Google translation
The use of class F22normal distribution is the most secure, but China and Russia are aware of: in the material and the backward situation, the conventional layout is not expected to be able to fight with F22. In 2000, China and Russia in the technology to develop cooperation, but did not reach any agreement of fifth generation fighter. To be sure, in 611 by Song Zong" a small aspect ratio and high lift aircraft aerodynamic layout research" published before, China has been the fifth generation fighter foundation conducted a lot of research, but to use which kind of structure has not been determined.
Today's J-10 pneumatic early many plans more prudent one, followed the j-9program in a large number of existing tunnel information, the more radical double delta wing plan because the risk was too large to give up;" small aspect ratio" in an article strake wing canard layout should be from his unsuccessful the canard double delta wing plan gradually evolved."
Shen also puts forward his own programme, in the competition, Shen Fei601seems to criticize canard defects, clarifies the three wing in the face of trim, motor and lift the benefits. But there are a few problem is unavoidable: three wing in the face of RCS increases than the canard and general layout of complex, for increasing resistance is more unbearable weight of engine. In601, there seems to be a conventional layout as a backup, it is their own uncertainty and the absence of absolute certainty that they lost the heavy machine competition.
In the late 1960's, China in the" lift" layout started the J9 project, China in1960 time begin to hope to be able to lead the world, unconventional" lift" layout that canard has begun a large number of. When J10published in 2005, countless people in it with lion type aircraft articles, but J10really that simple?
601to four wing planform programmes are made model, was tested in a wind tunnel experiment. Mainly consider the swept-wing or delta wing, wing and delta wing leading edge sweep method is adopted to increase the critical Maher number. But if the supersonic flight to Maher number 2, using subsonic swept-wing scheme must make the leading edge sweep angle greater than 60 degrees, but the leading edge sweep angle is too large, and the structure stress will deteriorate, will increase the weight of the structure;
In addition, the low-speed aerodynamic characteristics of space will also worsen, lift, drag increases. The big wing is adverse, and the delta wing is more applicable, not only has the advantages of a swept wing, and relatively long wing chord length to ensure root structure stress condition, reduce the structure weight, but also help to ensure that aircraft longitudinal flight stability. So six zero one was eliminated by the top three programs, and to the edge of the wings swept angle to55 degrees, called j9IV scheme. This is a normal form of delta wing layout scheme, starting appearance except for head to both sides of the inlet, the rest were associated with J7, J8, similar to the super 7early type, is also j7CP.
The J9 project, focus on the requirements of supersonic, both good subsonic performance, front canard design is far from mature, not to mention the differential, but still failed, only the layout is statically unstable, is still serious over China and the world at the time of pneumatic control level. The9project, in 1970 time end was abandoned, but it after repeatedly modified,601 for canard has laid the foundation!
If J20, then it can only talk about canard wing, from the overall. This? What about it?
"Solving the trim is another pathway of the thrust vector control ( TVC ) technology. Using TVC, its main advantages are: in the aerodynamic control surfaces were added based on a matching tie
Segment, balancing ability nature greatly enhanced; high-speed aerodynamic flight control surface deflection will produce great resistance, and the TVC can play the same control effect without deflected control surfaces;
TVC is not deflected thrust vector and generates a normal force, powerful engine jet in the rear fuselage to form a jet action, to create a new " lift" increment, while participating in trim
. F-22supersonic maneuverability greatly improved, TVC technical merit
In 1997 611completed the" thrust vector control on the aircraft's stability and controllability of the influence of" using the J-10kinetic model was fit for axisymmetric vectoring thrust nozzle simulation
Research; according to the paper, a canard and thrust vector combination can in post-stall area effective expansion of flight envelope, to get good control and stability of. Be careful
Described in the paper, a noun, the so-called" lateral-directional control system", probably refers to control canard differential system.
From this thesis can be seen, the canard configuration and thrust vector integration research,611 in at least12 years before the start of the. The four generation of the thrust vector integration development although there may not be any work
The history experience, theoretical preparation should be fully."
