CN101767648B - Device for eliminating side force of slender body at large incidence angle - Google Patents
Device for eliminating side force of slender body at large incidence angle Download PDFInfo
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- CN101767648B CN101767648B CN201010013713A CN201010013713A CN101767648B CN 101767648 B CN101767648 B CN 101767648B CN 201010013713 A CN201010013713 A CN 201010013713A CN 201010013713 A CN201010013713 A CN 201010013713A CN 101767648 B CN101767648 B CN 101767648B
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- sleeve
- side force
- clamping core
- small rack
- film
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Abstract
The invention discloses a device for eliminating side force for a slender body at a large incidence angle, comprising a film support frame and a retractable mechanism. A cover just above the front part of the head of the flying vehicle is provided with a retractable slit, the front end of the head of the flying vehicle is provided with a small bracket (8) and a large bracket (17). An electric telescopic rod (7) is located between the two brackets; the axis line of the electric telescopic rod (7) overlaps the central connection line of the two brackets. A guide rail (6) is located under the axis line of the flying vehicle and is parallel to the axis line. A connecting tube (18) is sleeved on a sleeve (2) of the film support frame, and is fixedly connected with two connecting sheets at one side of the connecting tube (18) through a connecting plate of a sliding block (12). The invention realizes the unfolding and the folding of a film (5) through the stretching and contracting movement of the electric telescopic rod at the axis line direction of the airplane; under the role of the airflow, the film generates self-excited vibration and non-steady streaming around, realizes the control of the asymmetric vortex, and eliminates the side force; the structure is simple, the performance is reliable, therefore, the invention is suitable for a fighter or a tactical missile and other flying vehicles.
Description
Technical field
The present invention relates to Aeronautics and Astronautics and weapon industry, is a kind of device of eliminating side force of slender body at large incidence angle.
Background technology
When aircraft such as fighter plane or tactical missile flies under big state of angle of attack; Flowing of the leeward district of aircraft is made up of all asymmetric whirlpool of some intensity and position, and the side force that these asymmetric whirlpools produced is that the flight and the control of aircraft has brought a lot of unfavorable factors.How to eliminate these side forces through the asymmetric whirlpool of regulation and control precursor, be the technical barrier that aerodynamics scientist and scientific research institution are making great efforts research always.
In the low incidence scope (0 °≤α＜10 °), the streaming of model for adhering to stable flowing, side force is zero; In medium and small angle-of-attack range (10 °＜α≤20 °), model flows and separates, the symmetrical whirlpool that a pair of rotation direction of rolling in the leeward district of model is opposite, and the locus of vortex does not change in time, and side force is zero; In medium angle-of-attack range (20 °＜α≤30 °), flow and to be stable asymmetric back of the body whirlpool in the leeward district of model and since vortex intensity a little less than, so side force is less; In big angle-of-attack range (30 °＜α≤70 °); Flow and be asymmetric back of the body vortex system in the leeward district of model; The vortex intensity in asymmetric whirlpool strengthens along with the increase of the angle of attack, but because reducing of main whirlpool affected zone makes that the variation tendency of side force in this angle-of-attack range is to increase afterwards earlier to reduce; In very big angle-of-attack range (α＞70 °); Rear portion, the leeward district of model is non-permanent separated flow; On body after the major part, form the non-permanent whirlpool that comes off, and along with the zone in the non-permanent whirlpool that alternately comes off of the increase of the angle of attack is increasing, side force reduces significantly; Until (α=90 °) form karman vortex, the side force aviation value is entirely zero.
