CN110395389A - A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft - Google Patents
A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft Download PDFInfo
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- CN110395389A CN110395389A CN201910578024.8A CN201910578024A CN110395389A CN 110395389 A CN110395389 A CN 110395389A CN 201910578024 A CN201910578024 A CN 201910578024A CN 110395389 A CN110395389 A CN 110395389A
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- tail
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft, includes wing (1), fuselage (2), V tail (3), V tail rear rudder (4), trailing edge rudder (5) and abdomeinal fin (6) using the symmetrical high lift-drag ratio aerodynamic arrangement in the face of the design.Wing (1) is symmetrically mounted below fuselage (2), and V tail (3) is symmetrically mounted on fuselage (2) rear upper, and abdomeinal fin (6) is mounted on fuselage (2) bottom rear；Wing (1) rear installs trailing edge rudder (5) respectively；V tail (3) rear installs V tail rear rudder (4) respectively；Trailing edge rudder (5) and V tail rear rudder (4) are the air-operated control rudder face of aircraft.Existing aerodynamic arrangement can effectively be eliminated under the big angle of attack due to roll guidance coupling effect bring medio-lateral instability, so as to improve lateral closed loop stability horizontal under the big angle of attack using this pneumatic design.
Description
Technical field
The present invention relates to a kind of hypersonic aircraft aerodynamic arrangements, can be suitable for hypersonic flight.
Background technique
Fig. 1 is the schematic three dimensional views of existing hypersonic aircraft aerodynamic arrangement.The allusion quotation represented is configured as with Waverider
The symmetrical aircraft layout in the hypersonic high lift-drag ratio face of type mainly changes directional velocity by the variation in lift direction, therefore vertical
Its flying quality longitudinally and laterally is determined to the ability for becoming the angle of attack and laterally tilting, this just needs to set manipulation layout
Meter makes flying instrument for the maneuvering capability of big range of angles of attack and quick rolling performance.HIFiRE 4 is as Waverider gas for the first time
The hypersonic flight test of dynamic shape, carries out in terms of the manipulation layout designs and flight stability control of high lift-drag ratio configuration
The research of exploration.4 aircraft of HIFiRE uses Waverider layout designs, and aircraft includes the truncated rider with side plate
The protrusion of body wing, wing top is fuselage, and side plate is extended downwardly in wing outer.The executing agency of HIFiRE 4 includes
RCS and pneumatic rudder, wherein RCS is only used in high-altitude of the height greater than 60km, uses pneumatic rudder when height reduces when dynamic pressure increases
Carry out gesture stability.Pneumatic rudder only includes two panels elevon, and it is rear rudder form that with bottom surface syntype and configuration is in tail portion.
The directionless rudder of HIFiRE 4, to provide enough shipping-direction stabilities, HIFiRE 4 devises dorsal fin and side baffle.But
The controllable maneuvering flight test of HIFiRE4 aircraft does not succeed.
Before 4 flight test of HIFiRE, class Waverider aircraft HTV-2 carried out twice 2010 and 2011
Flight test plans the speed gliding flight in endoatmosphere with highest Mach 20, but ends in failure.Failure for the first time
It is expected the reason is that yaw exceeds, and along with the rolling for exceeding controlled range.Second of flight test reduces flying drilling angle, In
It has flown under stable pneumatic control 3 minutes, but out of touch with ground again when attempting pull-up, the reason is that surface layer solar heat protection material
Material, which is disintegrated, to be destroyed aerodynamic configuration and causes violent rolling and out of control.
The air-operated control layout of HTV-2 uses Flap rudder and designs, and back body arranged beneath has 2 wing flap (body
Flap), there is RCS jet apparatus at 4 in tail portion.The complex controll side that HTV-2 is manipulated using base jet (RCS) and pneumatic rudder face
Formula.Pneumatic control is to be located at the symmetrical two panels wing flap in rear body bottom, and capable manipulation can only be rotated by positively biased, identical
Positive deflection angle carries out pitch control, and different positive deflection differences moves angle and then carries out horizontal lateral manipulation.
Horizontal lateral system is likely under the big angle of attack by first ride test it can be seen from the flight test result of HTV-2
Caused by unstability under aileron control, second of flight test reduces flying drilling angle and is improved system, but lift is also with attacking
Angle reduces and reduces, so that flying height reduces, the problem for bringing thermal environment more harsh causes second of flight test to be lost
It loses.
From the point of view of the design and flight test of comprehensive HIFiRE 4 and HTV-2, Waverider and class Waverider high lift-drag ratio are pneumatic
The design of manipulation characteristic and flight stability control problem of layout still there is no adequate solution, horizontal side under the especially big angle of attack
To closed loop stability it is most important for Waverider and class Waverider aircraft.
Summary of the invention
The technical problems to be solved by the present invention are: overcoming the deficiencies of the prior art and provide, a kind of improvement is hypersonic to fly
The aerodynamic arrangement of the horizontal side-coupled characteristic of row device can significantly improve the symmetrical high lift-drag ratio layout in hypersonic aircraft face and attack greatly
Horizontal lateral closed loop stability under angle.
