CN103057695A - Combined control surface of tailless airplane - Google Patents
Combined control surface of tailless airplane Download PDFInfo
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- CN103057695A CN103057695A CN201310005860XA CN201310005860A CN103057695A CN 103057695 A CN103057695 A CN 103057695A CN 201310005860X A CN201310005860X A CN 201310005860XA CN 201310005860 A CN201310005860 A CN 201310005860A CN 103057695 A CN103057695 A CN 103057695A
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Abstract
A combined control surface of a tailless airplane comprises a parallelogram-shaped embedded control surface and a parallelogram-shaped elevon. Each of the two straight edges of each of the parallelograms forming the embedded control surface and the elevon is parallel to the central axis of the body of the airplane; and each of the two inclined edges of each of the parallelograms forming the embedded control surface and the elevon is parallel to the trailing edge of a positioning wing. The embedded control surface and the elevon in the combined control surface are positioned in a same span-wise position of the wing, and the position of the embedded control surface is close to the leading edge of the wing. The trailing edge of the elevon overlaps with the trailing edge of the wing. The largest deflect angle of the embedded control surface is 90DEG, and the deflect angle of the elevon is +/-30DEG. The combine control surface can increase the lift force, and makes up the lift loss caused by the opening of the embedded control surface; and the combined control surface increases the vertical static stability of the tailless layout, so the coupling rolling torque is reduced or eliminated, the separation flow area is increased, a large resistance increment is obtained, the vertical trimming burden is mitigated, and the course control efficiency is improved.
Description
Technical field
The present invention relates to merge without the empennage body design of aircraft directional control rudder face, specifically a kind of combination rudder face of tailless aircraft.
Background technology
Merge aircraft without the empennage body, than conventional airplane, because it has cancelled the parts such as horizontal tail, elevating rudder, vertical fin, yaw rudder, adopt flat lifting body fuselage design in addition, the smooth fusion of Wing-Body Configurations, thus greatly reduced to soak area, reduce full machine resistance, had very high pneumatic efficiency.Merging aircraft without the empennage body will become take low oil consumption, anti-emission carburetor, low noise etc. as the desirable aerodynamic arrangement's form of the large-scale passenger plane following of new generation of main design goal.
The ultimate challenge that merges airplane design without the empennage body is rear course stability and the course control problem of bringing of vertical fin design that its cancellation is traditional.For controlling in the course of realizing aircraft, the coordination lift-over is motor-driven, resist the landing crosswind and alleviate non-symmetrical load, realize that full flight envelope flight is 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 of realizing the tailless aircraft directional control is to arrange resistance class rudder face at wing, such as split-drag-rudder, embedded rudder face, complete moving wing tip etc.Wherein, that embedded rudder face has is simple in structure, response is rapid, easy to maintenance, directional control efficient is higher, be arranged in top airfoil is beneficial to the advantages such as stealthy, is a kind of comparatively desirable directional control rudder face.But, use embedded rudder face to carry out course control, under the larger rudder face degree of bias, the rolling moment of its coupling is often very large, is unfavorable for finishing turning action, especially can not satisfy flat bank and gentle bank demand; The new line pitching moment increment of embedded rudder face coupling has further reduced again the Longitudinal static stability of tailless aircraft, has increased vertical trim burden.For reducing or eliminate the adverse effect of coupling rolling moment and coupling pitching moment, often need the simultaneously deflection of numerous rudder faces such as elevon, flaperon, embedded rudder face just can reach the maneuvering performance that meets the demands, cause the rudder face control law complicated, the problem such as safety factor is low.Therefore, dispose to obtain high directional control efficient, low coupling rolling moment and favourable pitching moment characteristic such as few rudder face of how trying one's best, become one of gordian technique that merges airplane design without the empennage body.
Summary of the invention
For overcoming the shortcoming of 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 are all parallel with the fuselage axis; Two hypotenuses of the parallelogram profile of described embedded rudder face and elevon are all parallel with trailing edge of living in.