The control to the asymmetric whirlpool of the big angle of attack at present mainly contains following several kinds of measures: 1) in the head perforating of model; The mode of blowing through aperture pulsation is controlled side force; Its major defect is that the needed air-blowing quantity size in the asymmetric whirlpool of control is closely related with speed of incoming flow, that is to say that flying speed increases, and air-blowing quantity is also wanted corresponding increase; Therefore required energy also will increase, and the weight cost of additional equipment is higher; 2) the model head is transformed into movable nose cone, left and right sides deflection through nose cone or rotation are to control, and the mechanism of obvious this mode is complicated, and is bigger to the change of model; 3) lay the shimmy mechanism of microvariations at the model head; Realize the forced vibration of shimmy mechanism through motor; Realize control with less consumed energy, see that from the document result effect of this mode is fine, but the shimmy mechanism of its microvariations is still very complicated asymmetric whirlpool; Need the weight cost of power supply and control mechanism also bigger, also be not easy to arrangement sometimes at model head finite space.
Summary of the invention
In order to eliminate the side force that slender body aircraft such as fighter plane or tactical missile produce owing to asymmetric whirlpool under the high-angle-of-attack flight situation; And do not hinder aircraft under zero side force under other angle of attack or little side force state, to fly, the present invention proposes a kind of device of eliminating side force of slender body at large incidence angle.
The present invention includes thin film support frame and jack, the self-excited vibration film is installed in Vehicle nose the place ahead, realize its expansion and withdrawal at the fore and aft motion of axes of aircraft direction through the electric expansion bar.Its concrete scheme is:
Have the folding and unfolding seam on the covering directly over before Vehicle nose, settle small rack and big support in Vehicle nose's front end respectively; The electric expansion bar is between small rack and big support, and the axis of electric expansion bar overlaps with the line of centres of two supports; Guide rail is positioned at aircraft axis below and aircraft parallel axes; The truss of guide rail one end and Vehicle nose is affixed, and the other end is connected with the cradling piece of small rack lower end; Connecting cylinder is between the clamping band and electric expansion bar that are installed on the sleeve; Connecting cylinder is sleeved on the sleeve of thin film support frame, and is connected through the connecting panel of slide block and two connecting straps of connecting cylinder one side.
Described thin film support frame comprises film, supporting spring, diagonal brace reed, film reinforced rib, clamping core, sleeve and clamping band.Clamping core in the thin film support frame is positioned at sleeve, and clamping band is enclosed within on the sleeve, and the crack of clamping core and sleeve is corresponding.The profile of film is a right-angled triangle, and the drift angle of this film equals Vehicle nose's semi-cone angle.A straight flange of film has and the mutual vertical support reed of clamping core, and another straight flange is fixed in the crack of clamping core.One end of supporting spring also embeds the clamping in-core.The surface adhesion of diagonal brace reed is on film, and an end of this diagonal brace reed is bonded on the supporting spring, and the other end is bonded on the clamping core.There is ball the sleeve termination of thin film support frame drift angle end, and the somewhat larger in diameter of this ball is in the external diameter of sleeve; The film reinforced rib that useful elastic is made on the hypotenuse of film.
There is crack on the surface of described clamping core along its axis direction, and this crack terminates in clamping core edge in the center of circle of radially crossing the clamping core of clamping core; Axially terminating in of clamping core apart from clamping core end.
Describedly have crack along its generatrix direction, and the end of this crack terminates in apart from sleeve other end end at sleeve one end; Near the position of supporting spring clamping band is housed in barrel end; Rubber sleeve circle between sleeve and the clamping band.
Described jack comprises small rack and big support, electric expansion bar, guide rail and slide block.Small rack all is positioned on the aircraft axis with big support, and wherein small rack must make thin film support frame take in fully in the head apart from the distance on head top, and the distance between small rack and the big support must satisfy the distance of the electric expansion throw of lever; In the middle of small rack and the big support circular hole is arranged; Small rack is affixed with the head truss of big support and aircraft.One end of electric expansion bar is fixed in the centre hole of big support, and the other end is packed in the centre hole of small rack, and can in the centre hole of small rack, slide.Have chute on the guide rail, slide block is positioned at the chute of guide rail.Slide block is captiveed joint with the folder connecting cylinder through the connecting panel of self.
The electric expansion bar connects with aircraft power supply through cable, connects with aircraft control system through signal wire (SW).