The technical scheme adopted by the invention is that: a kind of pneumatic cloth improving the horizontal side-coupled characteristic of hypersonic aircraft
Office, including wing, fuselage, V tail, V tail rear rudder, trailing edge rudder and abdomeinal fin；Wing is symmetrically mounted below fuselage, V tail pair
Title is mounted on above fuselage afterbody, and abdomeinal fin is mounted on fuselage bottom rear；Trailing edge installs trailing edge rudder respectively；After V tail
Edge installs V tail rear rudder respectively；Trailing edge rudder and V tail rear rudder are the air-operated control rudder face of aircraft.
Wing is trapezoidal, the lower aerofoil of two panels aerofoil surface and body bottom surface smooth transition as an entirety.
The leading edge shape of wing is straight line or curve, leading edge of a wing sweepback.
V tail has two panels, and the inclination of V tail is installed, and the angle theta between two panels V tail is 80 °~100 °.
Abdomeinal fin is triangle, and angle of sweep λ is greater than 70 °.
Anti- under trailing edge rudder, inverted diherdral γ is 10 °~20 °.
The present invention compared with prior art the advantages of it is as follows:
(1) present invention manipulates pitch channel and roll channel using the rear rudder that there is lower anti-espionage to levy, Neng Goufei
Conventional pneumatic layout is often effectively eliminated under the big angle of attack due to roll guidance coupling effect bring medio-lateral instability, thus
Improve horizontal lateral closed loop stability under the big angle of attack.
(2) the abdomeinal fin design that the present invention uses can improve lateral stability under the big angle of attack, reduce roll stability, from
And achieve the effect that improve horizontal side-coupled characteristic under the big angle of attack.
(3) the V tail rear rudder that uses of the present invention may be implemented the manipulation of jaw channel, at the same can also to pitch channel into
Row manipulation.
Detailed description of the invention
Fig. 1 is the schematic three dimensional views of existing hypersonic aircraft aerodynamic arrangement.
Fig. 2 is hypersonic aircraft three-dimensional profile figure of the invention.
Fig. 3 is trailing edge rudder inverted diherdral and V tail angle schematic diagram.
Fig. 4 is longitudinal profile and abdomeinal fin angle of sweep schematic diagram.
Fig. 5 is the lateral stability comparison diagram of hypersonic vehicle of the present invention and existing hypersonic vehicle.
Specific embodiment
Below with reference to example, illustrate a specific embodiment of the invention.
As shown in figs. 2 to 4, the aerodynamic arrangement of the horizontal side-coupled characteristic of a kind of improvement hypersonic aircraft of the invention,
Including 1, fuselage 2 of a pair of of wing, a pair of V tail 3, a pair of V tail rear rudder 4, a pair of of trailing edge rudder 5 and an abdomeinal fin 6；Machine
The wing 1 is symmetrically mounted on 2 lower section of fuselage, and V tail 3 is symmetrically mounted on 2 rear upper of fuselage, and abdomeinal fin 6 is mounted on 2 bottom rear of fuselage；
1 rear of wing installs trailing edge rudder 5 respectively；3 rear of V tail installs V tail rear rudder 4 respectively；Trailing edge rudder 5 and V tail rear
Rudder 4 is the air-operated control rudder face of aircraft.
Fuselage is generated according to overall dimension and charge space demand, fuselage 2 is for semicolumn, half-conical or according to plot ratio
The arbitrary shape for needing and designing.
Wing 1 be it is trapezoidal, wing 1 is located at the lower section of fuselage 2, and the leading edge shape of wing 1 is straight line or curve, wing 1 and machine
The lower aerofoil that 2 bottom surface of body can be connected as an entirety, this design can obtain higher lift resistance ratio.
Two panels V tail 3 is fixed on 1 rear upper of fuselage, and the angle theta between two panels V tail 3 is 80 °~100 °.V tail 3 can rise
To the effect for improving lateral stability, and this act under large angle of attack can still be maintained.
Abdomeinal fin 6 is fixed on 1 lower section of fuselage, and angle of sweep λ is generally higher than 70 °, and abdomeinal fin 6 can improve lateral steady under the big angle of attack
It is qualitative, roll stability is reduced, to achieve the effect that improve horizontal side-coupled characteristic under the big angle of attack.
The manipulation of pitch channel and roll channel is designed using trailing edge rudder 5, and trailing edge rudder 5 is levied with lower anti-espionage,
Inverted diherdral γ is 10 °~20 °.Under the design of anti-rear rudder 5 can effectively eliminate Conventional pneumatic layout under the big angle of attack by
In roll guidance coupling effect bring medio-lateral instability, so as to improve lateral closed loop stability horizontal under the big angle of attack.
Fig. 5 compared the LCDP of hypersonic vehicle of the present invention and existing class HTV-2 hypersonic vehicle with angle of attack variation song
Line, LCDP are also lateral control departure parameter, yaw stability criterion when being aileron movement, for predicting unfavorable yawing
Surmount and yaw Divergent Phenomenon caused by yaw static-stability torque, cross lateral closed loop of the aircraft in roll guidance can be reacted
Stability.The LCDP static stability decision condition of (x-axis is facing forward, and upward, z-axis is towards the right side for y-axis) under flight coordinate system are as follows:
LCDP < 0, static-stability；
LCDP > 0, it is quiet unstable.
