CN102837822A - Working principle of second generation helicopter - Google Patents

Abstract

The invention relates to a working principle of a second generation helicopter and belongs to the field of airplane design. The working principle can be utilized to solve the problems of ultralow airplane speed, ultrahigh failure rate, serious vibration, and the like. According to the technical scheme, a leveling frame, a coaxial shaft system, a vertical propeller and a gravity leveling method are adopted. The working principle is mainly used for increasing the speed, reducing the failure rate, solving vibration problem and reducing parking space.

Description

Second generation autogyro principle of work

(1) technical field

Airplane design.

(2) background technology

First generation autogyro has a common deadly defect: done by maneuvering system control blade and dance in the air motion, the conversion that flies and hover before aircraft could be realized.Because big oar is not hard-wired, has produced many problems.

1, the structural strength and the heavy burden ability of big oar have been reduced.

2, the fault rate of aircraft and the work capacity of ground service have been increased.

3, there is serious vibration problem in aircraft.

(3) summary of the invention

1, adjustment equalizer bar (being called for short the leveling frame).2, close coupled type axle system.3, vertical helical oar.

4, gravity adjustment balance control method (being called for short gravity leveling method).

The present invention is except that having solved the problem described in second background technology, and the spiral of also having eliminated autogyro is sick, has strengthened the adaptive capacity (can very little place in park) of autogyro to the place.More in view of gizmo quantity, concrete scheme please be seen the essence data.(autogyro is when tail-rotor is malfunctioning, and under the drive of big oar, aircraft gets into slew mode, get out of hand ability; This phenomenon is called the spiral disease)

(4) description of drawings

Fig. 1 is a leveling frame forward sight constructional drawing; Fig. 2 is a leveling frame backsight constructional drawing; Fig. 3 is a leveling frame side-looking constructional drawing; Fig. 4 is leveling frame plan structure figure; Fig. 5 is a registration arm median vertical line vertical section constructional drawing; Fig. 6 is that the close coupled type axle is a horizontal central line tangent plane constructional drawing; Fig. 7 is that the close coupled type axle is a median vertical line tangent plane constructional drawing; Fig. 8 is a monotubular rowlock horizontal central line tangent plane constructional drawing; Fig. 9 is a monotubular rowlock median vertical line tangent plane constructional drawing; Figure 10 is a bitubular rowlock median vertical line tangent plane constructional drawing; Figure 11 is a bitubular rowlock horizontal central line tangent plane constructional drawing; Figure 12 is a bidirectional locator median vertical line square section constructional drawing; Figure 13 is two-way positioning control system median vertical line vertical section constructional drawing; Figure 14 parks three-view diagram in the power leveling hangarage; Figure 15 is a power leveling aircraft median vertical line vertical section constructional drawing; Figure 16 flies the side-looking design sketch before being; Figure 17 is a tail-rotor type gravity leveling aircraft median vertical line vertical section constructional drawing; Figure 18 is a tail vane type gravity leveling aircraft median vertical line vertical section constructional drawing.

(5) specific embodiment

In Fig. 1: the 1st, undercarriage, the 2nd, bearing seat, the 3rd, axle, the 4th, fairing, the 5th, registration arm.

In Fig. 2: the 1st, put, the 2nd undercarriage, the 3rd, tail pipe, the 4th, lock, the 5th, registration arm on the shelf.The 6th, fairing.7, be two tail pipe type tail pipe installation places.The leveling frame is the joint portion that last cabin and following cabin < are seen Figure 15 >, and fairing < 6>makes the both sides rounding off on leveling frame and following cabin surface, can reduce friction and cornering resistance.The structure of tail pipe < 3>is to be welded into hollow rectangular post with trough material, and the outside puts thin pipe, also can directly replace with thick pipe.

In Fig. 3: the 1st, put, the 2nd undercarriage, the 3rd, axle, the 4th, bearing seat, the 5th, registration arm, the 6th, tail pipe, the 7th, lock on the shelf.Axle < 3>is welded on the place ahead of put on the shelf < 1 >, and bearing seat < 4>is fixed on the top of undercarriage < 2 >.It is open and closed around axle with undercarriage to put on the shelf.

In Fig. 4: the 1st, put, the 2nd undercarriage, the 3rd, registration arm, the 4th, axle, the 5th, bearing seat, the 6th, lock, the 7th, screw, the 8th, fairing, the 9th, tail pipe on the shelf.

Fairing < 8>will be loaded onto in the inboard of undercarriage < 2 >, and the upper surface that makes down cabin < see Figure 15>is smooth, can reduce flight resistance and increase the cabin space.The leveling frame connects up and down with screw < 7 >, and two cabins < also can weld >.Under the condition that guarantees structural strength, the diameter of tail pipe < 9>is more little good more, can reduce flight and cornering resistance.Raising speed and operating characteristic all are beneficial to.

In Fig. 5: the 1st, put, the 2nd undercarriage, the 3rd, interior registration arm, the 4th, lock hole, the 5th, lock, the 6th, pin, the 7th in the lock, lock inner spring, the 8th, outside fix pipe, the 9th, cover plate on the shelf.

