CN103057695B - A kind of combination rudder face of tailless aircraft - Google Patents
A kind of combination rudder face of tailless aircraft Download PDFInfo
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Abstract
A combination rudder face for tailless aircraft, comprises the embedded rudder face and elevon that are parallelogram.Two straight flanges forming the parallelogram profile of embedded rudder face and elevon all with fuselage axis parallel; Described embedded rudder face is all parallel with residing trailing edge with two hypotenuses of the parallelogram profile of elevon.Embedded rudder face in combination rudder face and elevon are in the same exhibition of wing to position, and the position of embedded rudder face is near the leading edge of a wing.The trailing edge of elevon overlaps with trailing edge.The deflection angle of embedded rudder face is 90 ° to the maximum, and the deflection angle of elevon is ± 30 °.The present invention can increase lift, makes up embedded rudder face and opens the loss of lift caused; Increase the Longitudinal static stability of tailless configuration, thus reduce or eliminate coupling rolling moment, separated flow region can be increased, obtain larger drag increment, effectively alleviate longitudinal trim burden, improve directional control efficiency.
Description
Technical field
The present invention relates to the design of anury blended wing-body aircraft directional control rudder face, specifically a kind of combination rudder face of tailless aircraft.
Background technology
Anury blended wing-body aircraft, compared to conventional airplane, eliminates the parts such as horizontal tail, elevating rudder, vertical fin, yaw rudder due to it, in addition adopt flat lifting body fuselage design, the smooth fusion of Wing-Body Configurations, thus substantially reduce and soak area, reduce full machine resistance, there is very high pneumatic efficiency.Anury blended wing-body aircraft will become with low oil consumption, anti-emission carburetor, low noise etc. as the desirable aerodynamic arrangement's form of the large-scale passenger plane of future new era of main design goal.
The ultimate challenge of anury blended wing-body airplane design is that it cancels the course stability and Heading control problem brought after traditional vertical fin designs.For realizing the course manipulation of aircraft, coordination rolling is motor-driven, resist landing crosswind and alleviate non-symmetrical load, realize the flight of full flight envelope controlled, and reach satisfied flight quality, tailless configuration needs novel directional control rudder face to replace the function of traditional vertical fin yaw rudder, and must guarantee to produce enough yaw control moment.
At present, the Main Means realizing tailless aircraft directional control is on wing, arrange resistance class rudder face, as split-drag-rudder, embedded rudder face, complete dynamic wing tip etc.Wherein, embedded rudder face have structure simple, respond rapid, easy to maintenance, directional control efficiency is higher, be arranged in top airfoil is beneficial to the advantages such as stealthy, is a kind of ideal directional control rudder face.But use embedded rudder face to carry out Heading control, under the larger rudder face degree of bias, the rolling moment of its coupling is often very large, has been unfavorable for turning action, especially can not have met flat bank and gentle bank demand; The new line pitching moment increment of embedded rudder face coupling further reduces again the Longitudinal static stability of tailless aircraft, adds longitudinal trim burden.For reducing or eliminate the adverse effect of coupling rolling moment and coupling pitching moment, often need numerous rudder faces such as elevon, flaperon, embedded rudder face to deflect the maneuvering performance that just can reach and meet the demands simultaneously, cause rudder face control law complicated, the problems such as safety factor is low.Therefore, as few effectors deployment of how trying one's best obtains high directional control efficiency, low coupling rolling moment and favourable pitching moment characteristic, one of gordian technique of anury blended wing-body airplane design is become.
Summary of the invention
For overcoming the shortcoming bringing large coupling rolling moment and unfavorable pitching moment when embedded control surface deflection carries out directional control, the present invention proposes a kind of combination rudder face of tailless aircraft.
The present invention includes embedded rudder face and elevon.Described embedded rudder face is identical with the oad of elevon 4, is parallelogram.Two straight flanges of the parallelogram profile of the embedded rudder face of described formation and elevon all with fuselage axis parallel; Described embedded rudder face is all parallel with residing trailing edge with two hypotenuses of the parallelogram profile of elevon.
Embedded rudder face in described combination rudder face and elevon are in the same exhibition of wing to position, and the position of described embedded rudder face is near the leading edge of a wing; The position of described elevon is near trailing edge.The trailing edge of elevon overlaps with trailing edge.
