CN107421402B - A kind of variable missile wing layout for navaho - Google Patents
A kind of variable missile wing layout for navaho Download PDFInfo
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- CN107421402B CN107421402B CN201710604390.7A CN201710604390A CN107421402B CN 107421402 B CN107421402 B CN 107421402B CN 201710604390 A CN201710604390 A CN 201710604390A CN 107421402 B CN107421402 B CN 107421402B
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- wing
- missile
- missile wing
- bomb body
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
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- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
A kind of variable missile wing layout for navaho, each missile wing are made of the upper layer wing and lower layer's wing.The upper layer wing is inverted, and keeps the upper layer wing chord corresponding to the apex angle at center with lower layer's wing chord to the apex angle at center.The upper layer wing and lower layer's wing have independent driving mechanism.Secondary gear reducer in each driving mechanism is connected with 4 transmission mechanisms being mounted in bomb body respectively.Each driving motor is all made of either-rotation motor.Using technical solution of the present invention, guided missile can be distributed by changing the missile wing of itself, in missile flight overall process, including ramp-up period, cruising phase and underriding stage, be able to maintain lower drag due to shock wave.
Description
Technical field
The present invention relates to Aeronautics and Astronautics technical field, specifically a kind of variable missile wing cloth for navaho
Office.
Background technique
The advantages such as navaho, accuracy at target high, far firing range, maneuverability strong with its penetration ability, at
To implement the developing direction that each military power of main tool and the world of precision strike pays close attention to, pole to enemy's depth grand strategy target
It may play the role of " trump card " in following high-tech war.
Resistance especially drag due to shock wave has important influence to navaho.For example, cruise missile is most of
Time all can be in the case where designing Mach number with supersonic flight under cruising condition, and the time shared by take-off climb and underriding stage is minimum.
In cruising phase, drag due to shock wave accounts for drag overall greatly.Therefore, reduce drag due to shock wave, can save motor power and
" faster, the higher, farther " flight of navaho may be implemented.
Nineteen thirty-five in the 5th aerodynamics world conference that Rome is held, German aerodynamics scientist Busemann
It is proposed the concept of double-vane wave absorption, he is separated traditional diamond wing by string, and antisymmetry is placed, and forms double-vane.Pass through double-vane
Between shock wave and dilatational wave interfere with each other, in the case where designing Mach number, drag due to shock wave is almost nil.But Busemann double-vane exists
During acceleration, deceleration, it may appear that serious flowing choking phenomenon, drag due to shock wave increased dramatically.
Summary of the invention
For the technical problem that Busemann double-vane drag due to shock wave increased dramatically under the supersonic condition of solution, the present invention is mentioned
A kind of variable missile wing layout for navaho is gone out.
The present invention includes bomb body, the missile wing for being located at bomb body two sides, driving mechanism and transmission mechanism.
It is characterized in that, each missile wing is made of the upper layer wing and lower layer's wing.The upper layer wing is inverted, and the upper layer wing chord is made
Apex angle to center is corresponding with the apex angle at lower layer's wing chord to center.
Described two lower layer's wings are separately mounted to the two sides of bomb body, and make at the vertex of a triangle of lower layer's wing and bomb body
The missile wing chord length that vertical range between bus is 0.15 times；The upper layer wing is separately mounted to the two sides of bomb body, and makes on this
The missile wing chord length that vertical range at the vertex of a triangle of the layer wing between bomb body bus is 0.15 times.The driving mechanism has
4, each missile wing has independent driving mechanism.
Each driving mechanism respectively includes a driving motor and a secondary gear reducer.Each driving motor is equal
Using either-rotation motor.
Secondary gear reducer in each driving mechanism is connected with 4 transmission mechanisms being mounted in bomb body respectively.
Control the deflection angle of each missile wing respectively by each transmission mechanism.
The double-vane is will to open up to cut open between rear along tangential level for the wing of diamond shape along the leading edge of the wing to cross section
Point, obtain two missile wings opened up to cross section for triangle.Obtain two are opened up to the missile wing that cross section is triangle and is distinguished
As the upper layer wing and lower layer's wing.
Each missile wing chord length is 0.15 times of bomb body length, and each missile wing length is 0.075 times of bomb body length, each missile wing
Maximum gauge be 0.05 times of missile wing length.Each missile wing is mounted at the bomb body length of 0.2 times of tail portion of missile wing centre distance bomb body,
Established angle is 3 °.