Registration arm is to be welded with 2 thick tubing of high strength arc, and the gap between two pipes is as much as possible little, stamps behind the butter and can movable get final product.In order to help to understand, processing and amplifying has been done in the gap among the figure.

Outside fix pipe < 8>is welded on < 1>top of putting on the shelf, and interior registration arm < 3>is to pass the top that put on the shelf < 1>is welded on undercarriage < 2 >.The effect of registration arm be prevent to put on the shelf with undercarriage about the dislocation, transfinite open, torsional deflection.When the leveling frame is opened to lock angle, pin < 6>in-line in lock hole < 4>and the lock, under the force of lock inner spring < 7 >, pin gets into lock hole in the lock.

In Fig. 6: the 1st, driving shaft bearing, the 2nd, axle-shaft gear, the 3rd, fix shaft, the 4th, fix shaft gear, the 5th, fix shaft bearing, the 6th, interior axle, the 7th, interior shaft gear, the 8th, rotation direction, the 9th, axle drive shaft, the 10th, seal cover cap, the 11st, axle is a shell, the 12nd, interior shaft gear locating tab.

3 times of big oar maximum pull design value will be able to bear at least with the big supporting use of oar, its structural strength in close coupled type axle system.Adopting 4 designs to make axle is that working stability, noise are little, the life-span is long.Because at least 3 points could be confirmed a plane, increase a some nature and can improve the stability on this plane, vibrate nature little noise is diminished; The axle that increases has been shared other each partial pressure, and wearing and tearing have reduced, and the life-span understands elongated naturally.

In Fig. 7: the 1st, last oar; The 2nd, following oar; The 3rd, inner shaft bearing; The 4th, the outer shaft bearing seat; The 5th, grease cup; The 6th, last cabin top ceiling; The 7th, interior axle; The 8th, outer shaft; The 9th, the butter hole; The 10th, the outer shaft gear-bearing; The 11st, outer shaft gear; The 12nd, outer shaft gear locating tab; The 13rd, axle drive shaft; The 14th, interior shaft gear; The 15th, interior shaft gear positioning screw cap; The 16th, card; The 17th, interior axle height adjustment screw; The 18th, rotation direction; The 19th, axle-shaft gear; The 20th, the pin hole; The 21st, driving shaft bearing; The 22nd, bearing cap shim; The 23rd, axle is a shell; The 24th, last cabin floor; The 25th, the fix shaft gear; The 26th, seal cover cap; The 27th, interior shaft gear locating tab; The 28th, screw rod.

Grease cup < 5>is the short pipe of a diameter and inner shaft bearing < 3>equal diameters, has bored a butter hole (overlapping with outer shaft butter hole < 9 >) above, is contained between two bearings, and being convenient to is that two bearings refuel simultaneously.

Outer shaft < 8>be one high-strength thick-walled, outer shaft gear locating tab < 12>has 4, is crossing distribution in same horizontal surface.Install to the position to outer shaft gear < 11>earlier during installation, outer shaft gear locating tab < 12>is inserted (relevant position of outer shaft gear and outer shaft is drilled with 4 same holes) from the inside of outer shaft, again inner shaft bearing < 3>being installed to the position can locate.

Axle drive shaft < 13>and driving shaft bearing < 21>are fixed on up and down that two axles are between the shell < 23 >, and the gap between outer shaft gear-bearing < 10>and outer shaft gear < 11>and the bearing cap shim < 22>is by bearing cap shim < 22>and spool be that the thickness of the pad between the shell < last 23>decides.

In the spiral shell public affairs of axle height adjustment screw < 17>to be fixed on axle be above the shell < 23 >, its side has up and down two screws, the size of this screw and screw rod < 28>big or small supporting.In the both sides of nut lower end of axle height adjustment screw respectively open a gap the size of this breach and card < 16>big or small supporting.Have two apertures above the card, big or small supporting, the distance of two little hole sizes and screw rod and two screws of spiral shell Gongshang face are supporting.

When adjusting work is accomplished, the breach of card and nut is coincide, the screw that the aperture and the spiral shell of card is public is identical, and the aperture that again screw rod is passed card is fixed in the screw of spiral shell public affairs and can locatees.

Diameter, thickness, tapering and the number of teeth of interior shaft gear < 14>and outer shaft gear < 11>are identical, guarantee under same axle drive shaft < 13>drives with this, and the cireular frequency of interior axle < 7>and outer shaft < 8>running is equal, in the opposite direction.If the shape of last oar < 1>and following oar < 2>is identical, their distrubing moment is just offset so, and whole propeller < contains oar and following oar>just can not produce disturbance.Therefore the air of screw propeller output is the circumference symmetry, is parallel to main shaft, just perpendicular to (will regard last oar and following oar as an integral body this time, and it is vertical with main shaft) of screw propeller.Two screw propellers that this shape is identical are called the similar shape screw propeller.

The compound no disturbance screw propeller of close coupled type require the cireular frequency fixed in shape identical, in the opposite direction, two oars of two oars runnings constant, can be different, key is that no distrubing moment is exported.This screw propeller is exactly the big oar that the present invention selectes.The similar shape screw propeller is a kind of Utopian screw propeller that is used for concept design, and special-shaped screw propeller is handled through method of difference also can reach the same effect of not having disturbance output with the similar shape screw propeller.