The span distance D1=0.83L of the straight flange distance fuselage axis, outside of the embedded rudder face in described combination rudder face; The span distance D2=0.63L of the straight flange distance fuselage axis, inner side of the embedded rudder face in described combination rudder face.The tangential length D3 of embedded rudder face and the tangential length D4 of elevon is respectively 0.3C, opens up and is respectively 0.2L to length.Space D 5 between embedded rudder face and the adjacent surface of elevon is 0.1C.Described L is aircraft half length, and described C is the wing chord length of m position, leading edge place outside combination rudder face.
The two ends of described embedded rudder face leading edge are hinged with the hinge axis be fixed on wing, and can deflect around this hinge axis, and deflection angle is 90 ° to the maximum.
The rotating shaft of described elevon is arranged in wing, and the leading edge of elevon is arranged in this rotating shaft by bearing, and can do ± 30 ° of deflections around this rotating shaft.When the deflection angle of elevon is 0 °, smooth transition between elevon and embedded rudder face.
In the present invention, the wing of fuselage both sides is respectively furnished with one group of combination rudder face, and the combination rudder face be positioned on the wing of both sides is symmetrical.
Two straight flanges of embedded rudder face and elevon are parallel to fuselage axis, and two hypotenuses are parallel with the trailing edge of residing wing.The leading edge of elevon is arc-shaped, so that it can deflect around the shaft up and down.Embedded rudder face in combination rudder face and elevon are in the same exhibition of wing to position.Embedded rudder face is installed near the leading edge of a wing; Elevon is installed near trailing edge, and the trailing edge of elevon overlaps with trailing edge.
When carrying out directional control, open left side combination rudder face to left drift, go off course to the right, open right side combination rudder face.Wherein, on the embedded rudder face in combination rudder face partially, under elevon partiallyAdopt combination rudder face scheme to carry out directional control, wing camber can be changed by the elevon in combination rudder face on the one hand, increase lift, make up embedded rudder face and open the loss of lift caused, thus reduce or eliminate coupling rolling moment.On the other hand, cause full machine aerodynamic loading to distribute after combined rudder deflecting facet to change, partially make wing rear portion aerodynamic loading increase under the elevon in combination rudder face, nose-down pitching moment increment will be brought, thus increase the Longitudinal static stability of tailless configuration, and significantly reduce longitudinal trim burden.The more important thing is, combination rudder face scheme can effectively utilize the interference between its embedded rudder face and elevon to increase separated flow region, obtains larger drag increment, thus substantially increases directional control efficiency.
Compared with prior art, the present invention has following outstanding effect:
1., by embedded rudder face and elevon are formed combination rudder face form, significantly improve directional control efficiency.Test proves, when on the embedded rudder face in combination rudder face inclined 30 °, under elevon when inclined 30 °, its yawing moment produced adds 30% ~ 70% when being comparatively used alone embedded rudder face.
2. the coupling rolling moment brought when effectively reducing directional control, reduces horizontal decoupling zero difficulty.When combination rudder face in embedded rudder face on inclined 30 °, under elevon when inclined 30 °, can substantially eliminate coupling rolling moment, obtain pure directional control moment, possess from decoupling ability, namely no longer need other control surface deflections to carry out horizontal decoupling zero, thus decrease effectors deployment needs, simplify rudder face control law.
3. add the Longitudinal static stability of tailless aircraft.Because tailless configuration's aircraft adopts quiet instability design usually, during flight, need its nose-up pitching moment of trim.To wing camber be changed after elevon deflection in combination rudder face, and increase the aerodynamic loading at wing rear portion, produce nose-down pitching moment increment, Longitudinal static stability is increased, also mitigate longitudinal trim burden.When combination rudder face in embedded rudder face on inclined 30 °, under elevon when inclined 30 °, the longitudinal moment trim of main state of flight can be realized, no longer need other control surface deflections to participate in longitudinal trim, thus decrease effectors deployment needs, simplify rudder face control law.
4. combine embedded rudder face in rudder face and the visual different mission phase of the elevon deflection angle different demand Reasonable adjustment to yawing moment and rolling moment.As needed large yawing moment and little coupling rolling moment to complete horizontal course maneuvering action, then can increase the embedded rudder face degree of bias, and suitably reduce the elevon degree of bias; As motor-driven in flat bank need be carried out, then can suitably increase the elevon degree of bias, reduce the embedded rudder face degree of bias, to eliminate coupling rolling moment.