4 transmission mechanisms are made of motor connection lever and missile wing connecting rod respectively, in which: the one of each motor connection lever
End respectively with the output shaft of each driving motor by being connected by shaft coupling and driving mechanism, the other end respectively with each missile wing
Connecting rod is connected；The other end of each missile wing connecting rod is connected with the threaded hole of missile wing wing root side surface respectively.Each electricity
The axis of machine connecting rod is parallel to the axis of the bomb body；Axis of the axis of each missile wing connecting rod perpendicular to each motor connection lever
Line.
The transmission ratio of institute's secondary gear reducer is 40, the first straight spur gear and the second straight spur gear therein
Engagement.Second straight spur gear is coaxial with third straight spur gear.Third straight spur gear and the 4th straight tooth column tooth
Wheel engagement.Transmission mechanism is connected by shaft coupling with the 4th straight spur gear.
The length of motor connection lever is 0.3 times of bomb body diameter in each transmission mechanism；Missile wing in each transmission mechanism
The length of connecting rod is also 0.3 times of bomb body diameter.
Using technical solution of the present invention, guided missile can be distributed by changing the missile wing of itself, in missile flight overall process,
It including ramp-up period, cruising phase and dives the stage, is able to maintain lower drag due to shock wave.
The Busemann twin designs thought that the present invention uses obtains two delta wings by the diamond shape wing along string subdivision,
Two delta wings are staggered relatively, using reasonable parameter designing, so that the shock wave that 2 triangular element leading edges generate is lucky
It beats and stops at aerofoil profile maximum gauge, the dilatational wave at maximum gauge gets to triangle rear staggered relatively just again.In this way
By the air-flow between two triangular elements, by shock wave compression twice and dilatational wave expansion twice, theoretically in a certain horse
It is conspicuous it is several under, the windward side of dual wing configuration and leeward surface pressure are almost equal, and wave resistance is close to zero.This state is known as Busemann
Dual wing configuration design point, corresponding Mach number are known as designing Mach number.
The present invention carries out parameter designing according to Busemann twin designs thought.2 delta wings of double-vane meet first
Central symmetry.In this way, given relative thickness, that is, can determine triangular element etc. angle corresponding to waist edges.According to incoming flow horse
Conspicuous number, determines oblique shock angle:
Wherein, ξ is angle corresponding to the waist edges such as triangular element, and β is oblique shock angle, M1For free stream Mach number, γ is
Specific heats of gases ratio.
Compared with prior art, the present invention has following technical effect that
The present invention is using Fluid Mechanics Computation technology (CFD) numerical simulation flight condition of guided missile.Governing equation is Europe
Draw equation.
1, assumed shown in simulation drawing 2 using pseudo steady, the guided missile accelerator that missile wing does not deflect.Fig. 6 is the guided missile
When under cruising condition, the pressure cloud atlas of missile wing edge.Corresponding resistance coefficient is 0.00354 at this time.It can be seen by Fig. 6
Out, double-vane is far from reaching theoretical design point at this time.There is one of normal shock wave in double-vane inlet, High Voltage area is always
Double-vane wing tip attachment is extended to, this can generate biggish resistance.
2, assume to simulate guided missile accelerator shown in FIG. 1 using pseudo steady.When guided missile accelerates to be up to cruising condition
When, missile wing rotates in a circumferential direction along bomb body to as shown in Figure 2.Fig. 7 is the pressure cloud atlas at the Missile Body nose of wing at this time.The state pair
The resistance coefficient answered is 0.00273.As seen from Figure 7, the twice oblique shock wave that double-vane is located windward is got at wing tip, then leeward
Place generates dilatational wave, and double-vane state and theoretical design point are very close at this time, therefore the resistance generated is lower.
Detailed description of the invention
Fig. 1 is in the present invention in take-off climb or the guided missile schematic diagram in stage of diving；
Fig. 2 is the guided missile schematic diagram in the present invention in cruising phase.
Fig. 3 is transmission mechanism and driving mechanism structure schematic diagram in the present invention.
Fig. 4 is bomb body in the present invention, missile wing, transmission mechanism and driving mechanism relative position schematic diagram, wherein 4a is to overlook
Figure, 4b is main view, and 4c is the right view of 4b.
Fig. 5 is power system principle figure in the present invention.
Fig. 6 is not use pressure cloud atlas of the guided missile of variable layout under cruising condition in the present invention.
Fig. 7 is the pressure cloud atlas of the bullet led in the present invention using variable layout under cruising condition.
In figure: 1. bomb bodys；2. the upper layer wing；3. lower layer's wing；4. motor connection lever；5. transmission mechanism；6. driving mechanism；7. driving
Motor；8. shaft coupling；9. the first straight spur gear；10. the second straight spur gear；11. third straight spur gear；12.
4th straight spur gear；13. missile wing connecting rod.
