CN109703743A - A kind of jet flow rudder face of blended wing-body airplane - Google Patents
A kind of jet flow rudder face of blended wing-body airplane Download PDFInfo
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- CN109703743A CN109703743A CN201811592697.0A CN201811592697A CN109703743A CN 109703743 A CN109703743 A CN 109703743A CN 201811592697 A CN201811592697 A CN 201811592697A CN 109703743 A CN109703743 A CN 109703743A
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Abstract
A kind of jet flow rudder face of blended wing-body airplane, rudder face are located at After-Body, carry out folding and unfolding by driving mechanism and significantly improve nose-up pitching moment when takeoff and landing to be coupled with the jet cutting car flow in front of it.The present invention is laid out tail portion rudder face relative to traditional blended wing-body, has higher rudder effectiveness, can dramatically increase available nose-up pitching moment.Simultaneously as the arm of force is longer, required nose-up pitching moment can be reached with lesser loss of lift, it is generally smaller to the adverse effect of takeoff and landing performance.The driving mechanism design that body can be taken in will not have an impact cruise performance.
Description
Technical field
It is specifically a kind of positioned at After-Body the present invention relates to the design of blended wing-body airplane fore-and-aft control rudder face
Jet flow rudder face.
Background technique
Blended wing-body airplane eliminates the primary control surfaces such as horizontal tail compared to normal arrangement, flat due to using
The design of lift body, smoothly transit between fuselage and wing, so that the whole area that soaks greatly reduces, resistance is reduced, gas
Efficiency of movement is obviously improved, and is one of the research hotspot of future aircraft distribution form.
One of the significant challenge of blended wing-body airplane design is that it cancels the longitudinally controlled ability of horizontal tail bring not
When the problem, especially low speed landing of foot, the trim pressure of nose-down pitching moment is larger, is often accompanied by biggish loss of lift.The cloth
The primary control surface of office is often arranged in wing and body rear, and the rudder face of trailing edge is located proximate to center of gravity, and control arm is short, rudder
Face efficiency is lower, although the rudder face arm of force of body rear is longer, the torque total amount that can be provided is relatively limited.In low speed landing
Under state, to generate enough nose-up pitching moments, often flight path can be caused to change with biggish loss of lift, or even occur
" sudden sinking " phenomenon, more stringent requirements are proposed for this design to high lift device, in turn, the high lift device of high-lift
But also the demand of nose-up pitching moment is bigger.Searching can minimize trim loss of lift and meet the longitudinally controlled of torque demand
Means are not only able to reduce landing head, enhance landing safety, additionally it is possible to which the design pressure for reducing high lift device is conducive to
The advantage of BWB layout is excavated to the maximum extent.
Nose-up pitching moment is insufficient when for blended wing-body airplane low speed landing, the larger problem of loss of lift, both at home and abroad
It also proposed some new control means, such as: abdomen spoiler (Staelens, Y.D., Blackwelder, R.F., Page,
M.A.,Novel pitch control effectors for a blended wing body airplanes in
takeoff and landing configuration.45th AIAA Aerospace Sciences Meeting And
Exhibit,2007,Reno,Nevada)；Vertical fin stabilizes rudder face (Aircraft with vertical stabilizers
arranged on a central fuselage body and method,as well as control unit,for
compensating a negative pitching moment.PatentNo.:US8496203B2)；Canard (Nasir,
R.M.,Kuntjoro,W.,Wisnoe,W.,Longitudinal Static Stability of a Blended-Wing-
Body Unmanned Aircraft with Canard as Longitudinal Control Surface,J.Journal
Of Mechanical Engineering.2012,9 (1), pp.99-121.) etc..Although above-mentioned control means are to promotion landing
When nose-up pitching moment have certain help, but there is also problems: abdomen spoiler is a kind of rudder for being arranged in body lower surface
Face, by increasing the lift in front of body center of gravity, the lift after center of gravity reduces, and whole lift promotes full machine while increase
Nose-up pitching moment, meeting under working condition proposes high requirement to motor power, together so that full machine resistance is obviously increased
When available torque it is also relatively limited, need to combine with other rudder faces to meet the demand for control of aircraft；Vertical fin stabilizes rudder
Face is arranged in both ends vertical fin top, nose-up pitching moment is provided under conditions of not influencing lift by its symmetric deflection, and will not draw
Enter additional yawing, but its nose-up pitching moment that can be provided is positively correlated with augmented resistance, big nose-up pitching moment is also brought along
Big resistance cost；Canard is arranged in front of wing, is played the role of similar horizontal tail, can be provided while promoting lift
Nose-up pitching moment, but simultaneously, the cruise drag of full machine is increased, the static stability of full machine, especially blended wing-body is degrading and is laid out
Static margin itself is not high even quiet unstable.Therefore, new line when acquisition can meet low speed landing with smaller cost
The longitudinally controlled means of torque demand have a very important significance.
