CN103921932A - Yawing pneumatic control augmentation type lift-body vehicle - Google Patents
Yawing pneumatic control augmentation type lift-body vehicle Download PDFInfo
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- CN103921932A CN103921932A CN201410174278.0A CN201410174278A CN103921932A CN 103921932 A CN103921932 A CN 103921932A CN 201410174278 A CN201410174278 A CN 201410174278A CN 103921932 A CN103921932 A CN 103921932A
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Abstract
The invention discloses a yawing pneumatic control augmentation type lift-body vehicle which comprises a body and a lateral tangent plane, wherein the lateral tangent plane is positioned on two sides in the rear of the body; the lateral tangent plane is a curved surface; as the curved surface is close to the rear of the body, the slope of the curved surface is gradually increased relative to a central axis of the body; the lateral tangent plane is perpendicular to an XOZ plane of the vehicle. An expansion-compression process allowing the rear body to laterally flow is constructed only through the lateral tangent plane based on a pneumatic principle, the yawing stability of the vehicle can be effectively improved, and the problems such as structure, thermal protection and pneumatic elasticity/pneumatic thermoelasticity brought by the process of mounting a heading stability plane are solved.
Description
Technical field
The present invention relates to a kind of lifting body aircraft, particularly the steady type lifting body of the pneumatic increasing of a kind of driftage aircraft.
Background technology
Produce the required lift of flight because lifting body aircraft mainly relies on fuselage, make lifting body there is very high volume characteristic; Simultaneously due to simple in structure, fuselage dullness is larger, has greatly reduced aircraft thermal protection difficulty and thermal protection system added mass.Therefore, lifting body aircraft becomes the important selection of space flight reentry vehicle layout gradually.
With regard to stability, lifting body vehicle yaw stability of channel relatively a little less than, and with the increase of Mach number and the angle of attack, yaw stability reduces obviously, therefore ensures that enough yaw stability are the important process of lifting body layout pneumatic design.At present, lifting body aircraft generally improves vehicle yaw stability by course stabilator is installed.As U.S. X-33 aircraft has not only been installed two vertical tails at body upper surface, and both sides have installed the tilting empennage of 20 ° of drift angles, strengthen yaw stability to be desirably in when improving pitching stability.But, for mainly for the lifting body of hypersonic state flight, expose pneumatic rudder face and can be with and serve unsurmountable shortcoming: 1, under hypersonic flight state, the wave resistance that pneumatic rudder face produces can make resistance increase rapidly; 2, thin pneumatic rudder face has increased Flight Vehicle Structure and heat protection design difficulty; 3, pneumatic rudder face faces the insoluble problems such as serious aeroelasticity/aerothermo-elasticity under hypersonic flight state.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, from pneumatic angle, provide the steady type lifting body of the pneumatic increasing of a kind of novel driftage aircraft, to meet in the design of hypersonic lifting body aircraft aerodynamic arrangement improving the demand of yaw stability.
Technical scheme of the present invention is: the steady type lifting body of the pneumatic increasing of a kind of driftage aircraft comprises body and side direction tangent plane, described side direction tangent plane is positioned at the both sides of described After-Body, described side direction tangent plane is curved surface, and more close to described After-Body, the slope of the relatively described body center of curved surface axis increases gradually, and described side direction tangent plane is vertical with aircraft XOZ plane.
Described body is bored or bores more for single.
Described body section is shaped as rhombus or ellipse.
Described body can be with air rudder face.
The present invention's advantage is compared with prior art as follows:
(1) the present invention does not need additionally to install the stable rudder face of lifting body aircraft course, can effectively avoid installing the additional resistance that course stabilator brings.
(2) the present invention is based on pneumatic principle, only construct the expansion-compression process of rear body lateral flow by side direction tangent plane, not only can effectively improve vehicle yaw stability, avoid installing the problems such as structure, thermal protection and aeroelasticity/aerothermo-elasticity that course stabilator brings simultaneously.
Brief description of the drawings
Fig. 1 is the birds-eye view of the steady type lifting body of the list cone pneumatic increasing of driftage of the present invention aircraft.
Fig. 2 is the go off course birds-eye view of the steady type lifting body of pneumatic increasing aircraft of bipyramid of the present invention.
Fig. 3 is the 3 d effect graph of the steady type lifting body of the pneumatic increasing of the driftage of diamond-shaped cross-section of the present invention aircraft.
Fig. 4 is the 3 d effect graph of the steady type lifting body of the pneumatic increasing of the driftage of oval cross section of the present invention aircraft.