Specific embodiment
Present embodiment discloses a kind of variable missile wing of suitable navaho layouts, comprising bomb body 1, are located at
Missile wing, driving mechanism 6 and the transmission mechanism 5 of bomb body two sides.The missile wing is made of the upper layer wing 2 and lower layer's wing 3.Each bullet
The wing uses Busemann double-vane, i.e., cuts open exhibition along tangential level between rear along the leading edge of the wing to the wing that cross section is diamond shape
Point, obtain two missile wings opened up to cross section for triangle.It is opened up using two obtained to cross section and is distinguished as the missile wing of triangle
As the upper layer wing 2 and lower layer's wing 3.The upper layer wing 2 is inverted, and makes the upper layer wing chord to the apex angle and lower layer's wing chord at center to center
Apex angle it is corresponding.
Each missile wing chord length is 0.15 times of bomb body length, and each missile wing length is 0.075 times of bomb body length, each missile wing
Maximum gauge be 0.05 times of missile wing length.Each missile wing is mounted at the bomb body length of 0.2 times of tail portion of missile wing centre distance bomb body,
Established angle is 3 °.
The tangential symmetrical centre of each missile wing wing root side surface has the threaded hole for connecting with transmission mechanism.
Described two lower layer's wings 2 are separately mounted to the two sides of bomb body, and make at the vertex of a triangle of lower layer's wing and bullet
The missile wing chord length that vertical range between body bus is 0.15 times；
The upper layer wing 3 is separately mounted to the two sides of bomb body, and makes female with bomb body at the vertex of a triangle of the upper layer wing
The missile wing chord length that vertical range between line is 0.15 times.
The driving mechanism has 4, and each missile wing has independent driving mechanism.Each driving mechanism includes a driving
Motor, two shaft couplings and four straight spur gears.Each driving motor is all made of either-rotation motor, is installed in bomb body
It is interior.
The output shaft of each driving motor 7 is connected by shaft coupling 8 with the first straight spur gear 9.First straight-tooth circle
Stud wheel 9 is engaged with the second straight spur gear 10.Second straight spur gear 10 is coaxial with third straight spur gear 11.The
Three straight spur gears 11 are engaged with the 4th straight spur gear 12.Transmission mechanism 5 passes through shaft coupling and the 4th straight tooth column tooth
Wheel 12 is connected.First straight spur gear 9, the second straight spur gear 10, third straight spur gear 11 and the 4th straight-tooth circle
Stud wheel 12 collectively forms the secondary gear reducer that transmission ratio is 40.
The transmission mechanism 5 has 4, is respectively used to control the deflection angle of each missile wing.4 transmission mechanisms
It is installed in bomb body.4 transmission mechanisms are made of motor connection lever 4 and missile wing connecting rod respectively, in which: each motor
One end of connecting rod by shaft coupling and driving mechanism respectively with the output shaft of each driving motor by being connected, other end difference
It is connected with each missile wing connecting rod；The other end of each missile wing connecting rod is connected with the threaded hole of missile wing wing root side surface respectively.
The axis of each motor connection lever is parallel to the axis of the bomb body；The axis of each missile wing connecting rod is perpendicular to each motor
The axis of connecting rod.Missile wing can rotate under the drive of transmission mechanism along bomb body.
The length of motor connection lever is 0.3 times of bomb body diameter in each transmission mechanism；Missile wing in each transmission mechanism
The length of connecting rod is also 0.3 times of bomb body diameter.
When guided missile is before take-off climb, motor driven rod piece rotation, missile wing is deflected around bomb body, and missile wing layout is as shown in Figure 1.
Later, guided missile enters climb mode after rocket booster accelerates.During climbing, can according to the flight demand of guided missile,
The position of appropriate adjustment missile wing.
When guided missile initially enters cruising condition, motor driven rod piece rotation, missile wing around bomb body deflect, bomb body two sides it is upper
Layer the wing 2 start it is lower partially, lower layer's wing 3 start it is upper partially.Under cruising condition, guided missile is always maintained at 2 positions of diagram, until exiting cruise
State.
When guided missile initially enters the underriding stage, motor-driven rotatable shaft rotation, the bomb body two sides upper layer wing 2 start it is upper partially, under
The layer wing 3 starts lower inclined.It, can be according to the flight demand of guided missile, the position of appropriate adjustment missile wing in process of subduction.