The production and the usage condition of screw propeller have variety.Both can vertically use, but also horizontal force; Both can use separately, also can compoundly use.In order to let aircraft have best performance, under given conditions, can even must make different shapes to last oar (bow oar) with following oar (back oar), for example install fiaring cone additional, and reduce output of distrubing moment or the like with this method.

Close coupled type axle system is because the rotation direction of two axle drive shafts is opposite, and cireular frequency equates.Select for use 2 identical electromagnetic adjustable speed motors of performance perameter to come driven in synchronism; Select for use the compound no disturbance screw propeller of close coupled type supporting again; Then the distrubing moment of whole drive system is offset fully, makes aircraft have fabulous stability, has realized the unmanned of last cabin simultaneously.This no disturbance drive system is that the present invention is able to one of key of success, and the application of this system vertically descends when aircraft is aloft run out of steam, and perhaps landing forwards under the effect of force of inertia can not get into spiral status.

If produce a small amount of disturbance, this is because the difference (difference in size, length difference) of interior axle and outer shaft causes in the production process, because do not consider this hairline during concept design.Adopt the difference balancing act during correction: go up oar and adopt different length, different thickness, material different with the reverse system that following oar and outer shaft are formed, the distrubing moment of the two is equated, just can accomplish not have disturbing moment output with the clockwise system that interior axle is formed.

The tail-rotor system that the present invention selectes is that the non-compound microvariations drive system of close coupled type < is seen Figure 13 >.Principle is: the rotation direction of the passive system that active system that drive motor and interior axle are formed and outer shaft and screw propeller are formed is opposite, so the distrubing moment of the two is cancelled out each other, the distrubing moment of system is very little.

Concrete grammar is: axle height adjustment screw < 17>in the cancellation of axle system.Interior axle < 7>and outer shaft < 8>are cut into isometric, and screw propeller is contained on the outer shaft.In axle lower end tooth punching and to extend to axle be below the shell < 23 >, the sleeve through inner tooth punching fuse with the drive motor of axle head tooth punching < jacket casing is on interior axle lower end and drive motor axle >.Axle is that shell < 23>is fixed on the drive motor shell with screw.

Comparative analysis: what the cassette series helicopter of Russia used is the compound movable screw propeller of close coupled type, and the blade of this oar will dance in the air during work.For anticollision, the diff-H of last oar and following oar designs very greatly, and the center of gravity of aircraft has uprised, and stability is the meeting variation naturally, and structural weight also can increase simultaneously.The diff-H of close coupled type composite shape-setting screw propeller is much smaller, and structural weight will reduce; Screw propeller with and axle drive shaft all be hard-wired, so the stability of aircraft and functional reliability are suitable with whirlpool oar aircraft.

Because the work efficiency that dances in the air movable screw propeller of blade is less than 30%, too many loss in efficiency reduces the speed of aircraft and heavy burden ability greatly, and has produced serious vibration problem; This is the intrinsic shortcoming of first generation helicopter, also is the too short basic reason of its voyage.The work efficiency < for example whirlpool oar aircraft>about 50% of general setting screw propeller, the size of heavy burden ability and speed and voyage mainly receives the Power Limitation of power plant, otherwise not restriction.But movable screw propeller also can produce ahead power when producing lift, because it carries auto-bank unit, this is intrinsic advantage of first generation helicopter and characteristic; Though though setting screw propeller high efficiency, level is used can not produce lift, vertical use can not produce ahead power, and this shortcoming is exactly the key issue that second generation helicopter need solve.

First generation helicopter becomes also to dance in the air, lose also and dance in the air, and can find out from this point: the performance of aircraft and software relation are very big, and hardware is not unique factor.

In Fig. 8: the 1st, horizontal plate, the 2nd, fairing, the 3rd, brace panel, the 4th, screw, the 5th, blade, the 6th, sleeve.The angle of blade < 5>and brace panel < 3>must not be greater than 30 degree, otherwise can have influence on structural strength.Blade < 5>is fixed on the horizontal plate < 1>with screw < 4>or welding, and they form a screw propeller jointly.

In Fig. 9: the 1st, pin, the 2nd, strengthening cap, the 3rd, sleeve, the 4th, pin hole, the 5th, blade, the 6th, fairing, the 7th, brace panel, the 8th, horizontal plate, the 9th, screw.

Strengthening cap < 2>is the short pipe of an internal diameter and sleeve < 3>equal diameters, has 2, and pin < 1>has 8, all is the necessary annex of rowlock.Earlier be enclosed within rowlock the correspondence position of close coupled type axle system < seeing Fig. 7>during installation, their pin hole is overlapped, again pin < 1>is inserted,, be enclosed within the sleeve two ends and kept one minute, can locate after the cooling then with fire heating strengthening cap.Sleeve will use high-strength thick-walled, and horizontal plate and brace panel will use heavy-gauge sheeting, and the angle between horizontal plate and brace panel and the sleeve is 90 ° of angles.