When aircraft was in the flight of low incidence state, the self-excited vibration structure closed at head inside.When aircraft is in the flight of big state of angle of attack, send instruction by chaufeur or internal processes, the elongation of electric expansion bar is pushed into head the place ahead with the self-excited vibration device.Under the effect of air-flow, film produces self-excited vibration, produces time-dependent streaming, and realizes the control to asymmetric whirlpool, eliminates side force.
Self-excited vibration film of the present invention is placed in the thin film support frame, and bracing frame is laid and slender body head the place ahead.When the flying angle of aircraft was positioned in the high-angle-of-attack flight scope, jack was accepted aviator's instruction, ejects thin film support frame, and diaphragm is self-excited vibration in air-flow, produces time-dependent streaming, and realizes the control to asymmetric whirlpool, eliminates side force.When aircraft recovered to fly under the low incidence state, jack was accepted aviator's instruction bracing frame is retracted to slender body precursor inside.
The present invention utilizes the self-excited vibration in air-flow of film, reaches the effect of under big angle of attack situation, eliminating side force, and does not influence the normal flight under zero side force and the small side force situation, is applicable to that cone angle is greater than 42 ° aircraft.Characteristics such as that the present invention has is simple in structure, dependable performance.
Description of drawings
Fig. 1 is the riding position scheme drawing of self-excited vibration device in Vehicle nose the place ahead;
Fig. 2 is the scheme of installation of self-excited vibration device in Vehicle nose;
Fig. 3 is the thin film support frame constructional drawing;
Fig. 4 is the A-A view of thin film support frame;
Fig. 5 is the structural representation of self-excited vibration device;
Fig. 6 is the cooperation scheme drawing of guide rail and bracing frame;
Fig. 7 is the structural representation of support;
Fig. 8 is that the B of supporting structure scheme drawing is to view.Wherein:
1. body 2. aluminium alloy sleeve barrels 3. supporting springs 4. film reinforced ribs 5. films 6. guide rails
7. electric expansion bar 8 small racks 9. clamping cores 10. clamping bands 11. rubbery loops 12. slide blocks
13. seal strip 14. aircraft truss 15. coverings 16. diagonal brace reeds 17. big support 18. connecting cylinders
Specific embodiments
Present embodiment is a kind of mechanical device that can eliminate aircraft at high angle of attack slender body side force, comprises thin film support frame and jack.
Present embodiment is installed in Vehicle nose the place ahead (shown in accompanying drawing 1) with thin film support frame, and realizes its expansion and withdrawal through the electric expansion bar at the fore and aft motion of axes of aircraft direction.
As shown in Figure 3, thin film support frame comprises film 5, supporting spring 3, diagonal brace reed 16, film reinforced rib 4, clamping core 9, sleeve 2 and clamping band 10.Wherein:
Clamping core 9 is circular rod member; Its diameter is 4mm, and there is crack on the surface of clamping core 9 along its generatrix direction, and this crack is in the center of circle of radially crossing clamping core 9 of clamping core 9; Terminate in clamping core 9 edges; Axially terminating in apart from clamping core 9 ends of clamping core 9, in the present embodiment, this crack terminates in apart from 5mm place, clamping core 9 termination at clamping core 9 generatrix directions.Crack length is than the long 1cm of length on film 5 right-angled triangle bases.
The thin walled hollow rod member that sleeve 2 is made for aluminum alloy.The aperture of sleeve 2 endoporus is with clamping core 9 diameters; The length of sleeve 2 is with the length of clamping core 9.Have the crack of an about 1mm of width at sleeve 2 one ends along its generatrix direction, and the end of this crack terminates in apart from sleeve 2 other end ends, in the present embodiment, the end of crack terminates in apart from 5mm place, sleeve 2 other end termination.Near the position of supporting spring 3 clamping band 10 is housed at sleeve 2 ends, to tighten up thin film support frame.Rubber sleeve circle 11 between sleeve 2 and the clamping band 10.
