft tail portion is set
It is equipped with multigroup unilateral exhaust unit.Unilateral exhaust unit is made of multiple gas vents, multiple gas vents in unilateral exhaust unit
Array distribution can be used.Unilateral exhaust unit may include multiple rows of gas vent.The shape of gas vent is generally circular, each to be vented
The axis in hole is perpendicular to aircraft fuselage surface where each gas vent.
In the present invention, duct is cavity structure, and duct arrangement is located proximate to aircraft outer surface.The reality of the duct
Now form can be：Cavity between the shell and aircraft inner cone of aircraft forms the culvert of unicom air admission hole and gas vent
Road.The partition board of polylith longitudinal direction is provided between aircraft skin and aircraft inner cone.The effect of partition board be duct is separated into it is more
A son field, polylith partition board are circularly and evenly distributed around the central axis of duct.
The duct include by air admission hole common segment and be branched off into the son field of each unilateral exhaust unit.Described point
The number of branch section is identical as the unilateral group number of exhaust unit.All air admission holes correspond to the common segment of unicom duct, duct it is public
Section and the joint of each son field are both provided with valve, the opening and closing of the son field for controlling each duct.Air-flow from into
Stomata enters after the common segment of duct each son field through duct from each unilateral exhaust unit row on aircraft lateral tail face
Go out.It is single that each duct son field corresponds to the unilateral exhaust that one group of multiple gas vent by identical quantity and same distribution form forms
Member.The quantity for the gas vent that unilateral exhaust unit includes and the aperture of gas vent depend on unilateral leaving area, unilateral side exhaust
Area is the sum of the leaving area of all gas vents in unilateral exhaust unit.Unilateral leaving area is too small, easy tos produce and is jammed,
Unilateral leaving area is excessive, can reduce torque adjusting effect.Unilateral leaving area is usually the air inlet face that all air admission holes are formed
Long-pending 0.8~1.2 times, each bore dia that is vented are not less than 0.5mm.In order to avoid flowing is jammed, the common segment and duct of duct
Each son field smallest cross-section area A* should meet area-Mach number relational expression, as follows：
Wherein Ma is air admission hole entrance Mach number, A0For the total air inlet area of all air admission hole entrances, γ is specific heat ratio.
Further, in order to control pitch channel and jaw channel, the son field number of the duct in the present invention is 4,
It is laid out using "+" word, each son field specification is identical and full symmetric, wherein two son fields control pitch channel, left and right up and down
Two son fields control jaw channel；Meanwhile the lateral surface of aircraft tail portion be provided with four groups respectively with 4 duct son fields one
One corresponding unilateral exhaust unit, four groups of unilateral side exhaust units are separately positioned on the upper side of aircraft tail portion, downside, left side
Face and right side, exhaust number of perforations, vent shape size and arrangement mode in four groups of unilateral side exhaust units it is identical and
Four groups of unilateral side exhaust units are full symmetric.
The advantageous effects of the present invention：
1) by the head trepanning of aircraft, the high pressure gas after Vehicle nose's bowshock is introduced into inner duct,
It is sprayed in aircraft tail portion using the high pressure gas of inner duct as the air source of porous jet flow, avoids carrying around extra injection work
Matter.
2) virtual oblique shock wave is formed in aircraft tail portion using porous array Jet enterference, makes aircraft fuselage surface pressure
Change, realize the purpose of Torque-adjusting, avoids the pneumatic heat problem brought using movable pneumatic control component.
Description of the drawings
The plane of symmetry cross section view of the porous flow control apparatus of Fig. 1 present invention
The front view and side view of the porous flow control apparatus of Fig. 2 present invention.
The 3-D view of the porous flow control apparatus of Fig. 3 present invention.