This figure also is the erection plan of vertical helical oar, and blade not necessarily haves three layers during actual the use.When blade is 1 layer, be installed in the middle level; When blade is 2 layers, be installed in the upper and lower.In order to simplify drawing, all be to do representative among the figure afterwards with one deck blade.

In Figure 10: the 1st, pin, the 2nd, strengthening cap, the 3rd, pin hole, the 4th, internal frame sleeve, the 5th, butter hole, the 6th, internal frame location hook, the 7th, outrigger location hook, the 8th, outrigger sleeve, the 9th, horizontal plate, the 10th, brace panel, the 11st, fairing, the 12nd, following oar, the 13rd, last oar, the 14th, truncated cone-shaped cover plate, the 15th, screw.

Pin < 1>has 8, and strengthening cap < 2>has 2, all is the necessary annex of rowlock.

Outrigger sleeve < 8>cannot up-and-down movement, only in horizontal surface, to rotate an angle of 90 degrees.Gap between inside and outside two sleeves < 4 and 8>will be tried one's best littler, coats can rotate behind the butter to get final product.The lower layer of water flat board of internal frame will do more, and the width of increase equals 2 times of thickness of outrigger location hook < 7 >.The outrigger location hook is weldingly fixed on the intersection of outrigger brace panel and horizontal plate.

Rowlock must turn around during use.Because blade is not a planar structure; Its upper limb and lower edge have certain height poor; Below if movable oar < 13>is placed on, the design of diff-H must be greater than the diff-H between the blade edge between the blade so, because movable oar repeatedly below can be run into top fixedly oar < 12>when opening.Turn use around, movable oar has just been avoided this problem up, and the diff-H between the blade can design very for a short time.

When parking, will go up oar and rotate 90 ° of angles, last oar and following oar almost stack togather in same vertical plane surface, can reduce parking space to greatest extent.Before taking off, under air resistance promotes, the auto-reverse 90 ° of angles of last oar, screw propeller becomes criss-cross again again, can obtain maximum work efficiency; Because have only a pair of blade in the same horizontal surface in work, have no interference.Just reduce to minimum level to the adverse effect of high performance airscrew cavity phenomenon, improve the work efficiency < power factor>of screw propeller.

The function of this rowlock is that same screw propeller is split into two, makes screw propeller have the function of horizontal and vertical co-conversion mutually, to parking and flying all very favourable.The screw propeller that assembles with this rowlock promptly is not fixing horizontal, neither fixing vertical: because its whole blades neither be operated in the same vertical plane surface neither be operated in the same horizontal surface, so it is movable vertical helical oar.

In Figure 11: the 1st, outrigger location hook, the 2nd, outrigger horizontal plate, the 3rd, outrigger sleeve, the 4th, internal frame sleeve, the 5th, internal frame location hook.Can find out from Ben Tu, if the excessive clearance between internal frame sleeve < 4>and the outrigger sleeve < 3>when aircraft flies in strong wind, will bump between the two; The gap is too small then can be stuck.

In Figure 12: the 1st, brute spring, the 2nd, rear casing, the 3rd, last locating plate,, the 4th, following locating plate, the 5th, axle.The model of left and right two brute springs < 1>is identical, is fixed on the both sides of locating plate < 3 >.On the rear casing that last locating plate is welded on < 2 >, following locating plate < 4>is welded on the axle < 5 >.

In Figure 13: the 1st, three-way motor, the 2nd, retarder, the 3rd, bearing seat, the 4th, following locating plate, the 5th, axle, the 6th, pin, the 7th, sleeve, the 8th, oblong connection pipe, the 9th, tail-rotor system, the 10th, tail pipe, the 11st, last locating plate, the 12nd, bidirectional locator shell.

Oblong connection pipe < 8>is welded on the shell < 12>of bearing seat < 3>and bidirectional locator, with screw total system is fixed on the rectangular post below of tail pipe < 10>at last.Three-way motor < 1>is fixed on the rectangular post below of tail pipe < 10>with screw.

<bidirectional locator>axle < 5>and three-way motor < 1>combine through retarder < 2 >, and under three-way motor < 1>drove, axle < 5>can left or be turned right and moved 90 ° of angles, and upper and lower two locatings plate this moment < 4 and 11>coincide and are in the same place, and it is blocked; After the loss of power, under the brute spring force of < seeing Figure 12 >, system reduces automatically.

Sleeve < 7>is the joint portion of tail-rotor system < 9>and two-way positioning control system; Be fixed in the horizontal surface at tail-rotor system center of gravity place; With pin < 6>or screw two systems incorporate are become an integral body, two systems will be as far as possible near and take necessary rectification measure.Under two-way positioning control system control, the tail-rotor system can possess the operation of accent power and two functions of steering operation at vertical direction and horizontal direction outputting power.The 26S Proteasome Structure and Function of tail-rotor system is please referred to the 12-13 section of Fig. 7 explanation.

In Figure 14: the 1st, birds-eye view, the 2nd, lateral plan, the 3rd, front elevation.