Summary of the invention
Use low speed landing nose-up pitching moment existing for the blended wing-body airplane of back up formula engine insufficient to overcome, often
The problem of with larger loss of lift, the invention proposes a kind of jet flow rudder faces of blended wing-body airplane.
The jet flow rudder face is located at blended wing-body layout body rear upper surface, in the arc-shaped sliding rail of driving lower edge of push rod
Carry out the folding and unfolding that rudder face is realized in sliding.Floor projection under the jet flow rudder face collapsed state is symmetrical about the body plane of symmetry, by
Four edges line surrounds.The sideline at the jet flow rudder face rear portion is camber line, and is overlapped with body rear.Jet flow rudder face two sides are straight
The length L1=0.1L, the L on side are that body opens up the floor projection length to outermost side end face, the exhibition of the jet flow rudder face
It is identical as the span-wise length of body to length D1.
The jet flow rudder face is symmetrical airfoil, the leading edge of the section in its shape for opening up any tangential section into range
For circular arc BAD, leading-edge radius is 0.1 times of the section aerofoil profile chord length；The top airfoil BC of the section is overlapped with body type face,
The top airfoil BC is cambered surface.The lower aerofoil DC of the section and the top airfoil BC are symmetrical.Determine the jet flow rudder face shape and
After size, jet flow rudder face is obtained by cutting from body tail portion.The jet flow rudder face of acquisition is connect with driving mechanism.
Front sideline of the jet flow rudder face close to engine and two sides about the symmetrical two sides of the body plane of symmetry
Line is straight flange, and two sidelines of two sides are parallel to each other.
The arc length of the arc-shaped sliding rail is 1.5 L1, and radius is 1.8 L1.L1 is the length of jet flow rudder face two sides straight flange
Degree.
The jet flow rudder face is obtained by cutting from body tail portion.In the both side surface of the jet flow rudder face at rear point
It does not process fluted, and is located at the groove within the scope of the chord length of the side 45% to 85%；Cunning is installed in the groove
Wheel group.
When the jet flow rudder face is connect with driving mechanism, two push rod one end in driving mechanism respectively with the jet flow
The up-front both ends of rudder face are hinged.Two arc-shaped sliding rails in the driving mechanism be respectively embedded into each groove and with it is described
Pulley blocks cooperation, hydraulic actuator drive jet flow rudder face to be slided along the arc-shaped sliding rail, realize rudder face by push rod
Folding and unfolding.
Back amount L2 under the jet flow rudder face opening state is up to 0.8L1, and the amount of moving up H2 is up to engine support
The 1/2 of height, inclined 30 degree in deflection angle A1 maximum.
In the present invention, jet flow rudder face is obtained by cutting body.Its back amount L2 is up under jet flow rudder face opening state
0.75L1, the amount of moving up H2 are up to the half of engine support height, and deflection angle A1 is up to inclined 30o.
Jet flow rudder face carries out folding and unfolding by driving mechanism, and the driving mechanism includes following major part: push rod, circular arc
Shape sliding rail, shaft, hydraulic actuator, sled drive mechanism.In addition to shaft, above-mentioned each component respectively have in rudder face two sides it is a set of, it is right
Claim arrangement.In each component, shaft is fixed on internal body, and hydraulic actuator is coupled, and can be rotated around it.Push rod
One end and jet flow rudder face are hinged, and jet flow rudder face can be driven to be slided along arc-shaped sliding rail under the action of hydraulic actuator,
Sled drive mechanism is fixed in body, for realizing the folding and unfolding of arc-shaped sliding rail.