Clamping band 10 is the hollow gyro-rotor, and the housing of this clamping band 10 breaks off along its bus.Two ends at clamping band 10 circumference all has the radially auricle of protrusion; Concentric connecting bore is all arranged on this auricle.The internal diameter of clamping band 10 is with the external diameter of sleeve 2.
Connecting cylinder 18 is two semicircular cylinders.Internal diameter after two semicircular cylinders fasten is with the external diameter of sleeve 2; At the two ends of two semicircular cylinders radially extended connecting strap is arranged respectively; Concentric connecting bore is all arranged on connecting strap.
Clamping core 9 in the thin film support frame is positioned at sleeve 2, and clamping band 10 is enclosed within on the sleeve 2, and the crack of clamping core 9 and sleeve 2 is corresponding.Supporting spring 3 is packed in the crack of clamping core 9 and sleeve 2.
Jack comprises two supports, electric expansion bar 7, guide rail 6 and slide block 12.Two supports are respectively small rack 8 and big support 17.Small rack 8 is " ten " font with big support 17, and at the center of " ten " font circular hole is arranged.Small rack 8 is with 17 two supports 8 of support are along the aircraft axis arranged greatly, and wherein small rack 8 must make thin film support frame take in fully in the head apart from the distance on head top, and the distance between small rack 8 and the big support 17 must satisfy the distance of electric expansion bar 7 strokes.Small rack 8 is that distance between 25cm small rack 8 and the big support 17 also is 25cm apart from the distance on head top in the present embodiment.The length of two supports and highly respectively with the internal diameter of Vehicle nose of living in position.
As shown in Figure 2.Four terminations of two supports are connected in respectively on the truss of aircraft.Between small rack 8 and big support 17, electric expansion bar 7 is installed.The axis of electric expansion bar 7 overlaps with the line of centres of two supports; One end of electric expansion bar 7 is fixed in the centre hole of big support 17, and the other end is packed in the centre hole of small rack 8, and can in the centre hole of small rack 8, slide.
During installation, open the folding and unfolding seam of 2mm on the covering before Vehicle nose directly over the 19cm.Settle small rack 8 and big support 17 (like Fig. 2) at head respectively from top 25cm and 50cm section.Four terminations of two supports and the riveted joint of head truss.Electric expansion bar 7 is installed between small rack 8 and the big support 17, and the fixed end of electric expansion bar 7 is connected through the center of bolt with big support 17, and flexible end then passes through connecting cylinder 18 and is connected with an end of sleeve 2.The truss riveted joint of guide rail 6 one ends and Vehicle nose, the other end then is connected with the cradling piece of small rack 8 lower ends through bolt; Guide rail 6 is parallel with axes of aircraft.As shown in Figure 5, slide block 12 embeds in the chute of guide rail 6, and can slide along guide rail 6; The chute mouth has seal ring 13, in case the lubricating oil in the on-slip groove spills.Clamping band 10 is sleeved on the thin film support frame.Connecting cylinder 18 is sleeved on the sleeve 2 of thin film support frame, and the connecting panel of slide block 12 is clipped between two connecting straps of connecting cylinder 18 1 sides, connects through bolt tightening; Connecting cylinder 18 is between the clamping band 10 and electric expansion bar 7 that are installed on the sleeve 2.
There is ball the sleeve termination of thin film support frame drift angle end, and the somewhat larger in diameter of this ball is in the external diameter of sleeve, and in the time of in bracing frame is taken in head, this ball is still stayed outside the covering, can not stretch out head smoothly to avoid thin film support frame to be stuck in the covering.
Electric expansion bar 7 connects with aircraft power supply through cable, connects with aircraft control system through signal wire (SW).
When aircraft was in the flight of low incidence state, the self-excited vibration structure closed at head inside.When aircraft is in the flight of big state of angle of attack, send instruction by chaufeur or internal processes, the elongation of electric expansion bar is pushed into head the place ahead with the self-excited vibration device.Under the effect of air-flow, film produces self-excited vibration, produces time-dependent streaming, and realizes the control to asymmetric whirlpool, eliminates side force.