Can find out from this figure: aircraft park area=screw propeller length * fuselage width.The tail-rotor reach is a target with military aircraft in this programme, and civil aircraft needn't adopt.Military aircraft particularly naval aircraft will reduce parking space as far as possible.So adopt telescopic distortion tail pipe, the advantage of this programme is under the condition that does not reduce tail-rotor moment, to reduce parking space, and shortcoming is a trouble.But the scheme of the big oar of folding that generally uses with first generation autogyro is compared, and the work capacity of folding distortion tail pipe can be ignored, and technical advantage is self-evident.Specific practice is: be fixed on a littler tail pipe back lower place to tail-rotor system and two-way positioning control system together and <be not with pipe >; Little tail pipe is inserted in the hollow rectangular post of tail pipe; Pull it before taking off, get final product with fixing the two the relative position of pin again.Two pin holes will respectively be bored in the relevant position of two tail pipes.If tail pipe directly uses thick pipe, so little tail pipe also uses thick pipe.

The employing fixedly parking space of the civil aircraft of tail pipe slightly increases, but can significantly reduce cost.This is because civil aircraft is higher to the economic index requirement, must reduce productive costs and use cost as far as possible.

In Figure 15: the 1st, rowlock, the 2nd, last oar, the 3rd, following oar, the 4th, last cabin, the 5th, cockpit, the 6th, power supply, the 7th, balance in roll face, the 8th, aroused in interest, the 9th, tension point, the 10th, tail pipe, the 11st, two-way positioning control system, the 12nd, electromagnetic adjustable speed motor, the 13rd, tail-rotor system, the 14th, close coupled type axle system, the 15th, power-transfer clutch, the 16th, electromagnetic adjustable speed motor, the 17th, recliner, the 18th, following cabin, 19, be aroused in interest, the 20th, aroused in interest, the 21st, the balance in roll line.

The power configuration of last cabin < 4>is exactly the compound no disturbance drive system of said close coupled type in Fig. 7 explanation.Power-transfer clutch < 15>is convenient to cut off an electromagnetic adjustable speed motor < 16>of war wound, and civil aircraft is used clutch instead.Recliner < 17>is used jack usually, and the two ends of jack are separately fixed on putting on the shelf of leveling frame and the undercarriage.

Power supply < 6>can be a battery pack; Also can be generator set, hang over balance in roll face < 7>with the identical generator set of 2 covers with Short Position (the double fairing of doing) half plug-in mode usually and go up (should not be plug-in) speed and higher scout, fighter plane and the special plane of safety requirements.The advantage of this layout is: (1) is favourable to the air inlet and the exhaust of driving engine.(2) space is big in the storehouse.(3) waste gas and noise influence little to personnel in the storehouse.(4) easy maintenance.

During customer requirement, two cover generator seies of power supply < 6>can directly be replaced two cover electromagnetic adjustable speed motors < 16 >, and electrical generator changes littler model into simultaneously, and electromagnetic speed-adjusting makes the throttle speed governing into.But the control of throttle must guarantee that whole drive system does not have distrubing moment output < throttle is synchronous>under the normal circumstances.

Tail-rotor system < 13>both can install up, also can install down, and concrete scheme will be confirmed (rotation direction that three-way motor can be controlled motor through the conversion of circuit) according to user's particular case.The angle of attack of tail-rotor system < 13>blade will be set at 45 °, makes clockwise work efficiency with counter-rotating identical.

The advantage of this programme is: (1) complete dynamo-electric gasification operation, and crew's work capacity is little, and 3 people's units can be flown for long-distance (2 chaufeurs can be in shifts, a mechanist emergent).(2) fault rate is low.Equipment with the most use is motor, and motor manufacturing technology unusual mature and reliable.(3) aircaft configuration is simple, and staff training is fast.

Aroused in interest is the abbreviation at the dynam center of object, and center of gravity is the statics center of object, but is not necessarily the dynam center.Because object under dynamic action with the air mutual action, its action effect and object surfaces shape relation are very big, have only the center of gravity and aroused in interest of the object of complete symmetry to be only coincidence fully, for example spheroid.The statics center is fixed, and the dynam center is unfixed.

With the aircraft shown in this data is example: the air of big slurry output is on one's body aircraft; Because the layout of the left and right sides of aircraft (seeing Figure 14) is identical; The moment of the aircraft left and right sides (comprising gravity torque and lifting force moment) equates, so the left and right directions of aircraft is a balance.Because the layout of the rear and front end of aircraft (seeing Figure 14 and 15) is different, the moment of aircraft rear and front end is just not necessarily identical.Because even the gravity torque at two ends equates < that is to say that big oar pulling force is point of action with the center of gravity >; If lifting force moment is unequal; Lifting force moment missionary society between the two ends makes aircraft produce the lift-over effect so, and the end that just lifting force moment is big is to the direction motion of lift, and the other end is then opposite; So the fore-and-aft direction of aircraft is with regard to overbalance.The reason that produces this phenomenon is that the lifting force moment that the difference configuration of rear and front end causes is lost unequal.The way of correcting is that the point of action with pulling force moves to the less end of lifting force moment; Make the gravity torque of a fore-and-aft direction of aircraft acquisition poor, the lifting force moment that reduces fore-and-aft direction simultaneously is poor, along with the continuous increase of tension point miles of relative movement; When the gravity torque difference of aircraft equates with the lifting force moment difference; The torque difference of rear and front end is zero, and aircraft is with regard to balance, and the point of action of this pulling force < 9>is exactly aircraft power center < 8 >.