Embedded rudder face in the described combination rudder face and elevon are in the same exhibition of wing to the 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 outside straight flange of the embedded rudder face in the described combination rudder face is apart from the span distance D1=0.83L of fuselage axis; The inboard straight flange of the embedded rudder face in the described combination rudder face is apart from the span distance D2=0.63L of fuselage axis.The tangential length D3 of embedded rudder face and the tangential length D4 of elevon are respectively 0.3C, and exhibition is respectively 0.2L to length.Space D 5 between the adjacent surface of embedded rudder face and elevon is 0.1C.Described L is aircraft half length, and described C is the wing chord length of m position, leading edge place, the combination rudder face outside.
The two ends of described embedded rudder face leading edge are hinged with the hinge axis that is fixed on the wing, and can be around this hinge axis deflection, and deflection angle is 90 ° to the maximum.
The rotating shaft of described elevon is installed in the wing, and the leading edge of elevon is installed in this rotating shaft by bearing, and can do around this rotating shaft ± 30 ° of deflections.When the deflection angle of elevon is 0 °, smooth transition between elevon and the embedded rudder face.
Among the present invention, respectively be furnished with one group of combination rudder face on the wing of fuselage both sides, and the combination rudder face that is positioned on the wing of both sides is symmetrical.
Two straight flanges of embedded rudder face and elevon are parallel to the fuselage axis, and two hypotenuses are parallel with the trailing edge of wing of living in.The leading edge of elevon is circular-arc, so that its around the shaft up and down deflection.The same exhibition that embedded rudder face in the combination rudder face and elevon are in wing is to the 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, right side combination rudder face is then opened in driftage to the right.Wherein, partially, inclined to one side under the elevon on the embedded rudder face in the combination rudder face.Adopt combination rudder face scheme to carry out directional control, can change wing camber by the elevon in the combination rudder face on the one hand, increase lift, remedy embedded rudder face and open the loss of lift that causes, thereby reduce or eliminates the rolling moment that is coupled.On the other hand, cause full machine aerodynamic loading to distribute behind the combined rudder deflecting facet and change, under the elevon in the combination rudder face wing rear portion aerodynamic loading is increased, will bring the pitching moment increment of bowing, thereby increase the Longitudinal static stability of tailless configuration, and greatly alleviated vertical trim burden.The more important thing is that combination rudder face scheme can effectively utilize the interference between its embedded rudder face and the elevon to increase the separated flow zone, obtains larger drag increment, thereby has greatly improved directional control efficient.
Compared with prior art, the present invention has following outstanding effect:
1. by embedded rudder face and elevon are consisted of combination rudder face form, obviously improved directional control efficient.Evidence, on the embedded rudder face of combination in the rudder face inclined to one side 30 °, inclined to one side 30 ° the time, the yawing moment of its generation has increased by 30%～70% when using embedded rudder face more separately under the elevon.
2. the coupling rolling moment of having brought when having effectively reduced directional control has reduced horizontal decoupling zero difficulty.On the embedded rudder face of combination in the rudder face inclined to one side 30 °, under the elevon inclined to one side 30 ° the time, but elimination coupling rolling moment, obtain pure directional control moment, possessed from the decoupling zero ability, namely no longer need other control surface deflections to carry out horizontal decoupling zero, thereby reduced rudder face configuration needs, simplified the rudder face control law.
3. increased the Longitudinal static stability of tailless aircraft.Because tailless configuration's aircraft adopts quiet unstable design usually, needs its nose-up pitching moment of trim during flight.To change wing camber after the elevon deflection in the combination rudder face, increase the aerodynamic loading at wing rear portion, produce the pitching moment increment of bowing, so that Longitudinal static stability is increased, also alleviate vertical trim burden.On the embedded rudder face of combination in the rudder face inclined to one side 30 °, inclined to one side 30 ° the time, can realize the longitudinal moment trim of main state of flight under the elevon, no longer need other control surface deflections to participate in vertical trim, thereby reduced rudder face configuration needs, simplified the rudder face control law.
4. the embedded rudder face in the combination rudder face is rationally adjusted the different demands of yawing moment and rolling moment with the visual different mission phases of elevon deflection angle., then can increase the embedded rudder face degree of bias, and suitably reduce the elevon degree of bias in order to finish horizontal course maneuver such as the large yawing moment of need and little coupling rolling moment; It is motor-driven to carry out flat bank such as need, then can suitably increase the elevon degree of bias, reduces the embedded rudder face degree of bias, to eliminate the coupling rolling moment.