Fig. 5 is the original profile of lifting body aircraft in experimental example.
Fig. 6 is the bottom size figure of lifting body aircraft in experimental example.
Fig. 7 is the steady profile of pneumatic increasing of going off course in experimental example.
Fig. 8 is original profile and the driftage steady profile of pneumatic increasing side line of centers pressure coefficient correlation curve in experimental example.
Fig. 9 is original profile and the driftage steady type profile of pneumatic increasing course pressure heart correlation curve in experimental example.
In figure 1, body; 2, side direction tangent plane.
Detailed description of the invention
Embodiment:
As shown in Figure 1 to 4, the steady type lifting body of the pneumatic increasing of a kind of driftage provided by the invention aircraft, it comprises body 1 and side direction tangent plane 2.As shown in Fig. 1～Fig. 2, described body can be single cone, can be also many cones.As shown in Fig. 3～Fig. 4, described body section shape can be rhombus, can be also oval.Meanwhile, can be with other pneumatic rudder face on body.The both sides of body 1 are cut to the side direction tangent plane 2 forming as shown in Figure 1 to 4, to build the steady region of pneumatic increasing.Side direction tangent plane 2 of the present invention is positioned at the both sides at body 1 rear portion of lifting body aircraft, and vertical with aircraft XOZ plane.As shown in Figure 3, OZ represents the Width of aircraft, and OX represents the length direction of aircraft, and OY represents the short transverse of aircraft.And side direction tangent plane 2 is curved surface, and along with close to body 1 rear portion, the slope of the relative body center of curved surface axis increases gradually.So build after lifting body aircraft body side surface flow region compress afterwards that first expands, steady to realize the pneumatic increasing of going off course.
Experimental example:
In order to verify effect of the present invention, having selected especially diamond-shaped cross-section list cone lifting body aircraft is original profile, adopts computational fluid mechanics means to carry out calculation of aerodynamic characteristics and comparative analysis.
Example 1: lifting body model total length is 4000mm, Fig. 5 has provided the 3D modelling of original profile, and Fig. 6 has provided the size of lifting body aircraft: head bottom radius is that to fall radius of a circle be that 390mm, bottom width are that the radius of 1900mm and bottom lateral margin is 25mm for 50mm, top and the bottom.After adopting the inventive method to original profile, curved surface cutting is carried out in body two sides, the steady profile of the structure pneumatic increasing of driftage.Concrete cutting adopts radius R
sthe circular arc of=5700mm, is starting to carry out curved surface cutting apart from head 2050mm place.The curve of cutting curved surface in XOZ plane is configured as, and gets the tangent line of cutting starting point on curve parallel with central axis.Meanwhile, for ensureing rear body compressibility influence, model bottom is cut among a small circle, sees Fig. 7.
The concrete governing equation of aerodynamic characteristic numerical method is average Navier-Stokes equation, and numerical calculation form adopts second order Roe form, and adopts four step Runge-Kutta methods to carry out explicit time propelling.Turbulence model adopts Spalart-Allmaras (S-A) model.Adopt algebraic method to generate integrative-structure grid.Rated condition be Mach number Ma=6, angle of attack=0 °～20 °, angle of side slip β=5 °, flying height is got H=25km.
Fig. 8 is given in α=5 °, under ° state of β=5, and the surface pressure distribution curve of original profile and the steady profile of pneumatic increasing side position of center line.The longitudinal axis is nondimensionalization pressure coefficient, and transverse axis is the distance apart from head summit, and in figure, has provided respectively the pressure coefficient of two kinds of profiles at sideslip windward side and sideslip lee face.As seen from the figure, the steady type lifting body of the pneumatic increasing of driftage provided by the present invention aircraft, can after lifting body aircraft, build significant flow board expansion-compression process by body side surface, making to increase steady region first reduces to increase afterwards at the pressure coefficient of sideslip windward side, because dividing, windward side and lee face pressure at both sides difference-product be lateral force, therefore can find out that the present invention moves after higher-pressure region is remarkable, thereby increase yawing moment to improve yaw stability.Fig. 9 presses innermost being line to provide the steady type lifting body of the pneumatic increasing of driftage of the present invention aircraft by course yaw stability is strengthened to effect.Wherein the longitudinal axis is that the heart is pressed in course, and lateral forces is put relative head vertex distance and account for the percentum of aircraft body overall length, and transverse axis is the angle of attack.As seen from the figure, adopt the steady type lifting body of the pneumatic increasing of the driftage aircraft of invention, lifting body aircraft course moves after pressing the heart significantly, and yaw stability effectively improves.Within the scope of 0 °～20 ° of the angles of attack, yaw stability on average strengthens 7.93%; ° state in angle of attack=10, yaw stability strengthens degree maximum, and the more original profile yaw stability of the steady profile of pneumatic increasing strengthens 9.6%.Comprehensive, the present invention can play significant pneumatic increasing to lifting body vehicle yaw stability and surely act on.