Under jet flow rudder face collapsed state, driving mechanism is located at internal body, and under landing state, sled drive mechanism is first
Arc-shaped sliding rail is stretched out outside body, hydraulic actuator drives pushrod movement, then pushes the jet flow rudder face being hinged with push rod
It slides into corresponding position along arc-shaped sliding rail to work, into after state of flight, jet flow rudder face is packed up, sled drive mechanism
Arc-shaped sliding rail is taken in body again.
Compared with prior art, the present invention has effect following prominent:
1. improving the control efficiency of body tail portion rudder face.Existing blended wing-body airplane body tail portion is frequently with such as
Simple rudder face 1 shown in FIG. 1 can carry out yaw motion up and down.It is the longitudinally controlled efficiency highest of full machine since its arm of force is longer
Rudder face.The present invention further excavates the long advantage of the body tail portion rudder face arm of force, makes it have the form of similar Fowler flap,
Generate jet flow rudder face 2 as shown in Figure 2.Increase the negative camber of After-Body and rudder face torque arm length in the retrogressing of rudder face partially,
The control efficiency of rudder face is promoted while enhancing nose-up pitching moment.
2. improving the available drift angle of rudder face.Simple rudder face 1 shown in FIG. 1 is in the case of big upper drift angle, rudder face rear portion
It is easy to happen flow separation, limits the control ability of rudder face.Jet flow rudder face 2 can be flowed by the seam below rudder face to be increased
Boundary-layer energy postpones flow separation, improves the available drift angle of rudder face.Fig. 3 is the table under simple rudder face 1 drift angle situation upper greatly
Face nowed forming, it is seen that below rudder face, streamline helically form, there are apparent flow separations.Fig. 4 is identical size phase
With the nowed forming of the jet flow rudder face 2 under drift angle, in jet flow rudder face lower aerofoil, streamline is in straight state, keeps good attachment stream
It is dynamic.Therefore, jet flow rudder face has bigger available drift angle.
3. realizing the coupling of jet cutting car flow and rudder face, nose-up pitching moment is dramatically increased.Body tail portion rudder as shown in Figure 1
Face is difficult to efficiently use it since there are certain distances with jet cutting car flow under big upper drift angle situation.This
Jet flow rudder face in invention can move up and upward deflect, and jet cutting car flow be significantly affected to it, on it
Aerofoil forms higher-pressure region, increases the pressure difference of rudder face upper and lower surface, effectively offer nose-up pitching moment.Fig. 5 compared simple rudder face and receive
Pitching moment curve 3 under the state of rising, pitching moment curve 4 and jet flow rudder face opening state under simple rudder face opening state
Under pitching moment curve 5.Nose-up pitching moment more significant than simple rudder face can be brought under jet flow rudder face opening state, provided
Nose-up pitching moment amount be approximately that simple rudder face can be provided nose-up pitching moment amount 2 times.Fig. 6 compared under simple rudder face opening state
Pressure distribution 6, the pressure of rudder face under the pressure of jet flow rudder face opening state lower body distribution 7 and jet flow rudder face opening state
Distribution 8.It is worth noting that under jet flow rudder face opening state rudder face pressure distribution 8, due to jet cutting car flow bring it is huge
Upper and lower surface pressure difference makes rudder face produce significant negative lift.Along with the longer arm of force of rudder face, which is brought
A large amount of nose-up pitching moment, this is jet flow rudder face the root of more nose-up pitching moments can be more efficiently provided than simple rudder face where.