The manufacturing process of present embodiment thin film support frame is:
1. according to the semi-cone angle of Vehicle nose, use the polyethylene foil clip of thick about 0.1mm to go out the right-angled triangle of drift angle, its hypotenuse is about is to launch 20cm, pave as Vehicle nose's semi-cone angle.
2. clip length is about the elastic of 22cm, and the hypotenuse of right-angled triangle film is rolled 2 circles, and in the process of volume, coats epoxy resin glue, forms film reinforced rib 4.
3. supporting spring 3 is the copper sheet of wide 6mm, thick 0.2mm.Supporting spring 3 is bonded on the flash of triangle film 5; One end of elastic is fixed on the upper end of supporting spring 3, and the other end places in the crack of clamping core 9.Diagonal brace reed 16 usefulness copper sheets are processed, and it is wide to be 3mm, and thick is 0.1mm, and long is 5cm.One end of diagonal brace reed 16 be fixed on supporting spring 3 apart from the base about 2/5 place, the other end then is fixed on the triangle base, cements with glue, obtains the vibration of thin membrane sheet.
4. choosing diameter is the plastics round bar of 3.5mm, and plastics round bar one end is rived downwards with cutter along diameter, stops in the place of about 5mm apart from the bottom, forms clamping core 9.The base of vibration of thin membrane sheet is embedded in the crack of clamping core 9 and tightens, and, formed thin film support frame with the epoxy resin glue bonding.
5. according to the size of clamping core 9, choose aluminum alloy drum 2, its length is with the length of clamping core, and its internal diameter is with the clamping core diameter.Clamping core 9 one ends are left the finedraw of the wide 1.6mm of being about along generatrix direction, stop, forming sleeve 2 in place apart from the about 5mm in bottom.Thin film support frame is embedded in the sleeve 2 along the clamping core, and terminal at reed with clamping band 10 bandings.
Claims (9)
1. a device of eliminating side force of slender body at large incidence angle is characterized in that, the device of described elimination side force of slender body at large incidence angle comprises thin film support frame and jack; Have the folding and unfolding seam on the covering directly over before Vehicle nose, settle small rack (8) and big support (17) in Vehicle nose's front end respectively; Electric expansion bar (7) is positioned between small rack (8) and the big support (17), and the axis of electric expansion bar (7) overlaps with the line of centres of two supports; Guide rail (6) be positioned at aircraft axis below and with the aircraft parallel axes; The truss of guide rail (6) one ends and Vehicle nose is affixed, and the other end is connected with the cradling piece of small rack (8) lower end; Connecting cylinder (18) is sleeved on the sleeve (2) of thin film support frame, and is connected through the connecting panel of slide block (12) and two connecting straps of connecting cylinder (18) one sides.
2. a kind of according to claim 1 device of eliminating side force of slender body at large incidence angle is characterized in that, thin film support frame comprises film (5), supporting spring (3), diagonal brace reed (16), film reinforced rib (4), clamping core (9), sleeve (2) and clamping band (10); Clamping core (9) in the thin film support frame is positioned at sleeve (2), and clamping band (10) is enclosed within on the sleeve (2), and the crack of clamping core (9) and sleeve (2) is corresponding; The profile of film (5) is a right-angled triangle, and the drift angle of this film (5) equals Vehicle nose's semi-cone angle; A straight flange of film (5) has and the mutual vertical support reed (3) of clamping core (9); Another straight flange is fixed in the crack of clamping core (9); One end of supporting spring (3) also embeds in the clamping core (9); The surface adhesion of diagonal brace reed (16) is on film, and an end of this diagonal brace reed (16) is bonded on the supporting spring (3), and the other end is bonded on the clamping core (9).