The front was said: the advantage that close coupled type does not have the disturbance drive system is: the distrubing moment of system outlet is zero.So the stable type aircraft is a vertical uplift not having under the situation of outer force-disturbance, do not have any other sign; Because the torque difference of all around both direction of stable type aircraft all is zero <being exactly that lifting force moment difference and gravity torque difference equate >, aroused in interest < 8>of aircraft and tension point < 9>overlap.At this moment start tail-rotor system < 13 >, let it produce lift, the lifting force moment at aircraft rear portion will be greater than the lifting force moment of front portion so; It is poor that aircraft just obtains the lifting force moment of a fore-and-aft direction, and aroused in interest will rearward moving forms new aroused in interest < 19 >; Aircraft has got into the overweight state in the place ahead, has just become the instability mode aircraft, will tilt to the less the place ahead of lifting force moment; Will drive down at big oar and fly forward, just realize the march forward transformation of power of big oar pulling force.Anterior torque difference with the rear portion is big more, and the leaning angle of aircraft is big more, and aroused in interest amount of movement is big more, and aircraft just can fly forward with bigger speed, so tail-rotor system < 13>must adapted electromagnetic adjustable speed motor < 12 >.

More than fact proved: for same particle, the effect that lift increases is the same with the effect that gravity reduces, and the effect that lift reduces is the same with the effect that gravity increases, and negative lift equals gravity.Around this principle, we can carry out the actv. manipulation to the instability mode aircraft.

The mechanical characteristic of anterior instability typing aircraft is opposite with the mechanical characteristic of stable type aircraft.Because aroused in interest < 20>forward configuration of aircraft, tension point < 9>lags behind in other words, and the gravity torque of aircraft forward is greater than the gravity torque at rear portion, and aircraft is in the overweight state in the place ahead.The existence of gravity torque difference can't be taken off vertically aircraft.To make this time the tail-rotor system produce negative lift, be used for offsetting the lift at aircraft rear portion; From effect, also equal to have increased the gravity at rear portion, make aircraft aroused in interest rearward mobile.Heighten the rotating speed of tail-rotor system motor, when the negative lift moment that increases had been offset original gravity torque difference, the front and back torque difference of aircraft was zero, and new aroused in interest < 8>overlap with tension point < 9 >, and aircraft has just become the stable type aircraft, just can take off vertically.

When flying before needing, aircraft must get into the overweight state in the place ahead again.Turn down the rotating speed of tail-rotor system motor up to being zero, the torque difference of fore-and-aft direction is increasing, aroused in interestly moves forward more and morely, and aircraft is more and more unstable, and the speed that flies before the aircraft just can slowly be put on.High-speed flight if desired must increase the lift of afterbody as the stable type aircraft, strengthens aroused in interest lead, will connect the circuit of tail-rotor system motor instead, lets the tail-rotor system produce lift.When needing deceleration and landing, above-mentioned process is just reversed one time.

Any helicopter all have one predetermined aroused in interest.This is aroused in interest if big oar tension point has broken away from, and aircraft is in the overweight state of certain direction, and trim just can be taken off vertically again.Therefore any expendable article < for example fuel oil, goods>all must equivalent be distributed in the balance in pitch face and the balance in roll face both sides of aircraft symmetrically, and while ana consumption, otherwise all can produce the interior force-disturbance identical with outer force-disturbance effect.

In sum: the stability of autogyro is the interrelation decision of fulcrum < tension point>and equilibrium point < aroused in interest >.The torque difference at two ends equalled zero when the two overlapped, and aircraft is in stabilized conditions < static >; The torque difference at two ends was greater than zero when the two separated, aircraft be kept in motion < instability >; The stable type airplane motion needs the increase of torque difference, and the instability mode aircraft is static to need making zero of torque difference.The maintenance that the two state < overlaps or separation>or the process of conversion are exactly the maintenance of aircraft state < static or motion>or the process of conversion, or perhaps the process of the maintenance of aircraft stability or variation.

The instability of helicopter has two types: it is fixed that the phenomenon that the place ahead is overweight is called anterior instability, the phenomenon that the rear is overweight be called the rear instability.The method of operating of extra-duty method of operating in rear and stable type is identical, but difficulty is very big.Help flying forward because the place ahead is overweight, the rear is overweight to be helped flying backward.That is to say that the rear is overweight leaps difficulty before more, flies to consume the leveling capability of aircraft before reluctantly, this with aircraft before fly mode of operation and do not conform to, only if fly before aircraft has and after fly two kinds of mode of operations.But the multimode operation meeting causes higher productive costs and maintenance cost, is worthless; Its cost is lower with regard to realizing the flight of any direction through tune for the aircraft of unidirectional flight.So: it is overweight to occur artificial rear in the use, and the place ahead is overweight can not be too many, keep the stable of system as possible.That is to say: the disturbance that the limited leveling capability of aircraft mainly is used for offsetting external force, the waste of leveling capability is exactly the waste of safety index.