5. combine rudder face scheme and add directional control redundancy, improve flight safety.As when the embedded rudder face combined in rudder face or elevon et out of order cannot use, remaining rudder face can deflect as flaperon etc. reconfigures the gesture stability of course in length and breadth participating in tailless aircraft with other rudder faces.
6. combined rudder mask has good multi-functional attribute.Combination rudder face both one-sidedly can have been opened and also can open both sides, one-sided when opening, and can complete directional control and anti-cross wind flying; When bilateral symmetry is opened, at cruising flight phase, the function of vertical fin can be served as, realize course and increase steady; In the landing stage, can be used for regulating full machine to rise drag characteristic, improve takeoff and landing performance.
Accompanying drawing explanation
The full machine birds-eye view of accompanying drawing 1 anury blended wing-body aircraft;
Accompanying drawing 2 anury blended wing-body aircraft side birds-eye view;
Accompanying drawing 3 combines rudder face partial schematic diagram;
Accompanying drawing 4 is with the wing profile schematic diagram of combination rudder face;
Accompanying drawing 5 combined rudder deflecting facet schematic diagram;
The embedded control surface deflection partial enlarged drawing of accompanying drawing 6;
Accompanying drawing 7 combines rudder face and compares with the yawing moment of single embedded rudder face;
Accompanying drawing 8 combines rudder face and compares with the rolling moment of single embedded rudder face;
The pitching moment that accompanying drawing 9 combines rudder face and single embedded rudder face and common rudder face not open mode compares;
The nowed forming of the common rudder face of accompanying drawing 10 not open mode;
The nowed forming of the single embedded rudder face of accompanying drawing 11;
Accompanying drawing 12 combines the nowed forming of rudder face;
The distribution of pressure that accompanying drawing 13 combines rudder face and single embedded rudder face and common rudder face not open mode compares.Wherein:
1. fuselage axis; 2. combine rudder face; 3. embedded rudder face; 4. elevon; 5. trailing edge; 6. the leading edge of a wing; 7. the outer straight flange of embedded rudder face; 8. straight flange in embedded rudder face; 9. elevon rotating shaft; 10. wing profile; 11. wing covers; 12. embedded rudder face hinge axis; The yawing moment of 13. single embedded rudder faces; The yawing moment of 14. combination rudder faces; The rolling moment of 15. single embedded rudder faces; The rolling moment of 16. combination rudder faces; Pitching moment when 17. common rudder faces are not opened; The pitching moment of 18. single embedded rudder faces; The pitching moment of 19. combination rudder faces; Distribution of pressure when 20. common rudder faces are not opened; The distribution of pressure of 21. single embedded rudder faces; The distribution of pressure of 22. combination rudder faces.
L: anury blended wing-body aircraft half length;
M: leading edge outside combination rudder face;
C: the wing chord length of leading edge m position outside combination rudder face;
D1: the outer straight flange of combination rudder face is to the span distance of fuselage axis;
D2: in combination rudder face, straight flange is to the span distance of fuselage axis;
D3: embedded rudder face chord length;
D4: elevon face chord length;
D5: the spacing of embedded rudder face and elevon adjacently situated surfaces;
δ 1: embedded control surface deflection angle;
δ 2: elevon deflection angle;
T: embedded rudder face thickness.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
The full machine birds-eye view of anury blended wing-body aircraft as shown in Figure 1.The wing of fuselage both sides is furnished with one group of combination rudder face 2 respectively, and described in the combination rudder face 2 that is positioned on the wing of both sides symmetrical.Because the symmetrical and rudder face of full machine geometry is also for being arranged symmetrically with, therefore the present invention is only described with side, as shown in Figure 2.
Combination rudder face 2 comprises embedded rudder face 3 and elevon 4.Described embedded rudder face 3 is identical with the oad of elevon 4, is parallelogram.The embedded rudder face of described formation 3 is all parallel with fuselage axis 1 with two straight flanges of the parallelogram profile of elevon 4; Described embedded rudder face 3 is all parallel with residing trailing edge 5 with two hypotenuses of the parallelogram profile of elevon 4.The leading edge of elevon 4 is arc-shaped, and the wing place coordinated with this elevon 4 leading edge is also arc-shaped, to facilitate the deflection of this elevon 4.