Similar to the F22diamond head first is a must.
F22diamond head has two effects: first, the stealth irregular radar scattering, this everybody knows, on the other hand is also important: diamond head open air, head sides slope
The air compression effect. That is to say, it is a vortex generator.
Four generation machine from SU27, F16began to have the strake vortex air generator, F18big brother special strake vortex air generator is very beautiful, of course, a canard front canard vortex generator
More effective than the conventional layout, it is said. The F22 is the first to create a production aircraft nose vortices, F22 added 2vortex generator vortex, it is head, small strake vortex as auxiliary
.
As the lifting body and stealth design, almost square accounts in every detail of the J20, diamond head is indispensable, flight control of the complex appears to still solve problem, but fortunately,
But song old in his papers appearing in a worried: as the main vortex generator, the canard vortex will not receive head vortex interference?
It also seems to be a thorny problem. In T50, head of vorticity and similar false duck wing movable strake also seem to have this problem.
According to a number of public information, seems to be validated, this problem is not solved, can be used to control, but it still affected J20 and T50 design. But for J20, it
A good, a bad. Benefits are: coupling trim and vortex lift problem solving and a consideration, harm would immediately said, but also cannot say is a weakness.
Seem to will head vortex on the canard and leading-edge strake effects to a minimum, J20and T50 seem to have adopted for canard and leading-edge strake away from the head of the design. T50 nose from
The wing so far is not without reason.
T50 also uses a multiple vortex generators, but its movable strake is more conventional layout for the compensation of the concessions, strictly speaking, T50is double cavity between the lift
Body is conservative, and combined with the stealth F22, J20 integral lifting body can be said to be almost two times, and J20combined with the overall stealth fusion of multiple vortex generator is integral lifting body
One fighter only.
J20coupling can be said to be from the coupling, but actually, the real wing from the front wing has a considerable distance, large area of the front wing to ensure balancing role, as well as the vortex lift, but if
The main wing really left front wing, the vortex lift it or lose a lot of weight, J20actual away from the front canard wing trim, ensure the absolute strong, supersonic motor performance is very outstanding, but
Is subsonic and lifting body weakened do!
The typhoon will use small almost invisible pneumatic generator retaining a vortex generator, amplifying the wing area, but the J20solution is allergic to the pole, wing area on the
Large! Article edge increases one main vortex generator! This seems to be similar to typhoon false distance coupling world the one and only!
So J20's main vortex generator has been increased to three, the nose vortices, canard vortex vortex, wing, while the strake vortex will serve as an important auxiliary pneumatic measure, used for duck wing
, wing and Fuselage Aerodynamic integration design modification and vortex flow improvement and upgrading!
Two years ago, the closest concept may appear wing cutting edge extending out a sharp narrow edge, duck wing housed in edge design. But we have not thought of, J20
The importance of the strake vortex is beyond imagination. It almost can be counted as a separate main vortex generator!
Just to meet the stealthy airframe design, enough to let Americans proud, J20stealth unconventional multiple vortex generators of integral lifting body, its aerodynamic design need much effort
, flight control system need to be complicated!?
Strake vortex lift increase, and away from the center of gravity balancing ability can achieve large canard vortex lift and balancing ability of the dual strong, not only so, their design
Blended wing body combination of stealth requirements, presenting a planar integral lifting body effect! This benefit is the world knows, but apart from the early 1990's American actual verification
Have no practical use outside! In the J20thrust vector, balancing capacity will be increased further!
Can say, J20technique either canard, strake, DSi inlet are J10, FC1 as the technical accumulation, can say, J20technology does not exceed the world existing technology fan
Wai, but put them together, need to be extremely strong foundation, J20was the first to put into practice.
Another the body length of the reasons are complex, J20more than F22stressed area rate reduce, reduce the resistance," stealth bye" is nonsense, but compared with short thick F22, J20 more fine
Multiple, and the S shaped inlet is undoubtedly in the rear fuselage torsion, it is occupying valuable space, in order to give the internal weapons lattice cabin space, J20body length is no doubt. While T50by
On the two costal engine only slightly turned downwards, the intermediate space, so do not so long, cost is the stealth bad!