5. combination rudder face scheme has increased the directional control redundancy, has improved flight safety.As at embedded rudder face or the elevon et out of order can't use time of combination in the rudder face, remaining rudder face can reconfigure the in length and breadth course attitude control that deflection participates in tailless aircraft with other rudder faces such as flaperon etc.
6. the combined rudder mask has good multi-functional attribute.But the combination rudder face both can one-sidedly have been opened also both sides and open, and during one-sided opening, can finish directional control and anti-cross wind flying; When bilateral symmetry is opened, in the cruising flight stage, can serve as the function of vertical fin, realize that the course increases surely; In the landing stage, can be used for regulating full machine and rise drag characteristic, improve takeoff and landing performance.
Description of drawings
Accompanying drawing 1 merges the full machine birds-eye view of aircraft without the empennage body;
Accompanying drawing 2 merges aircraft one side birds-eye view without the empennage body;
Accompanying drawing 3 combination rudder face partial schematic diagrams;
Accompanying drawing 4 is with the wing profile scheme drawing of combination rudder face;
Accompanying drawing 5 combined rudder deflecting facet scheme drawings;
Accompanying drawing 6 embedded control surface deflection partial enlarged drawings;
The yawing moment of accompanying drawing 7 combination rudder faces and single embedded rudder face relatively;
The rolling moment of accompanying drawing 8 combination rudder faces and single embedded rudder face relatively;
Accompanying drawing 9 combination rudder faces and single embedded rudder face and common the rudder face not pitching moment of open mode compare;
Accompanying drawing 10 common rudder faces are the nowed forming of open mode not;
The nowed forming of accompanying drawing 11 single embedded rudder faces;
The nowed forming of accompanying drawing 12 combination rudder faces;
Accompanying drawing 13 combination rudder faces and single embedded rudder face and common the rudder face not distribution of pressure of open mode compare.Wherein:
1. fuselage axis; 2. combination 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 the embedded rudder face; 9. elevon rotating shaft; 10. wing profile; 11. wing cover; 12. embedded rudder face hinge axis; 13. the yawing moment of single embedded rudder face; 14. the yawing moment of combination rudder face; 15. the rolling moment of single embedded rudder face; 16. the rolling moment of combination rudder face; The pitching moment when 17. common rudder face is not opened; 18. the pitching moment of single embedded rudder face; 19. the pitching moment of combination rudder face; The distribution of pressure when 20. common rudder face is not opened; 21. the distribution of pressure of single embedded rudder face; 22. the distribution of pressure of combination rudder face.
L: merge aircraft half length without the empennage body;
M: combination rudder face outside leading edge;
C: the wing chord length of leading edge m position, the combination rudder face outside;
D1: the outer straight flange of combination rudder face is to the span distance of fuselage axis;
D2: straight flange is to the span distance of fuselage axis in the combination rudder face;
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: the elevon deflection angle;
T: embedded rudder face thickness.
The specific embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
Merge the full machine birds-eye view of aircraft as shown in Figure 1 without the empennage body.The wing of fuselage both sides is furnished with respectively one group of combination rudder face 2, and the described combination rudder face 2 that is positioned on the wing of both sides is symmetrical.Because how much symmetries of full machine and rudder face be also for being arranged symmetrically with, so the present invention only described with a side, as shown in Figure 2.
Embedded rudder face 3 in the described combination rudder face 2 and elevon 4 are in the same exhibition of wing to the 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 the described combination rudder face 2 is apart from the span distance D1=0.83L of fuselage axis 1; The inboard straight flange 8 of the embedded rudder face 3 in the described combination rudder face 2 is apart from the span distance D2=0.63L of fuselage axis 1.The tangential length D3 of embedded rudder face 3 and the tangential length D4 of elevon 4 are respectively 0.3C, and exhibition is respectively 0.2L to length.Space D 5 between the adjacent surface of embedded rudder face 3 and elevon 4 is 0.1C.Described L is aircraft half length, and described C is the wing chord length of combination m position, leading edge place, rudder face 2 outside.
The profile of embedded rudder face 3 and elevon 4 all obtains by the former wing profile 10 of subdivision.