Because of gravity quickens to drop, it is auto-reverse and produce a small amount of lift under air resistance promotes that close coupled type does not have the disturbance drive system when aircraft aloft ran out of steam.Because aroused in interest and center of gravity are not same point, so the overweight end of aircraft is because of lift-over effect ground connection at first; If aroused in interest and center of gravity overlaps, aircraft is exactly a free-falling body.

The needs that the stability of research aircraft is to use, next is only the needs of production.Because in use, aircraft and its kinematic scheme of load (comprise in the machine any have the article of quality and the external force that aircraft receives) formation.The type of aircraft can have a variety of, and the state of system has only stable and unstable two types, can handle this aircraft of two types and just can handle this system of two types.From angle of mechanics, the manipulation process of aircraft is the manipulation process to total system, is to the maintenance of the two states of total system or the process of conversion.Real aircraft can only be that < implication of the words is following: the aroused in interest of aircraft is exactly big oar tension point, and the median vertical line vertical section is exactly the balance in pitch face, and the median vertical line square section is exactly the balance in roll face in stable type; These two balancing planes are called balance in pitch line and balance in roll line respectively with the tangent line on following cabin floor, and the tangent line of these two balancing planes is exactly aroused in interest vertical line, is called the VE line, also is called the optimum balance line; The plane at the aroused in interest place vertical with pulling force is vertical balancing plane >, the but conversion frequently between two states of real system, and in most cases be unsettled, the tail-rotor system of aircraft often uses.This is static because of air under the perfect condition, the state exchange of aircraft seldom, the use of tail-rotor system is exactly seldom naturally.This is the difference of the theory and practice that must understand of user.Overweight for fear of the rear occurring, be convenient to the goods configuration, must be marked on balance in roll line < 21>down on cabin < 18>floor.This shows: the balance in roll face embodies the balance in pitch of aircraft, and the balance in pitch face embodies the balance in roll of aircraft, and vertical balancing plane embodies the vertical balance of aircraft.

In like manner, the torque difference of left and right directions also can destroy the balance in roll of aircraft; That is to say: vertically overweightly help vertical flight, the horizontal overweight horizontal flight that helps, overweight direction is exactly a heading, overweightly nowhere then can't fly.Because just the arm of force is very little for the length of aircraft left and right directions, internal force still be the torque difference that produces of external force all be very little; Secondly the cross motion resistance of aircraft is very big.The influence that aircraft relies on powerful steering hardware < tail-rotor system>can offset horizontal distrubing moment easily.So the cross motion of aircraft is ignored during theoretical investigation, as long as the trim of machine internal burden.Leveling method in the production process is identical with the described fore-and-aft leveling method of preamble.

In like manner, the torque difference of above-below direction also can destroy the vertical balance of aircraft.Because the arm of force of aircraft above-below direction is a point and needn't calculate < 1 takes advantage of any several former number >, the gravity of aircraft also is certain, so as long as the size of control lift just can control the vertical balance of aircraft and control height.

Generally speaking: the state of aircraft is embodied in three directions < fore-and-aft direction promptly vertically, left and right directions is promptly horizontal, above-below direction is promptly vertical >, and the state of different directions can be identical, also can be different.For example aircraft is vertical stable when promptly highly constant, and vertical and horizontal can be stabilized conditionss, also can be state of kinematic motion < instabilities >; If three directions are < omnidirectional is stable>when all being in stabilized conditions, aircraft remain static < park or hover >.

In sum: the state of object is by the decision of the interrelation of the point of action of power < pulling force or thrust>and mechanics center < equilibrium point >.Object was in stabilized conditions < static>when the two overlapped, object be kept in motion < instability>when the two separates; The maintenance that the two state < overlaps or separation>or the process of conversion are exactly the maintenance of object state < static or motion>or the process of conversion, or perhaps the maintenance of object stability or the process of variation.

Specifically: the mechanics center comprises dynam center < aroused in interest>and statics center < gravity >.Object does not have resistance of motion when in quiescence or vacuum, moving, aroused in interest and center of gravity is same point; Most objects have resistance of motion in fluid, aroused in interest and center of gravity is not same point; Spheroid has the characteristic that universal distrubing moment equates, its aroused in interest and center of gravity all is the centre of sphere.

In Figure 16: the 1st, aroused in interest the 1, the 2nd, aroused in interest the 2, the 3rd, aroused in interest the 3, the 4th, tension point, the 5th, lift point of action, the 6th, tiltangle, the 7th, ahead power point of action, the 8th, leveling angle, the 9th, balance in roll face, the 10th, registration arm, the 11st, recliner.

In order to reduce flight resistance, also, when before aircraft begins, flying to top rake, start recliner < 11>simultaneously for people and goods in the cabin can not toppled over, the leveling frame will be opened an angle, and this angle is exactly leveling angle < 8 >, best leveling angle=leaning angle.