F22 stubby, is due to abnormal engine, J20a little longer, due to duck layout and stealth, super cruise to balance the needs of.
In addition, J20canard wing still uses J10ideas, using spanwise along the variable camber of large area is lift design, with obvious anhedral angle; the design of pneumatic and flight control design
The difficulty of cost, risk, income, obtain high lift aerodynamic control surfaces to good control effect. But the drawback is that the stealth ability does not appear to be arranged in parallel, in fact, a parallel arrangement of fly
Control is more demanding, and the eddy current complex worse, may fly after calculation, and without the use of such seemingly advanced layout, although there will be some signal scattering, but not good
To deal with the problem. The problem lies mainly in duck wing and body between joints and the rotating shaft. J20 uses a small strip protrusion block joint practice, it can reduce the RCS, but seems to have brought
A small control surfaces. J20designers to so much control surface, courage and skills terrible!
The main wing, J20 is designed in the regulation distance, using a large swept trapezoidal wing approach, similar to the French Rafale as concise and lively, taking into account and fuselage is not parallel to the lower RCS signal reflection
, to ensure the relatively small area with numerous vortex lift on supersonic and subsonic effect. Many people wish to consider W wing, but it seems like science fiction, but there are many disadvantages:
The 1processing complex, cost increase, while the strength of the defective.
2 W wing itself will have some radar wave reflectivity. While large swept trapezoidal wing appear to be simple, in fact, restrained the stealth effect is absolutely good.
3W wing to enhance strength, will inevitably result in weight lifting. However, it will move along the length of the fuselage, resulting in increased, and if the stretched back out, sharp edge during takeoff
A clean landing risk.
Differential duck wing, canard is few, and the importance, little is known about.
J20hood vents are serrated design, it is invisible, but many pictures show, vents are one large and one small change, to be sure, in the J20 thrust vector before, engine thrust and torque experiment has begun. While the V tail relaxed fighter yaw stability appears to be for this match!
It also seems to be a thorny problem. In T50, head of vorticity and similar false duck wing movable strake also seem to have this problem.
According to a number of public information, seems to be validated, this problem is not solved, can be used to control, but it still affected J20 and T50 design. But for J20, it
A good, a bad. Benefits are: coupling trim and vortex lift problem solving and a consideration, harm would immediately said, but also cannot say is a weakness.
Seem to will head vortex on the canard and leading-edge strake effects to a minimum, J20and T50 seem to have adopted for canard and leading-edge strake away from the head of the design. T50 nose from
The wing so far is not without reason.
T50 also uses a multiple vortex generators, but its movable strake is more conventional layout for the compensation of the concessions, strictly speaking, T50is double cavity between the lift
Body is conservative, and combined with the stealth F22, J20 integral lifting body can be said to be almost two times, and J20combined with the overall stealth fusion of multiple vortex generator is integral lifting body
One fighter only.
J20coupling can be said to be from the coupling, but actually, the real wing from the front wing has a considerable distance, large area of the front wing to ensure balancing role, as well as the vortex lift, but if
The main wing really left front wing, the vortex lift it or lose a lot of weight, J20actual away from the front canard wing trim, ensure the absolute strong, supersonic motor performance is very outstanding, but
Is subsonic and lifting body weakened do!
The typhoon will use small almost invisible pneumatic generator retaining a vortex generator, amplifying the wing area, but the J20solution is allergic to the pole, wing area on the
Large! Article edge increases one main vortex generator! This seems to be similar to typhoon false distance coupling world the one and only!
So J20's main vortex generator has been increased to three, the nose vortices, canard vortex vortex, wing, while the strake vortex will serve as an important auxiliary pneumatic measure, used for duck wing
, wing and Fuselage Aerodynamic integration design modification and vortex flow improvement and upgrading!