From Fig. 5 it can be found that the LCDP of (α > 15 °) class HTV-2 hypersonic vehicle is greater than zero under the big angle of attack, lateral shakiness
It is fixed；And the LCDP of hypersonic vehicle of the present invention keeps LCDP less than zero in calculating range of angles of attack, this illustrates the present invention
Design can improve horizontal lateral closed loop stability under the big angle of attack.
The manipulation of jaw channel realizes that V tail rear rudder 4 can keep rudder under large angle of attack by V tail rear rudder 4
Effect, while can also be manipulated on pitch channel.
The unspecified book of the present invention partly belongs to technology well known to those skilled in the art.
Claims (6)
1. a kind of aerodynamic arrangement for improving the horizontal side-coupled characteristic of hypersonic aircraft, it is characterised in that: including wing (1),
Fuselage (2), V tail (3), V tail rear rudder (4), trailing edge rudder (5) and abdomeinal fin (6)；Wing (1) is symmetrically mounted under fuselage (2)
Side, V tail (3) are symmetrically mounted on fuselage (2) rear upper, and abdomeinal fin (6) is mounted on fuselage (2) bottom rear；Wing (1) fate afterwards
It An Zhuan not trailing edge rudder (5)；V tail (3) rear installs V tail rear rudder (4) respectively；Trailing edge rudder (5) and V tail rear rudder
It (4) is the air-operated control rudder face of aircraft.
2. a kind of aerodynamic arrangement for improving the horizontal side-coupled characteristic of hypersonic aircraft according to claim 1, special
Sign is: wing (1) is trapezoidal, the bottom wing of two panels wing (1) aerofoil and the smooth transition of fuselage (2) bottom surface as an entirety
Face.
3. a kind of aerodynamic arrangement for improving the horizontal side-coupled characteristic of hypersonic aircraft according to claim 2, special
Sign is: the leading edge shape of wing (1) is straight line or curve, wing (1) leading-edge sweep.
4. a kind of aerodynamic arrangement for improving the horizontal side-coupled characteristic of hypersonic aircraft according to claim 1 or 2,
Be characterized in that: V tail (3) has two panels, and V tail (3) inclination is installed, and the angle theta between two panels V tail (3) is 80 °~100 °.
5. a kind of aerodynamic arrangement for improving the horizontal side-coupled characteristic of hypersonic aircraft according to claim 4, special
Sign is: abdomeinal fin (6) is triangle, and angle of sweep λ is greater than 70 °.
6. a kind of aerodynamic arrangement for improving the horizontal side-coupled characteristic of hypersonic aircraft according to claim 5, special
Sign is: anti-under trailing edge rudder (5), inverted diherdral γ is 10 °~20 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910578024.8A CN110395389A (en) | 2019-06-28 | 2019-06-28 | A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft |
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| CN201910578024.8A CN110395389A (en) | 2019-06-28 | 2019-06-28 | A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111994263A (en) * | 2020-07-15 | 2020-11-27 | 中国科学院力学研究所 | Hypersonic aircraft for improving course stability and design method thereof |
Citations (5)
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|---|---|---|---|---|
| FR2254481A1 (en) * | 1973-12-13 | 1975-07-11 | Messerschmitt Boelkow Blohm | Aircraft with canards and twin fin tailplane - has stable control afforded by canards anhedrally and fins dihedrally arranged |
| CN106507755B (en) * | 2008-12-12 | 2011-02-16 | 中国航天空气动力技术研究院 | A kind of pneumatic control layout for sweepback delta-wing aircraft |
| CN106043668A (en) * | 2016-07-06 | 2016-10-26 | 中国人民解放军海军航空工程学院 | Aerodynamic configuration of three-surface aircraft |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN107839893A (en) * | 2017-09-25 | 2018-03-27 | 中国商用飞机有限责任公司 | aircraft |
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2019
- 2019-06-28 CN CN201910578024.8A patent/CN110395389A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2254481A1 (en) * | 1973-12-13 | 1975-07-11 | Messerschmitt Boelkow Blohm | Aircraft with canards and twin fin tailplane - has stable control afforded by canards anhedrally and fins dihedrally arranged |
| CN106507755B (en) * | 2008-12-12 | 2011-02-16 | 中国航天空气动力技术研究院 | A kind of pneumatic control layout for sweepback delta-wing aircraft |
| CN106043668A (en) * | 2016-07-06 | 2016-10-26 | 中国人民解放军海军航空工程学院 | Aerodynamic configuration of three-surface aircraft |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN107839893A (en) * | 2017-09-25 | 2018-03-27 | 中国商用飞机有限责任公司 | aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111994263A (en) * | 2020-07-15 | 2020-11-27 | 中国科学院力学研究所 | Hypersonic aircraft for improving course stability and design method thereof |
| CN111994263B (en) * | 2020-07-15 | 2022-03-08 | 中国科学院力学研究所 | Hypersonic aircraft for improving course stability and design method thereof |
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Application publication date: 20191101 |