Embedded rudder face 3 in described combination rudder face 2 and elevon 4 are in the same exhibition of wing to position, and described embedded rudder face 3 is installed near the leading edge of a wing 6; Described elevon 4 is installed near trailing edge 5.The trailing edge of elevon 4 overlaps with trailing edge.
The outside straight flange 7 of the embedded rudder face 3 in described combination rudder face 2 is apart from the span distance D1=0.83L of fuselage axis 1; The inner side straight flange 8 of the embedded rudder face 3 in described combination rudder face 2 is apart from the span distance D2=0.63L of fuselage axis 1.The tangential length D3 of embedded the rudder face 3 and tangential length D4 of elevon 4 is respectively 0.3C, opens up and is respectively 0.2L to length.Space D 5 between embedded rudder face 3 and the adjacent surface of elevon 4 is 0.1C.Described L is aircraft half length, and described C is the wing chord length of m position, leading edge place outside combination rudder face 2.
The profile of embedded rudder face 3 and elevon 4 is all obtained by the former wing profile 10 of subdivision.
After the chordwise location of embedded rudder face 3 on wing is determined to position with exhibition, directly obtained by cutting wing cover 11.The thickness t of embedded rudder face is the thickness of wing cover, described embedded rudder face is embedded in wing completely, and can not change former wing profile.The two ends of embedded rudder face 3 leading edge are hinged with the hinge axis 12 be fixed on wing, and can deflect around this hinge axis, and deflection angle is 90 ° to the maximum.
After the chordwise location of elevon 4 on wing is determined to position with exhibition, directly obtained by cutting wing.The leading edge of elevon 4 is arc-shaped.
The rotating shaft 9 of elevon 4 is arranged in wing, and the leading edge of elevon 4 is arranged in this rotating shaft by bearing, and can do ± 30 ° of deflections around this rotating shaft.When the deflection angle of elevon 4 is 0 °, smooth transition between elevon 4 and embedded rudder face 3.
In the present embodiment, when carrying out directional control, the embedded rudder face 3 in combination rudder face 2 will deflect with elevon 4 simultaneously.Wherein, on embedded rudder face 3 partially, elevon 4 times partially, as shown in Figure 5.After embedded rudder face 3 and elevon 4 form and combine rudder face, interfere with each other owing to existing between two kinds of rudder faces, will favourable nowed forming change be formed, and expand to be separated and stay eddy zone, increase resistance, thus the yawing moment that generation is larger, raising directional control efficiency.Elevon 4 times in combination rudder face 2 partially, will increase wing camber, make up this side due to embedded rudder 3 open after the airfoil lift loss that causes, thus fundamentally reduce or eliminate the rolling moment that is coupled.In addition, because elevon 4 is positioned at wing rear portion, loading effect after the wing partially brought under it, will produce nose-down pitching moment increment, thus increase the Longitudinal static stability of quiet unstable tailless aircraft, alleviate longitudinal trim burden simultaneously.The deflection angle of embedded rudder face 3 and elevon 4 and the visual different flight state of unfolding mode adjust accordingly lift, resistance, pitching moment, yawing moment, the isoparametric real needs of rolling moment, to complete flat bank, gentle bank, horizontal course maneuvering, anti-cross wind flying, improve the multiple-tasks such as takeoff and landing performance.
Utilize computational fluid mechanics simulation software, demonstrate the good aeroperformance that combined rudder mask of the present invention has high directional control efficiency, low coupling rolling moment, increase Longitudinal static stability, flying speed is Mach number 0.2.
Can see from the contrast of Fig. 7 yawing moment, when combining embedded control surface deflection angle δ 1=30 °, elevon deflection angle δ 2=30 ° in rudder face, the yawing moment 14 of the combination rudder face produced under each angle of attack is all significantly improved compared to the yawing moment 13 being used alone embedded rudder face, increase by 30% ~ 70% respectively depending on angle of attack difference, thus significantly improve directional control efficiency.The contrast of Fig. 8 rolling moment then shows, and combination rudder face is while raising directional control efficiency, and the rolling moment 16 of the combination rudder face of its coupling is compared the rolling moment 15 being used alone embedded rudder face and but greatly reduced.When embedded control surface deflection angle δ 1=30 °, elevon deflection angle δ 2=30 °, the configuration of this combination rudder face degree of bias has possessed the ability eliminating coupling rolling moment completely, pure Heading control moment can be obtained, achieve from decoupling zero, this reduces effectors deployment needs during yaw control, thus simplify rudder face control law.