The cross section view of the porous flow control apparatus of Fig. 4 present invention
Fig. 5 axial direction force coefficient result of calculations compare
Fig. 6 normal force coefficient result of calculations compare
Fig. 7 resistance coefficient result of calculations compare
Fig. 8 lift coefficient result of calculations compare
Fig. 9 lift resistance ratio result of calculations compare
Figure 10 pitching moment coefficient result of calculations compare
The result of calculation comparison of the focal positions Figure 11
0 degree of state plane of symmetry Mach number cloud atlas of gas vent Model angle of attack under Figure 12
The symmetrical surface pressure cloud atlas of 0 degree of state of gas vent Model angle of attack under Figure 13
The neighbouring Mach number cloud atlas of 0 degree of state air admission hole of gas vent Model angle of attack and streamline distribution under Figure 14
The neighbouring Mach number cloud atlas of 0 degree of state gas vent of gas vent Model angle of attack and streamline distribution under Figure 15
10 degree of state plane of symmetry Mach number cloud atlas of gas vent Model angle of attack under Figure 16
The symmetrical surface pressure cloud atlas of 10 degree of states of gas vent Model angle of attack under Figure 17
The neighbouring Mach number cloud atlas of 10 degree of state air admission holes of gas vent Model angle of attack and streamline distribution under Figure 18
The neighbouring Mach number cloud atlas of 10 degree of state gas vents of gas vent Model angle of attack and streamline distribution under Figure 19
Specific implementation mode
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to embodiment party of the present invention
Formula is described in further detail.
A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle, including it is opened in aircraft head
The air admission hole in portion and the gas vent for being opened in aircraft tail portion, by being arranged in aircraft interior between air admission hole and gas vent
Duct carry out unicom.
Its shape of the invention is as shown in Figure 1 to 4, is mainly made of air admission hole 1, duct 2 and gas vent 3.Air admission hole 1 with
Duct 2 is connected to, and duct 2 is connected to gas vent 3.Duct 2 be hollow structure, duct 2 be aircraft interior aircraft inner cone 5 with
The cavity formed between aircraft skin 6.The partition board 4 of polylith longitudinal direction is provided between aircraft skin 6 and aircraft inner cone 5,
The effect of partition board 4 is that duct is separated into multiple son fields, and polylith partition board 4 circumferentially uniformly divides around the central axis of duct 2
Cloth.
Air admission hole 1 is opened in the head of aircraft, and shape is generally circular, and quantity is one or more, and air inlet axially bored line hangs down
Directly in aircraft fuselage surface.If air inlet hole number is 1, the position that opens up of air admission hole is Vehicle nose stationary point position
It sets；If air inlet hole number is multiple, air admission hole distributing position should be along aircraft central axis circumferentially to being uniformly distributed.Air inlet
Hole number, aperture depend on whole air inlet area.Whole air inlet area is about the 5%~10% of aircraft fuselage bottom area,
The too small then torque adjusting effect unobvious of air inlet area, air inlet area is excessive, can reduce fuselage interior dischargeable capacity.Air admission hole
Aperture should be not less than 0.5mm.All air admission holes are connected to inner duct.
Duct 2 is cavity structure, arranges that formula scheme, i.e. duct 2 are arranged close to aircraft outer surface using outside.Duct 2
Designed using two sections, include by air admission hole common segment and be branched off into the son field of each side gas vent.All charge air flows
2 common segment of duct is flowed by air admission hole 1,2 branch of duct is controlled using valve in 2 common segment of duct and son field joint
The open and close of section.In order to avoid flowing is jammed, 2 common segment of duct should meet face with each son field smallest cross-section area A*
Product-Mach number relational expression：
Wherein Ma is entrance Mach number, A0For inlet induction area, γ is specific heat ratio.
In order to control pitch channel and jaw channel, 2 son field number of duct is 4, is laid out using "+" word, each branch
Section specification is identical and full symmetric, wherein two son fields control pitch channel up and down, the son field control yaw of left and right two is logical
Road.