4. jetevon is smaller in face of the adverse effect of takeoff and landing performance, and will not have an impact to cruise performance.Rudder face is mentioning
It usually can be especially not high to blended wing-body positioning efficiency along with the reduction of lift and the increase of resistance when for nose-up pitching moment
Rudder face for, this problem is more prominent.Fig. 7 compared the lift curve 9 under simple rudder face collapsed state, simple rudder face
The lift curve 11 under lift curve 10 and jet flow rudder face opening state under opening state.As it can be seen that jet flow rudder face opening state
It is lower to bring the loss of lift bigger than simple rudder face, but increased loss amount very little, about 20%.Fig. 8 compared simple rudder
Resistance curve 12 under the collapsed state of face, under the resistance curve 13 and jet flow rudder face opening state under simple rudder face opening state
Resistance curve 14.The resistance bigger than simple rudder face can be brought under jet flow rudder face opening state, this is advantageous landing,
To take off be it is unfavorable, landing state more pays close attention to the aeroperformance variation of High Angle of Attack, in figure, with the increase of the angle of attack, increases
Amount of resistance constantly reducing, increased amount of resistance is in lesser magnitude under High Angle of Attack takeoff condition.In general, consider
Will certainly reduce to jet flow rudder face much stronger than the control ability of simple rudder face inefficient trailing edge rudder face with concora crush
Power, generally liter drag losses caused by trim will certainly reduce.Simultaneously as jet flow rudder face can be obtained by cutting body,
Rudder face is recoverable to home position under off working state, and driving mechanism is hidden in internal body, when can't bring cruise
Aeroperformance loss.
Detailed description of the invention
Fig. 1 is the simple rudder face that existing blended wing-body airplane generallys use；
Fig. 2 is the jet flow rudder face of blended wing-body airplane proposed by the present invention；
Fig. 3 is surface flow form of the simple rudder face under big upper drift angle situation；
Fig. 4 is surface flow form of the jet flow rudder face under big upper drift angle situation；
Fig. 5 is simple rudder face collapsed state, simple rudder face opening state, the pitching moment under jet flow rudder face opening state
Property comparison.
Fig. 6 is simple rudder face opening state, the pressure profiles versus under jet flow rudder face opening state.
Fig. 7 is simple rudder face collapsed state, simple rudder face opening state, the lift efficiency under jet flow rudder face opening state
Compare；
Fig. 8 is simple rudder face collapsed state, simple rudder face opening state, the drag characteristic under jet flow rudder face opening state
Compare；
Fig. 9 is the structural schematic diagram of jet flow rudder face；
Figure 10 is the full machine top view under jet flow rudder face collapsed state；
Figure 11 is the tangential section shape schematic diagram of jet flow rudder face；
Figure 12 is jet flow rudder face driving mechanism schematic diagram；
Figure 13 is jet flow rudder face and its driving mechanism side view.
In figure:
1. simple rudder face；2. jet flow rudder face；3. the pitching moment curve under simple rudder face collapsed state；4. simple rudder face
Pitching moment curve under opening state；5. the pitching moment curve under jet flow rudder face opening state；6. simple rudder face open shape
Pressure distribution under state；7. the pressure of jet flow rudder face opening state lower body is distributed；8. rudder face under jet flow rudder face opening state
Pressure distribution；9. the lift curve under simple rudder face collapsed state；10. the lift curve under simple rudder face opening state；11.
Lift curve under jet flow rudder face opening state；12. the resistance curve under simple rudder face collapsed state；13. simple rudder face is opened
Resistance curve under state；14. the resistance curve under jet flow rudder face opening state；15. the body plane of symmetry；16. body；17. machine
Body is opened up to outermost side end face；18. engine；19. engine support；20. push rod；21. arc-shaped sliding rail；22. support；23. turn
Axis；24. hydraulic actuator；25. sled drive mechanism；26. pulley blocks；27. arc-shaped sliding rail end end plate.
L: body is opened up to outermost side end face extent of horizontal projection degree；
L1: the length of jet flow rudder face floor projection two sides straight flange；
L2: jet flow rudder face back amount；
H2: the jet flow rudder face amount of moving up；
A1: jet flow control surface deflection angle.
Specific embodiment
As shown in figure 9, jet flow rudder face 2 provided by the invention is located at blended wing-body layout body rear upper surface, in push rod
The arc-shaped sliding rail 21 of 20 driving lower edge carries out the folding and unfolding that rudder face is realized in sliding.
Floor projection under 2 collapsed state of jet flow rudder face is symmetrical about the body plane of symmetry 15, is surrounded by four edges line,
As shown in the shadow region Figure 10, wherein close to the front sideline of engine 17 and about the symmetrical two sides of the body plane of symmetry 15
Two sidelines be straight flange, and two sidelines of two sides are parallel to each other.The sideline at the jet flow rudder face rear portion is camber line, and with
Body rear is overlapped.The length L1=0.1L, the L of jet flow rudder face two sides straight flange are that body is opened up to outermost side end face
The span-wise length D1 of 17 floor projection length, the jet flow rudder face 2 is identical as the span-wise length of body 16.