Claims (5)
1. a kind of variable missile wing for navaho is laid out, comprising bomb body, the missile wing that is located at bomb body two sides, drive
Motivation structure and transmission mechanism；
It is characterized in that, each missile wing is made of the upper layer wing and lower layer's wing；The upper layer wing is inverted, and makes the upper layer wing chord in
The apex angle of the heart is corresponding with the apex angle at lower layer's wing chord to center；
The Liang Ge lower layer wing is separately mounted to the two sides of bomb body, and makes at the vertex of a triangle of lower layer's wing between bomb body bus
Vertical range be 0.15 times of missile wing chord length；The upper layer wing is separately mounted to the two sides of bomb body, and makes the three of the upper layer wing
The missile wing chord length that vertical range between angular apex and bomb body bus is 0.15 times；The driving mechanism has 4, each
Missile wing has independent driving mechanism；Secondary gear reducer in each driving mechanism respectively be mounted in bomb body 4
A transmission mechanism is connected；Control the deflection angle of each missile wing respectively by each transmission mechanism；
Double-vane be will open up be to cross section diamond shape the wing along the wing leading edge to, along tangential horizonally split, obtaining two between rear
Open up the missile wing to cross section for triangle；Obtain two are opened up to the missile wing that cross section is triangle as the upper layer wing and
Lower layer's wing；
4 transmission mechanisms are made of motor connection lever and missile wing connecting rod respectively, in which: one end of each motor connection lever point
It is not connected with the output shaft of each driving motor by shaft coupling and driving mechanism, the other end is connected with each missile wing connecting rod respectively；It should
The other end of each missile wing connecting rod is connected with the threaded hole of missile wing wing root side surface respectively；The axis of each motor connection lever is flat
Row is in the axis of the bomb body；Axis of the axis of each missile wing connecting rod perpendicular to each motor connection lever.
2. being laid out as described in claim 1 for the variable missile wing of navaho, which is characterized in that each missile wing string
0.15 times of a length of bomb body length, each missile wing length are 0.075 times of bomb body length, and the maximum gauge of each missile wing is missile wing length
0.05 times；Each missile wing is mounted at the bomb body length of 0.2 times of tail portion of missile wing centre distance bomb body, and established angle is 3 °.
3. being laid out as described in claim 1 for the variable missile wing of navaho, which is characterized in that institute's secondary gear subtracts
The transmission ratio of fast device is 40, and the first straight spur gear therein is engaged with the second straight spur gear；Second straight tooth column tooth
It takes turns coaxial with third straight spur gear；Third straight spur gear is engaged with the 4th straight spur gear；Transmission mechanism passes through
Shaft coupling is connected with the 4th straight spur gear.
4. being laid out as claimed in claim 2 for the variable missile wing of navaho, which is characterized in that each driver
The length of motor connection lever is 0.3 times of bomb body diameter in structure；The length of missile wing connecting rod is also 0.3 times in each transmission mechanism
Bomb body diameter.
5. being laid out as claimed in claim 2 for the variable missile wing of navaho, which is characterized in that each driving machine
Structure respectively includes a driving motor and a secondary gear reducer；Each driving motor is all made of either-rotation motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710604390.7A CN107421402B (en) | 2017-07-24 | 2017-07-24 | A kind of variable missile wing layout for navaho |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710604390.7A CN107421402B (en) | 2017-07-24 | 2017-07-24 | A kind of variable missile wing layout for navaho |
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| Publication Number | Publication Date |
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| CN107421402A CN107421402A (en) | 2017-12-01 |
| CN107421402B true CN107421402B (en) | 2019-09-24 |
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| CN201710604390.7A Active CN107421402B (en) | 2017-07-24 | 2017-07-24 | A kind of variable missile wing layout for navaho |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110514072B (en) * | 2019-08-29 | 2022-02-01 | 中国航天空气动力技术研究院 | Combined speed reduction device and method for ensuring safe water entry of missile crossing water-air medium |
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| CN102730181A (en) * | 2012-05-11 | 2012-10-17 | 西北工业大学 | Aerobat aerodynamic configuration adopting mixing wing body |
| CN103115532A (en) * | 2013-03-05 | 2013-05-22 | 西北工业大学 | Supersonic missile anti-drag wings |
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
| CN204937478U (en) * | 2015-08-13 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Supersonic Cruise Aircraft with scalable canard |
-
2017
- 2017-07-24 CN CN201710604390.7A patent/CN107421402B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730181A (en) * | 2012-05-11 | 2012-10-17 | 西北工业大学 | Aerobat aerodynamic configuration adopting mixing wing body |
| CN103115532A (en) * | 2013-03-05 | 2013-05-22 | 西北工业大学 | Supersonic missile anti-drag wings |
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
| CN204937478U (en) * | 2015-08-13 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Supersonic Cruise Aircraft with scalable canard |
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| CN107421402A (en) | 2017-12-01 |
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