In sum, the one proposed by the invention steady type lifting body of the pneumatic increasing aircraft of going off course, by curved surface cutting is carried out in lifting body aircraft After-Body side, build after lifting body aircraft the body side surface flow region compressing afterwards that first expands, after realizing higher-pressure region, lifting body side, move, reach and rely on pneumatic means to realize the object that yaw stability strengthens.The present invention does not need additionally to install the stable rudder face in course, and the additional resistance that can effectively avoid the stable rudder face in course to bring has also been avoided the problems such as structure, thermal protection and aeroelasticity/aerothermo-elasticity that pneumatic rudder face brings simultaneously.
As known by the technical knowledge, the present invention can realize by other the embodiment that does not depart from its Spirit Essence or essential feature.Therefore, above-mentioned disclosed embodiment, with regard to each side, is all casehistory, is not only.Within the scope of the present invention all or be all included in the invention in the change being equal in scope of the present invention.
Claims (4)
1. the steady type lifting body of the pneumatic increasing of a driftage aircraft, it is characterized in that: comprise body and side direction tangent plane, described side direction tangent plane is positioned at the both sides of described After-Body, described side direction tangent plane is curved surface, and along with close to described After-Body, the slope of the relatively described body center of described curved surface axis increases gradually, and described side direction tangent plane is vertical with aircraft XOZ plane.
2. the steady type lifting body of the pneumatic increasing of driftage according to claim 1 aircraft, is characterized in that: described body is single cone and bipyramid.
3. the steady type lifting body of the pneumatic increasing of driftage according to claim 1 and 2 aircraft, is characterized in that: described body section is shaped as rhombus or ellipse.
4. the steady type lifting body of the pneumatic increasing of a kind of driftage according to claim 1 and 2 aircraft, is characterized in that: described body can be with air rudder face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410174278.0A CN103921932B (en) | 2014-04-28 | 2014-04-28 | Go off course pneumatic increasing steady type lifting body aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410174278.0A CN103921932B (en) | 2014-04-28 | 2014-04-28 | Go off course pneumatic increasing steady type lifting body aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103921932A true CN103921932A (en) | 2014-07-16 |
| CN103921932B CN103921932B (en) | 2016-08-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410174278.0A Active CN103921932B (en) | 2014-04-28 | 2014-04-28 | Go off course pneumatic increasing steady type lifting body aircraft |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4149688A (en) * | 1976-10-01 | 1979-04-17 | Aereon Corporation | Lifting body aircraft for V/STOL service |
| DE3642640A1 (en) * | 1986-12-13 | 1988-06-23 | Dieter M Schulz | Wing (mainplane) design for ground-effect aircraft |
| US5884871A (en) * | 1997-03-27 | 1999-03-23 | Boeing North American, Inc. | Use of absorbing walls for laminar flow control |
| US6793171B1 (en) * | 2003-04-02 | 2004-09-21 | Northrop Grumman Corporation | Method and system for flying an aircraft |
| CN1816476A (en) * | 2003-05-05 | 2006-08-09 | 敏捷思有限责任公司 | Aircraft comprising a lift-generating fuselage |
-
2014
- 2014-04-28 CN CN201410174278.0A patent/CN103921932B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4149688A (en) * | 1976-10-01 | 1979-04-17 | Aereon Corporation | Lifting body aircraft for V/STOL service |
| DE3642640A1 (en) * | 1986-12-13 | 1988-06-23 | Dieter M Schulz | Wing (mainplane) design for ground-effect aircraft |
| US5884871A (en) * | 1997-03-27 | 1999-03-23 | Boeing North American, Inc. | Use of absorbing walls for laminar flow control |
| US6793171B1 (en) * | 2003-04-02 | 2004-09-21 | Northrop Grumman Corporation | Method and system for flying an aircraft |
| CN1816476A (en) * | 2003-05-05 | 2006-08-09 | 敏捷思有限责任公司 | Aircraft comprising a lift-generating fuselage |
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|---|---|
| CN103921932B (en) | 2016-08-24 |
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