Gas vent 3 is arranged in aircraft fuselage lateral tail, and 3 shape of gas vent is generally circular, and 3 axis of gas vent is vertical
In aircraft fuselage surface.Air-flow is discharged by 2 son field of duct from gas vent 3, and 2 son field of each duct corresponds to identical quantity
With the gas vent 3 of position distribution.3 aperture of unilateral gas vent, quantity depend on unilateral leaving area, and unilateral leaving area is too small then
It easy tos produce and is jammed, unilateral leaving area is excessive, can reduce torque adjusting effect, and unilateral leaving area is usually air inlet area
0.8~1.2 times, each bore dia that is vented is not less than 0.5.Array distribution can be used in unilateral gas vent 3, and unilateral side can be arranged more
Row, each row can arrange multiple gas vents 3.
Under the conditions of hypersonic, due to Vehicle nose's surface pressing highest, then head high pressure gas can pass through air inlet
Hole 1 flows into duct 2, and 2 internal pressure of duct is made to increase.Since afterbody surface pressing is relatively low, then high pressure gas in duct 2
Know from experience and be discharged by afterbody gas vent 3 and form transverse jet, under the influence of jet flow shock wave, high pressure is generated before jet flow
Area generates low-pressure area after jet flow, to change of flight device surface pressure distribution, carries out torque adjusting.
A kind of thinking of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle proposed by the present invention
It is mainly derived from the principle of transverse jet/mainstream interference, changes wall pressure distribution using Jet enterference, but its jet source is simultaneously
It is not from traditional Attitude rocket engine, but the high pressure gas after forward shock.If designed using single spraying hole,
It generates the less efficient of additional control, therefore combines micro- spray Array Design thought in Boundary layer flow, in aircraft machine
Body tail portion forms the multiply air-flow with certain speed, pressure, is interfered each other between per share air-flow, jet flow front interlayer is made to produce
It is estranged from, form virtual " pneumatic slope ", and then the wall pressure distribution of aircraft is adjusted, so realize control force
The purpose of square.By taking pitch channel is adjusted as an example, pitching moment can be adjusted by the upper duct son field of unlatching or lower duct son field,
Simultaneously close off left and right duct son field.When opening upper duct son field, air-flow is discharged through upper duct son field from upper air-vent,
Aircraft is set to generate nose-up pitching moment；When opening lower duct son field, air-flow is discharged through lower duct son field from lower gas vent, makes
Aircraft generates nose-down pitching moment.The implementation method and parts machining of the present invention is all fairly simple, is not present in engineer application
Bigger difficulty.
Porous flowing control design case is used for certain hypersonic aircraft, 89 air inlets are uniformly distributed on its head
Hole, each a diameter of 20mm of air admission hole.Unilateral side is vented 3 row of pore size distribution totally 45 gas vents, each a diameter of 32mm of gas vent.It is logical
Duct is crossed to be connected to air admission hole with gas vent.Numerical simulation under 6 height 25km states of Mach number is carried out using method for numerical simulation
It is special to compared no pore model NH, the aeroperformance of lower exhaust pore model SH_DB and upper air-vent model SH_UB and flow field for research
Sign.It is wherein axial symmetry blunted cone shape without pore model, inlet and outlet hole and duct is not present；Lower exhaust pore model only exists down
Duct son field and downside gas vent, upper air-vent model only exist duct son field and upside gas vent.
Axial force coefficient result of calculation comparison is as shown in figure 5, normal force coefficient result of calculation compares as shown in fig. 6, resistance
Coefficient result of calculation compares as shown in fig. 7, the comparison of lift coefficient result of calculation is as shown in figure 8, lift resistance ratio result of calculation compares such as
Shown in Fig. 9, the comparison of pitching moment coefficient result of calculation is as shown in Figure 10, and result of calculation comparison in focal position is as shown in figure 11.Its
Middle NH is represented without pore model, and SH_DB represents lower exhaust pore model, and SH_UB represents upper air-vent model.