The jet flow rudder face 2 is symmetrical airfoil in its shape for opening up any tangential section into range, takes body symmetrical
Tangential section at face 15 carries out relevant feature description, and other positions are identical with this, as shown in figure 11.The leading edge of the section
For circular arc BAD, leading-edge radius is 0.1 times of the section aerofoil profile chord length；The top airfoil BC of the section is overlapped with body type face,
The top airfoil BC is cambered surface.The lower aerofoil DC of the section and the top airfoil BC are symmetrical.
After the shape and size for determining the jet flow rudder face, jet flow rudder face is obtained by cutting from body tail portion.
The both side surface of the jet flow rudder face at rear is processed fluted respectively, and the groove is made to be located at the side
Within the scope of 45% to 85% chord length；Pulley blocks 26 are installed in the groove.
The jet flow rudder face 2 of acquisition is connect with driving mechanism.Specifically: by two push rods 20 in the driving mechanism
One end is hinged with the up-front both ends of the jet flow rudder face 2 respectively.Two arc-shaped sliding rails 21 in the driving mechanism are respectively embedded into
Cooperate in each groove and with the pulley blocks 26, hydraulic actuator 24 drives jet flow rudder face 2 along the circle by push rod 20
Arc-shaped slide rail 21 is slided, and realizes the folding and unfolding of rudder face.Back amount L2 under 2 opening state of jet flow rudder face is up to
0.8L1, the amount of moving up H2 are up to the 1/2 of 19 height of engine support, and deflection angle A1 is up to inclined 30 degree.
As shown in Figure 12,13, the driving mechanism includes two push rod 20, two arc-shaped sliding rails, 21, two hydraulic works
Dynamic 24, two sled drive mechanisms 25 of cylinder and support 22 and shaft 23.The shaft 23 is located in body, and erection support
On 22；The support is located in body and is fixed on the machine body on surface.It is separately installed on the end of the both ends of the shaft hydraulic
Pressurized strut 24.One end of two push rods 20 is hinged with the piston rod in hydraulic actuator respectively, the other end respectively with the jet flow
Rudder face leading edge is hinged, and under the action of hydraulic actuator 24, and jet flow rudder face 2 is driven to be slided along arc-shaped sliding rail 21, real
The folding and unfolding of existing rudder face.
One end of the arc-shaped sliding rail 21 is fitted into the sled drive mechanism 25 of internal body, and the other end passes through jetevon
Face 2, and jet flow rudder face surface shape is made by the end plate when jet flow rudder face moves to opening state equipped with end plate 27 in end
At complete smooth surface, as shown in figure 13.The arc length of the arc-shaped sliding rail 21 is 1.5 L1, and radius is 1.8 L1.L1 is
The length of jet flow rudder face two sides straight flange.
In the present embodiment, under 2 collapsed state of jet flow rudder face, driving mechanism is located at internal body, and sliding rail end
End plate 27 is concordant with the upper surface of jet flow rudder face 2, guarantees that rudder face upper surface forms complete smooth curved surface；It is sliding under landing state
Rail driving mechanism 25 first stretches out arc-shaped sliding rail 21 outside body under the action of motor internal, and hydraulic actuator 24 drives
Push rod 20 moves, and then pushes the jet flow rudder face 2 being hinged with push rod to slide into corresponding position along arc-shaped sliding rail 21 and carries out work
Make, into after state of flight, jet flow rudder face 2 is retracted to home position by push rod 20, and sled drive mechanism 22 is again by arc-shaped cunning
Rail 21 withdraws body, until sliding rail end end plate 27 is concordant with jet flow rudder face upper surface.