When embedded rudder face 3 the chordwise location on the wing with the exhibition behind location positioning, by the cutting wing cover 11 directly obtain.The thickness t of embedded rudder face is the thickness of wing cover, and described embedded rudder face can be embedded in the wing fully, and can not change former wing profile.The two ends of embedded rudder face 3 leading edges are hinged with the hinge axis 12 that is fixed on the wing, and can be around this hinge axis deflection, and deflection angle is 90 ° to the maximum.
When elevon 4 the chordwise location on the wing with the exhibition behind location positioning, by the cutting wing directly obtain.The leading edge of elevon 4 is circular-arc.
The rotating shaft 9 of elevon 4 is installed in the wing, and the leading edge of elevon 4 is installed in this rotating shaft by bearing, and can do around this rotating shaft ± 30 ° of deflections.When the deflection angle of elevon 4 is 0 °, smooth transition between elevon 4 and the embedded rudder face 3.
In the present embodiment, when carrying out directional control, the embedded rudder face 3 in the combination rudder face 2 will simultaneously deflection with elevon 4.Wherein, on the embedded rudder face 3 partially, elevon 4 times partially, as shown in Figure 5.Embedded rudder face 3 interferes with each other owing to existing between two kinds of rudder faces after consisting of the combination rudder face with elevon 4, changes forming favourable nowed forming, enlarges and separates in eddy zone, increases resistance, thereby produces larger yawing moment, improves directional control efficient.The elevon of combination in the rudder face 24 times will increase wing camber partially, remedy this side because the airfoil lift loss that embedded rudder 3 causes after opening, thereby fundamentally reduce or eliminate the rolling moment that is coupled.In addition, because elevon 4 is positioned at the wing rear portion, loading effect behind its lower wing that partially brings with the generation pitching moment increment of bowing, thereby increases the Longitudinal static stability of quiet unstable tailless aircraft, alleviates simultaneously vertical trim burden.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, in order to finish flat bank, gentle bank, motor-driven, the anti-cross wind flying in horizontal course, improve the multiple-tasks such as takeoff and landing performance.
Utilize the computational fluid mechanics simulation software, verified that combined rudder mask of the present invention has the good aeroperformance of high directional control efficient, 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 2=30 ° of 1=30 ° of embedded control surface deflection angle δ, the elevon deflection angle δ of combination in the rudder face, the yawing moment 14 of the combination rudder face that produces under each angle of attack all is significantly improved than the yawing moment 13 of the embedded rudder face of independent use, increase respectively 30%～70% depending on angle of attack difference, thereby significantly improved directional control efficient.The contrast of Fig. 8 rolling moment shows that then the combination rudder face is when improving directional control efficient, and the rolling moment 15 that the rolling moment 16 of the combination rudder face of its coupling is compared the embedded rudder face of independent use but greatly reduces.When 2=30 ° of 1=30 ° of embedded control surface deflection angle δ, elevon deflection angle δ, this combination rudder face degree of bias configuration has possessed the ability of eliminating the coupling rolling moment fully, can obtain pure course control torque, realized from decoupling zero, rudder face configuration needs when this has just reduced yaw control, thus the rudder face control law simplified.
The contrast of Fig. 9 pitching moment then clearlys show, when using embedded rudder face separately, pitching moment 17 when the pitching moment 18 of single embedded rudder face is not opened than common rudder face has produced the pitching moment increment that comes back, with increasing vertical statical unstability of tailless configuration's aircraft, also increased vertical trim burden.And use when making up rudder face, the pitching moment 19 of combination rudder face has been brought the pitching moment increment of bowing than the pitching moment 18 of single embedded rudder face, is conducive to increase the Longitudinal static stability of tailless aircraft, alleviates simultaneously vertical trim burden.As can be seen from the above analysis, the favourable variation of Fig. 7～Fig. 9 three-axis force square has clearly shown the outstanding advantages of combination rudder face: high directional control efficient, low coupling rolling moment, increase Longitudinal static stability, this is to use separately embedded rudder face to accomplish.
Below in conjunction with the common rudder face of Figure 10 not open mode, the single embedded rudder face of Figure 11, Figure 12 make up nowed forming contrast and the contrast of Figure 13 distribution of pressure under these three kinds of states of rudder face, further disclose the physical mechanism that the combination rudder face produces high directional control efficient, low coupling rolling moment, increases Longitudinal static stability.Can know from Figure 10 and to see that when common rudder face was not opened, the wing upper and lower surface is adhered to mobilely, does not separate.And after opening embedded rudder face, because the wing geometric configuration changes, obvious separated flow has appearred in embedded rudder face rear portion, as shown in figure 11.