The contrast of Fig. 9 pitching moment then clearly shows, when being used alone embedded rudder face, pitching moment 17 when the pitching moment 18 of single embedded rudder face is not opened compared to common rudder face creates the pitching moment increment of new line, to longitudinal statical unstability of tailless configuration's aircraft be increased, too increase longitudinal trim burden.And during use combination rudder face, the pitching moment 19 of combination rudder face, compared to the pitching moment 18 of single embedded rudder face, brings nose-down pitching moment increment, be conducive to the Longitudinal static stability increasing tailless aircraft, alleviate longitudinal trim burden simultaneously.As can be seen from the above analysis, the favourable change of Fig. 7 ~ Fig. 9 three-axis force square clearly shows the outstanding advantages of combination rudder face: high directional control efficiency, low coupling rolling moment, increase Longitudinal static stability, this is used alone embedded rudder face and cannot accomplishes.
Below in conjunction with the common rudder face of Figure 10 not open mode, the single embedded rudder face of Figure 11, Figure 12 combine nowed forming contrast under these three kinds of states of rudder face and the contrast of Figure 13 distribution of pressure, disclose combination rudder face further and produce high directional control efficiency, low coupling rolling moment, increase the physical mechanism of Longitudinal static stability.Can know from Figure 10 and see, when common rudder face is not opened, wing upper and lower surface is attachment flowing, is not separated.And after opening embedded rudder face, because wing geometric configuration changes, obvious separated flow has appearred in embedded rudder face rear portion, as shown in figure 11.
In Figure 13, sets forth the distribution of pressure 20 when common rudder face is not opened, the distribution of pressure 21 of single embedded rudder face and the distribution of pressure of combination rudder face.The distribution of pressure of contrast Figure 13 also can find, the air-flow due to embedded rudder face front is subject to the unexpected compression of embedded rudder face, and flow velocity reduces, pressure raises fast, define strong adverse pressure gradient, cause the more common rudder face of this region circular rector not open mode significantly reduce, cause loss of lift.
Also can see from Figure 11, after opening embedded rudder face, at trailing edge place, be separated the inducing action of staying whirlpool and wash effect by formation significantly, further reduce circular rector, exacerbate the loss of lift.Visible, the appearance of close coupling rolling moment mainly embedded rudder face causes this side airfoil lift loss to cause more greatly after opening, and close coupling rolling moment is disadvantageous to the turning action completing aircraft, or even danger.After elevon and embedded rudder face form and combine rudder face, Figure 13 distribution of pressure shows, and under combination rudder face configuration, the strong adverse pressure gradient in embedded rudder face front still exists, and lift still has loss.But, with be used alone embedded rudder face unlike, because elevon changes wing camber, air-flow, when arriving trailing edge, creates significantly and washes effect, as shown in figure 12, this makes upper surface of the airfoil air-flow velocity increase, being reflected on Figure 13 distribution of pressure is exactly that the circular rector at embedded rudder face rear portion obviously promotes, and compensate for the loss of lift that embedded rudder face causes, thus is fundamentally preventing the generation of large coupling rolling moment.In addition, Figure 13 distribution of pressure also shows, to the rear under elevon, and the aerodynamic loading at wing rear portion increases, loading effect after being formed, and this will bring nose-down pitching moment increment, is conducive to the Longitudinal static stability increasing tailless aircraft.The more important thing is, Figure 12 reflects, elevon brings down to be washed effect that the separation at embedded rudder face rear portion is stayed when eddy zone is used alone embedded rudder face than Figure 11 is larger, thus significantly increase the resistance of combination rudder face side, this is also that combination rudder face of the present invention can obtain larger yawing moment to improve the root place of directional control efficiency.