Two years ago, the closest concept may appear wing cutting edge extending out a sharp narrow edge, duck wing housed in edge design. But we have not thought of, J20
The importance of the strake vortex is beyond imagination. It almost can be counted as a separate main vortex generator!
Just to meet the stealthy airframe design, enough to let Americans proud, J20stealth unconventional multiple vortex generators of integral lifting body, its aerodynamic design need much effort
, flight control system need to be complicated!?
Strake vortex lift increase, and away from the center of gravity balancing ability can achieve large canard vortex lift and balancing ability of the dual strong, not only so, their design
Blended wing body combination of stealth requirements, presenting a planar integral lifting body effect! This benefit is the world knows, but apart from the early 1990's American actual verification
Have no practical use outside! In the J20thrust vector, balancing capacity will be increased further!
Can say, J20technique either canard, strake, DSi inlet are J10, FC1 as the technical accumulation, can say, J20technology does not exceed the world existing technology fan
Wai, but put them together, need to be extremely strong foundation, J20was the first to put into practice.
Another the body length of the reasons are complex, J20more than F22stressed area rate reduce, reduce the resistance," stealth bye" is nonsense, but compared with short thick F22, J20 more fine
Multiple, and the S shaped inlet is undoubtedly in the rear fuselage torsion, it is occupying valuable space, in order to give the internal weapons lattice cabin space, J20body length is no doubt. While T50by
On the two costal engine only slightly turned downwards, the intermediate space, so do not so long, cost is the stealth bad!
F22 stubby, is due to abnormal engine, J20a little longer, due to duck layout and stealth, super cruise to balance the needs of.
In addition, J20canard wing still uses J10ideas, using spanwise along the variable camber of large area is lift design, with obvious anhedral angle; the design of pneumatic and flight control design
The difficulty of cost, risk, income, obtain high lift aerodynamic control surfaces to good control effect. But the drawback is that the stealth ability does not appear to be arranged in parallel, in fact, a parallel arrangement of fly
Control is more demanding, and the eddy current complex worse, may fly after calculation, and without the use of such seemingly advanced layout, although there will be some signal scattering, but not good
To deal with the problem. The problem lies mainly in duck wing and body between joints and the rotating shaft. J20 uses a small strip protrusion block joint practice, it can reduce the RCS, but seems to have brought
A small control surfaces. J20designers to so much control surface, courage and skills terrible!
The main wing, J20 is designed in the regulation distance, using a large swept trapezoidal wing approach, similar to the French Rafale as concise and lively, taking into account and fuselage is not parallel to the lower RCS signal reflection
, to ensure the relatively small area with numerous vortex lift on supersonic and subsonic effect. Many people wish to consider W wing, but it seems like science fiction, but there are many disadvantages:
The 1processing complex, cost increase, while the strength of the defective.
2 W wing itself will have some radar wave reflectivity. While large swept trapezoidal wing appear to be simple, in fact, restrained the stealth effect is absolutely good.
3W wing to enhance strength, will inevitably result in weight lifting. However, it will move along the length of the fuselage, resulting in increased, and if the stretched back out, sharp edge during takeoff
A clean landing risk.
Differential duck wing, canard is few, and the importance, little is known about.
J20hood vents are serrated design, it is invisible, but many pictures show, vents are one large and one small change, to be sure, in the J20 thrust vector before, engine thrust and torque experiment has begun. While the V tail relaxed fighter yaw stability appears to be for this match!
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Lateral movement, slip, J20 does not use ready-made similar to F22 as the traditional aerodynamic layout, instead of using the canard aerodynamic layout, is in pursuit of high mobility.
long fuselage design is intended to be useful for high-speed flight, it is in order to make up for the inadequate level of engine technology, with the development of high performance vector engine development, combine the two, mobility increases, but increases the complexity of flight control, flight control programming can produce more complex flight action.J20 flight control programming need the best programming staff，Write the best flight control procedures, can fully play its mobility potential, in theory it can do almost anything can think of complex movements, if equipped with vector engine , human physiological limit