3. like the said a kind of device of eliminating side force of slender body at large incidence angle of claim 2, it is characterized in that there is ball the sleeve termination of thin film support frame drift angle end, the somewhat larger in diameter of this ball is in the external diameter of sleeve; The film reinforced rib (4) that useful elastic is made on the hypotenuse of film (5).
4. like the said a kind of device of eliminating side force of slender body at large incidence angle of claim 2; It is characterized in that; There is crack on the surface of clamping core (9) along its axis direction, and this crack terminates in clamping core (9) edge in the center of circle of radially crossing clamping core (9) of clamping core (9); Axially terminate in clamping core (9) end at clamping core (9).
5. like the said a kind of device of eliminating side force of slender body at large incidence angle of claim 2, it is characterized in that, have crack along its generatrix direction, and the end of this crack terminates in sleeve (2) other end end at sleeve (2) one ends; At sleeve (2) one ends clamping band (10) is housed; Rubber sleeve circle (11) between sleeve (2) and the clamping band (10).
6. a kind of according to claim 1 device of eliminating side force of slender body at large incidence angle is characterized in that, jack comprises small rack (8) and big support (17), electric expansion bar (7), guide rail (6) and slide block (12); Small rack (8) and big support (17) all are positioned on the aircraft axis; Wherein small rack (8) must make thin film support frame take in fully in the head apart from the distance on head top, and the distance between small rack (8) and the big support (17) must satisfy the distance of electric expansion bar (7) stroke; One end of electric expansion bar (7) is fixed in the centre hole of big support (17), and the other end is packed in small rack (8) centre hole, and can in the centre hole of small rack (8), slide; Guide rail has chute on (6), and slide block (12) is positioned at the chute of guide rail (6); Slide block (12) is captiveed joint with folder connecting cylinder (18) through the connecting panel of self.
7. like the said a kind of device of eliminating side force of slender body at large incidence angle of claim 6, it is characterized in that between the connecting panel of slide block (12) and connecting cylinder (18), seal strip (13) being arranged.
8. a kind of according to claim 1 device of eliminating side force of slender body at large incidence angle is characterized in that, there is mounting hole at small rack (8) and big support (17) center; Small rack (8) and big support (17) are affixed with the head truss of aircraft.
9. a kind of according to claim 1 device of eliminating side force of slender body at large incidence angle is characterized in that, electric expansion bar (7) connects with aircraft power supply through cable, connects with aircraft control system through signal wire (SW).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010013713A CN101767648B (en) | 2010-01-14 | 2010-01-14 | Device for eliminating side force of slender body at large incidence angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010013713A CN101767648B (en) | 2010-01-14 | 2010-01-14 | Device for eliminating side force of slender body at large incidence angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101767648A CN101767648A (en) | 2010-07-07 |
| CN101767648B true CN101767648B (en) | 2012-10-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010013713A Expired - Fee Related CN101767648B (en) | 2010-01-14 | 2010-01-14 | Device for eliminating side force of slender body at large incidence angle |
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| Country | Link |
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| CN (1) | CN101767648B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103407570A (en) * | 2013-07-12 | 2013-11-27 | 西北工业大学 | Eddy current generating device for controlling lateral force of large-incidence-angle slender body |
| CN111452954A (en) * | 2020-04-20 | 2020-07-28 | 中国民用航空飞行学院 | Broken vortex structure of wing, wing and aircraft |
-
2010
- 2010-01-14 CN CN201010013713A patent/CN101767648B/en not_active Expired - Fee Related
Non-Patent Citations (3)
| Title |
|---|
| 于欣芝等.控制大迎角非对称力的头部旋转法.《航空学报》.1986,第7卷(第5期),494-498. * |
| 曾友兵等.头部鼓包对不同截面机身侧力影响研究.《航空学报》.2007,第28卷(第4期),833-838. * |
| 蔡晋生等.几何微扰动对脱体涡非对称性影响的数值分析.《空气动力学学报》.1997,第15卷(第2期),212-215. * |
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