Claims (4)
1. a combination rudder face for tailless aircraft, is characterized in that, comprises embedded rudder face and elevon; Described embedded rudder face is identical with the oad of elevon, is parallelogram; Two straight flanges of the parallelogram profile of the embedded rudder face of described formation and elevon all with fuselage axis parallel; Described embedded rudder face is all parallel with residing trailing edge with two hypotenuses of the parallelogram profile of elevon; Embedded rudder face in described combination rudder face and elevon are in the same exhibition of wing to position, and the position of described embedded rudder face is near the leading edge of a wing; The position of described elevon is near trailing edge; The trailing edge of elevon overlaps with trailing edge;
The wing of fuselage both sides is respectively furnished with one group of combination rudder face, and the combination rudder face be positioned on the wing of both sides is symmetrical;
The span distance D1=0.83L of the straight flange distance fuselage axis, outside of the embedded rudder face in described combination rudder face; The span distance D2=0.63L of the straight flange distance fuselage axis, inner side of the embedded rudder face in described combination rudder face; The tangential length D3 of embedded rudder face and the tangential length D4 of elevon is respectively 0.3C, opens up and is respectively 0.2L to length; Space D 5 between embedded rudder face and the adjacent surface of elevon is 0.1C; Described L is aircraft half length, and described C is the wing chord length of m position, leading edge place outside combination rudder face.
2. the combination rudder face of tailless aircraft as claimed in claim 1, is characterized in that, the two ends of described embedded rudder face leading edge are hinged with the hinge axis be fixed on wing, and can deflect around this hinge axis, and deflection angle is 90 ° to the maximum.
3. the combination rudder face of tailless aircraft as claimed in claim 1, it is characterized in that, the rotating shaft of described elevon is arranged in wing, and the leading edge of elevon is arranged in this rotating shaft by bearing, and can do ± 30 ° of deflections around this rotating shaft.
4. the combination rudder face of tailless aircraft as claimed in claim 3, is characterized in that, when the deflection angle of elevon is 0 °, and smooth transition between elevon and embedded rudder face.
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| CN104554707A (en) * | 2015-01-14 | 2015-04-29 | 西北工业大学 | Novel flying wing unmanned aerial vehicle and heading control method thereof |
| CN105398565A (en) * | 2015-10-23 | 2016-03-16 | 庆安集团有限公司 | Rear wing modification mechanism for flying wing aircraft |
| CN107697270A (en) * | 2017-09-29 | 2018-02-16 | 南京航空航天大学 | Dismantled and assembled aileron mounting structure |
| CN109625240A (en) * | 2018-11-23 | 2019-04-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Weaken the apparatus and system of flying wing layout plane pitching angle moment nonlinearity |
| CN109703744A (en) * | 2019-02-20 | 2019-05-03 | 西安爱生技术集团公司 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
| CN114357799B (en) * | 2022-01-17 | 2024-01-12 | 成都飞机工业（集团）有限责任公司 | Differential resistance rudder pre-deflection judging method, device, equipment and storage medium |
| CN115092380A (en) * | 2022-08-22 | 2022-09-23 | 中国空气动力研究与发展中心空天技术研究所 | Three-channel decoupling control surface suitable for flat fusion body layout aircraft |
| CN115489722B (en) * | 2022-11-07 | 2023-03-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Stepless switching control method and device for control surface of aircraft, aircraft and medium |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4553721A (en) * | 1983-08-05 | 1985-11-19 | Lockheed Corporation | Spoiler device for attachment to a leading edge slat |
| US8191820B1 (en) * | 2007-12-11 | 2012-06-05 | Northrop Gurmman Corporation | Flying wing aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6892982B2 (en) * | 2003-01-29 | 2005-05-17 | Northrop Grumman Corporation | Aircraft with forward opening inlay spoilers for yaw control |
| US7108230B2 (en) * | 2003-06-06 | 2006-09-19 | Northrop Grumman Corporation | Aircraft with topside only spoilers |
-
2013
- 2013-01-08 CN CN201310005860.XA patent/CN103057695B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4553721A (en) * | 1983-08-05 | 1985-11-19 | Lockheed Corporation | Spoiler device for attachment to a leading edge slat |
| US8191820B1 (en) * | 2007-12-11 | 2012-06-05 | Northrop Gurmman Corporation | Flying wing aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 无尾布局嵌入式舵面的大迎角纵向操纵能力研究;孙静 等;《航空学报》;20120325;第33卷(第3期);第430-43页 * |
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