It can be seen that in 0 degree of state of the angle of attack there are when intake and exhaust flowing, aircraft resistance coefficient increase about 6.6%, but produce
Normal force coefficient and pitching moment coefficient increment, lower exhaust pore model produce positive 0.032 lift coefficient and 0.0125
Nose-down pitching moment, upper air-vent model produces 0.032 negative lift coefficient and 0.0125 nose-up pitching moment.In Low Angle Of Attack shape
Under state (- 5~5 degree of degree), there are when intake and exhaust flowing, aircraft focal position is moved after slightly having, and is conducive to the static-stability of aircraft
Design.
It is vented for pore model below, the Field Characteristics under 10 degree of states of 0 degree of the angle of attack and the angle of attack are as shown in Figure 12~19.
From flow field structure, air admission hole, duct and the gas vent of lower exhaust pore model nearby produce complicated Field Characteristics,
Shock wave structure is produced just because of exhaust spraying leading edge and forms virtual " pneumatic slope ", makes effect and the " body of gas vent
Wing flap " is similar, to change the distribution of fuselage surface pressure, realizes the purpose of Torque-adjusting, thus demonstrates the present invention's
Validity.
The explanation of the preferred embodiment of the present invention contained above, this be for the technical characteristic that the present invention will be described in detail, and
Be not intended to invention content being limited in concrete form described in embodiment, according to the present invention content purport carry out other
Modifications and variations are also protected by this patent.The purport of the content of present invention is to be defined by the claims, rather than by embodiment
Specific descriptions are defined.
Claims (10)
1. a kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle, it is characterised in that：Including opening up
Air admission hole in Vehicle nose and the gas vent that is opened on each lateral surface of aircraft tail portion, air admission hole and gas vent
Between by be arranged aircraft interior duct carry out unicom；Duct is hollow structure, the shell and aircraft of aircraft
Cavity between inner cone forms the duct of unicom air admission hole and gas vent, and the duct is designed using two sections, including by air admission hole
The son field of the common segment set out and the gas vent being branched off on each lateral surface of aircraft tail portion.
2. the porous flow control apparatus according to claim 1 applied to hypersonic motor-driven reentry vehicle, special
Sign is that the air admission hole is 1 round air admission hole, which is opened in Vehicle nose stationary point position, and the air admission hole
Axis where the air admission hole aircraft fuselage surface；
Alternatively, the air admission hole is multiple round air admission holes, multiple air admission holes are opened in Vehicle nose and along aircraft centers
For axis circumferentially to being uniformly distributed, the axis of each air admission hole is each perpendicular to its respectively place aircraft fuselage surface.
3. the porous flow control apparatus according to claim 1 or 2 applied to hypersonic motor-driven reentry vehicle,
It is characterized in that, the whole air inlet area for being opened in all air admission holes formation of Vehicle nose is aircraft fuselage bottom area
5%~10%, single air admission hole aperture is not less than 0.5mm.
4. the porous flow control apparatus according to claim 1 applied to hypersonic motor-driven reentry vehicle, special
Sign is that each lateral surface of aircraft tail portion is provided with multigroup unilateral exhaust unit being made of multiple gas vents, unilateral side row
Gas vent in gas unit is distributed using array.
5. the porous flow control apparatus according to claim 4 applied to hypersonic motor-driven reentry vehicle, special
Sign is that unilateral exhaust unit includes multiple rows of gas vent, and gas vent is circle, and the axis of each gas vent is perpendicular to each gas vent
Place aircraft fuselage surface.
6. the porous flow control apparatus according to claim 4 or 5 applied to hypersonic motor-driven reentry vehicle,
It is characterized in that, the sum of leaving area of all gas vents is unilateral leaving area in unilateral exhaust unit, and unilateral leaving area is
0.8~1.2 times of the air inlet area that all air admission holes are formed, each bore dia that is vented are not less than 0.5mm.