Among Figure 13, the distribution of pressure of the distribution of pressure 20 when having provided respectively common rudder face and not opening, the distribution of pressure 21 of single embedded rudder face and combination rudder face.The distribution of pressure of contrast Figure 13 also can be found, because the air-flow in embedded rudder face the place ahead is subject to the unexpected compression of embedded rudder face, flow velocity reduces, pressure raises fast, formed strong adverse pressure gradient, cause the more common rudder face of this zone circular rector not open mode significantly reduce, cause loss of lift.
Also can see from Figure 11, open embedded rudder face after, at the trailing edge place, the inducing action of separate staying the whirlpool will form washes effect on obvious, has further reduced circular rector, has aggravated the loss of lift.As seen, the appearance of close coupling rolling moment causes after mainly embedded rudder face is opened this side airfoil lift loss to cause more greatly, and the close coupling rolling moment is disadvantageous to the turning action of finishing aircraft, or even dangerous.After elevon and embedded rudder face consisted of the combination rudder face, Figure 13 distribution of pressure showed that under combination rudder face configuration, the strong adverse pressure gradient in embedded rudder face the place ahead still exists, and lift still has loss.But, different from the embedded rudder face of independent use is, because elevon has changed wing camber, air-flow is washed effect under having produced significantly, as shown in figure 12 when arriving trailing edge, this is so that the increase of upper surface of the airfoil air-flow velocity, being reflected on Figure 13 distribution of pressure is exactly that the circular rector at embedded rudder face rear portion obviously promotes, and has remedied the loss of lift that embedded rudder face causes, thereby in the generation that has fundamentally prevented large coupling rolling moment.In addition, Figure 13 distribution of pressure also shows, under the elevon partially after, the aerodynamic loading at wing rear portion increases, loading effect after forming, this will bring the pitching moment increment of bowing, and be conducive to increase the Longitudinal static stability of tailless aircraft.The more important thing is, Figure 12 reflects, elevon brings washes effect so that the separation at embedded rudder face rear portion is larger when staying eddy zone than the embedded rudder face of the independent use of Figure 11 down, thereby significantly having increased the resistance that makes up rudder face one side, this also is that combination rudder face of the present invention can obtain larger yawing moment to improve the root place of directional control efficient.
Claims (5)
1. the combination rudder face of a tailless aircraft is characterized in that, comprises 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 are all parallel with the fuselage axis; Two hypotenuses of the parallelogram profile of described embedded rudder face and elevon are all parallel with trailing edge of living in; Embedded rudder face in the described combination rudder face and elevon are in the same exhibition of wing to the 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;
Respectively be furnished with one group of combination rudder face on the wing of fuselage both sides, and the combination rudder face that is positioned on the wing of both sides is symmetrical.
2. the combination rudder face of tailless aircraft as claimed in claim 1 is characterized in that the outside straight flange of the embedded rudder face in the described combination rudder face is apart from the span distance D1=0.83L of fuselage axis; The inboard straight flange of the embedded rudder face in the described combination rudder face is apart from the span distance D2=0.63L of fuselage axis; The tangential length D3 of embedded rudder face and the tangential length D4 of elevon are respectively 0.3C, and exhibition is respectively 0.2L to length; Space D 5 between the adjacent surface of embedded rudder face and elevon is 0.1C; Described L is aircraft half length, and described C is the wing chord length of m position, leading edge place, the combination rudder face outside.
3. 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 that is fixed on the wing, and can be around this hinge axis deflection, and deflection angle is 90 ° to the maximum.
4. the combination rudder face of tailless aircraft as claimed in claim 1 is characterized in that the rotating shaft of described elevon is installed in the wing, and the leading edge of elevon is installed in this rotating shaft by bearing, and can do around this rotating shaft ± 30 ° of deflections.
5. the combination rudder face of tailless aircraft as claimed in claim 4 is characterized in that, when the deflection angle of elevon is 0 °, and smooth transition between elevon and the embedded rudder face.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114357799A (en) * | 2022-01-17 | 2022-04-15 | 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114357799A (en) * | 2022-01-17 | 2022-04-15 | 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 |
| 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 |
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