Claims (7)
1. a kind of jet flow rudder face of blended wing-body airplane, which is characterized in that jet flow rudder face is located at blended wing-body layout body
Rear upper surface carries out the folding and unfolding that rudder face is realized in sliding in the arc-shaped sliding rail of driving lower edge of push rod；The jet flow rudder face is packed up
Floor projection under state is symmetrical about the body plane of symmetry, is surrounded by four edges line；The sideline at the jet flow rudder face rear portion is camber line,
And it is overlapped with body rear；The length L1=0.1L, the L of jet flow rudder face two sides straight flange are that body is opened up to outermost side
The span-wise length D1 of the floor projection length in face, the jet flow rudder face is identical as the span-wise length of body；
The jet flow rudder face is symmetrical airfoil in its shape for opening up any tangential section into range, and the leading edge of the section is circle
Arc BAD, leading-edge radius are 0.1 times of the section aerofoil profile chord length；The top airfoil BC of the section is overlapped with body type face, it is described on
Aerofoil BC is cambered surface；The lower aerofoil DC of the section and the top airfoil BC are symmetrical；After the shape and size for determining the jet flow rudder face,
Jet flow rudder face is obtained by cutting from body tail portion；The jet flow rudder face of acquisition is connect with driving mechanism.
2. the jet flow rudder face of blended wing-body airplane as described in claim 1, which is characterized in that the jet flow rudder face is close to hair
The front sideline of motivation and two sidelines about the symmetrical two sides of the body plane of symmetry are straight flange, and two sidelines of two sides
It is parallel to each other.
3. the jet flow rudder face of blended wing-body airplane as described in claim 1, which is characterized in that determine the shape of the jet flow rudder face
After shape and size, jet flow rudder face is obtained by cutting from body tail portion.
4. the jet flow rudder face of blended wing-body airplane as described in claim 1, which is characterized in that the jet flow rudder face is close to rear
The both side surface at place is processed fluted respectively, and is located at the groove within the scope of the chord length of the side 45% to 85%；At this
Pulley blocks are installed in groove.
5. the jet flow rudder face of blended wing-body airplane as described in claim 1, which is characterized in that by the jet flow rudder face and drive
When motivation structure connects, two push rod one end in driving mechanism are hinged with the up-front both ends in jetevon face respectively；The driving
Two arc-shaped sliding rails in mechanism are respectively embedded into each groove and cooperate with the pulley blocks, and hydraulic actuator is by pushing away
Bar drives jet flow rudder face to be slided along the arc-shaped sliding rail, realizes the folding and unfolding of rudder face.
6. the jet flow rudder face of blended wing-body airplane as described in claim 1, which is characterized in that the jet flow rudder face open shape
Back amount L2 under state is up to 0.8L1, and the amount of moving up H2 is up to the 1/2 of engine support height, in deflection angle A1 maximum
Inclined 30 degree.
7. the jet flow rudder face of blended wing-body airplane as described in claim 1, which is characterized in that the arc of the arc-shaped sliding rail
A length of 1.5 L1, radius are 1.8 L1；L1 is the length of jet flow rudder face two sides straight flange.
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| CN111516854A (en) * | 2020-04-03 | 2020-08-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Flow control component for promoting jet flow deflection |
| CN112722241A (en) * | 2021-02-02 | 2021-04-30 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN115307861A (en) * | 2022-10-10 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Flight verification method and flight verification model for torque control performance of jet control surface |
| CN115892439A (en) * | 2023-03-10 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | High-wind-resistance distributed propulsion aircraft |
| WO2023109154A1 (en) * | 2021-12-15 | 2023-06-22 | 北京航空航天大学宁波创新研究院 | Wing and method for improving control efficiency of two-dimensional airfoil rudder surface |
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| CN111516854A (en) * | 2020-04-03 | 2020-08-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Flow control component for promoting jet flow deflection |
| CN111516854B (en) * | 2020-04-03 | 2021-08-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Flow control component for promoting jet flow deflection |
| CN112722241A (en) * | 2021-02-02 | 2021-04-30 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN112722241B (en) * | 2021-02-02 | 2024-04-12 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| WO2023109154A1 (en) * | 2021-12-15 | 2023-06-22 | 北京航空航天大学宁波创新研究院 | Wing and method for improving control efficiency of two-dimensional airfoil rudder surface |
| CN115307861A (en) * | 2022-10-10 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Flight verification method and flight verification model for torque control performance of jet control surface |
| CN115892439A (en) * | 2023-03-10 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | High-wind-resistance distributed propulsion aircraft |
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