7. the porous flow control apparatus according to claim 6 applied to hypersonic motor-driven reentry vehicle, special
Sign is that the number of the son field is identical as the unilateral group number of exhaust unit.
8. the porous flow control apparatus according to claim 7 applied to hypersonic motor-driven reentry vehicle, special
Sign is, the smallest cross-section area A of its common segment of duct0The smallest cross-section area A* of its each son field should meet face with duct
Product-Mach number relational expression is as follows：
Wherein Ma is air admission hole entrance Mach number, and γ is specific heat ratio.
9. the porous flow control apparatus according to claim 7 applied to hypersonic motor-driven reentry vehicle, special
Sign is that all air admission holes correspond to the common segment of unicom duct, and the common segment of duct and the joint of each son field are both provided with
Valve, the opening and closing of the son field for controlling each duct；Air-flow enters after the common segment of duct from air admission hole through duct
Each son field from each unilateral exhaust unit discharge on aircraft lateral tail face.
10. the porous flow control apparatus according to claim 9 applied to hypersonic motor-driven reentry vehicle, special
Sign is that the son field number of duct is 4, is laid out using "+" word, and each son field specification is identical and full symmetric, wherein on
Lower two son fields control pitch channel, and the son field of left and right two controls jaw channel；Meanwhile the lateral surface of aircraft tail portion is set
Being equipped with four groups, unilateral exhaust unit, four groups of unilateral side exhaust units are separately positioned on correspondingly with 4 duct son fields respectively
Upper side, downside, left side and the right side of aircraft tail portion, exhaust number of perforations, row in four groups of unilateral side exhaust units
Stomata shape size and arrangement mode is identical and four groups of unilateral side exhaust units are full symmetric.
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| CN201610810260.4A CN106184719B (en) | 2016-09-08 | 2016-09-08 | A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle |
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| CN201610810260.4A CN106184719B (en) | 2016-09-08 | 2016-09-08 | A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle |
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| CN107344613A (en) * | 2017-06-16 | 2017-11-14 | 青岛华创风能有限公司 | A kind of fluid motivational techniques for wing and blade |
| CN107539460B (en) * | 2017-08-30 | 2020-06-19 | 清华大学 | Aircraft deformation nose cone device imitating bee abdomen |
| CN109131950A (en) * | 2018-10-24 | 2019-01-04 | 中国航天空气动力技术研究院 | A kind of body of revolution aircraft based on novel wing flap rudder face |
| CN109579637B (en) * | 2018-12-07 | 2023-04-18 | 中国人民解放军国防科技大学 | Missile attitude control mechanism without control surface |
| CN109581315B (en) * | 2018-12-18 | 2020-10-16 | 中国人民解放军国防科技大学 | Hypersonic aircraft radar stealth performance evaluation method |
| CN110435929B (en) * | 2019-07-23 | 2022-06-17 | 南京航空航天大学 | Active type air charging and exhausting device for aerospace craft |
| CN112550678B (en) * | 2020-12-10 | 2021-10-15 | 西北工业大学 | Supersonic aircraft sonic boom suppression method based on blowing and sucking flow control |
| CN116534246B (en) * | 2023-07-05 | 2023-09-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Flow direction vortex modulation device |
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| US6866233B2 (en) * | 2003-01-03 | 2005-03-15 | Orbital Research Inc. | Reconfigurable porous technology for fluid flow control and method of controlling flow |
| US7207520B2 (en) * | 2005-05-31 | 2007-04-24 | Lockheed Martin Corporation | System, method, and apparatus for designing streamline traced, mixed compression inlets for aircraft engines |
| CN102953826B (en) * | 2012-11-22 | 2013-11-27 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for forebody-inner passage circulation |
| CN104354852B (en) * | 2014-10-20 | 2017-02-22 | 中国科学院力学研究所 | Upper wing adjusting device and high-speed aircraft |
| CN104386237A (en) * | 2014-11-17 | 2015-03-04 | 朱晓义 | High-speed aircraft and cartridge |
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