The tail-rotor system produces lift when flying before the aircraft, if the leveling frame is not opened, whole airplane turns forward so, and the point of action of big oar pulling force still is original aroused in interest 1 < 1 >, but the aroused in interest meeting of aircraft is mobile backward, forms new aroused in interest 2 < 2 >.After the leveling frame is opened, because the raising of the center of gravity of last fuselage, so aroused in interest < 2>of whole airplane also can correspondingly rise to aroused in interest 3 < 3 >.Simultaneously, the point of action of pulling force also moves backward, forms a new tension point.The result is that the distance of point of action and original aroused in interest 1 < 1>of new aroused in interest 3 < 3>and pulling force is bigger, and the torque difference of fore-and-aft direction is bigger, and aircraft more instability also just flies sooner.Can know simultaneously: double accent force mechanisms tail-rotor system or the tail vane system of doing steering hardware can only be used for the state of aircraft and the conversion or the maintenance of direction, cannot use arbitrarily, otherwise aircraft can't keep a stable status < to hover or move >.

When aircraft turns to, aircraft median vertical line vertical section and belonged to angle between the plane originally yaw angle.The yaw angle that aircraft obtains in unit time is yaw rate, unit degree of being/second, and formula is: yaw rate=A/T, wherein A is a yaw angle, T is the time.The yaw rate of aircraft is big more, and leveling capability is strong more.

Clearly: the yaw rate of aircraft is bigger, accelerating ability is good more, leveling capability is strong more.Just the control ability of aircraft is strong more, and the steady ability of the change of aircraft is strong more in other words.

The aircraft that does not become steady ability does not have value of service, and becoming steady essence is exactly leveling.Be exactly on the contrary any aircraft that can use all be variable stability airplane, it is different that difference is that different aircraft becomes steady mode, ability is different.The purpose of leveling can be to keep stable < course, highly, speed >, also can be to destroy stable < course, highly, speed >.Therefore the standard of estimating the aeroplane performance quality is: surely must live, become fast.

See that Figure 16 can know:

The pulling force conversion ratio equals ramp rate, so leaning angle is big more, forward flight speed is big more.If because the allowable angle of inclination design lift that causes bigger than normal is less than normal then must take the lift-rising measure, otherwise aircraft will crash when high-speed flight in stall, for example sets up fixedly short limb as rice-24 aircrafts; To control down the length of cabin simultaneously, avoid blade to beat head.For high-speed aircraft, the pulling force maximum conversion rate also is a very important parameters.

Contrastive analysis on the new and old thing: autogyro is extraordinary aircraft, and it should perpendicular movement, horizontal motion again.Because the power of power plant and mode of operation restriction, it is unpractical directly using with pattern flight, so the distortion aircraft has just become optimal selection.What first generation helicopter was selected is the screw propeller deformation program, exactly screw propeller is taken apart, makes movable screw propeller.But, because blade dances in the air the propeller power loss that causes too big (remaining less than 30%), cause the speed of first generation helicopter and load carrying ability very little, cause voyage very little.This is that the process that moves ahead of blade and the pulling force difference of back row process cause, and the loss in efficiency that blade pulling force difference causes is exactly the main source of vibrational energy.Because the screw propeller that dances in the air at a high speed wearing and tearing are very fast, need auto-bank unit again, so the fault rate of drive system is very high, the work capacity of ground service is very big.The practicality of aircraft is very poor to be obvious to all.

The loss in efficiency that the major cause that first generation autogyro speed and voyage are too little causes except blade dances in the air was too big, another major cause was exactly that the too for a short time pulling force maximum conversion rate that causes of allowable angle of inclination is too little, had lost voyage in the time of aircraft loss speed.The problem that this software defect causes can not be resolved except changing software.Because the amount of dancing in the air of blade is big more, the loss rate of power is big more, and the vibratory magnitude of aircraft is big more, and the recruitment of resistance is big more; The too big aircraft that must cause of allowable angle of inclination design can't use.

The present invention has selected the scheme of frame deflection.Hard-wired screw propeller no longer dances in the air blade, has guaranteed that the work efficiency of screw propeller can not reduce (about 50%), and powerful power reserve and higher pulling force maximum conversion rate will inevitably be greatly improved the speed of aircraft and load carrying ability, and voyage also can strengthen.The disappearance of blade pulling force difference makes the vibration problem of aircraft obtain solution fundamentally.Because hard-wired screw propeller is wearing and tearing not, do not want auto-bank unit yet, so the fault rate of aircraft will inevitably significantly reduce, the work capacity of ground service significantly reduces naturally, the practicality of aircraft is higher.

In Figure 17: the 1st, cockpit, the 2nd, tail-rotor system, the 3rd, leveling load, the 4th in the machine, rear terminal point, the 5th, the place ahead terminal point, the 6th, apart from controller, the 7th, optimum balance line, the 8th, the outer leveling load of machine.

The only responsible handling maneuver of tail-rotor system < 2>does not need control system, so crosswise fixed at the rearmost end of tail pipe, adopts common electric machine to get final product.Be the yaw angle of may command aircraft the current"on"time of control motor, and the rotation direction of control motor (clockwise or counter-rotating) is the yaw direction (turning left or right-hand rotation) of may command aircraft

Participate in the load that the leveling process can change and be called leveling load < size variation, change in location >.The move distance of leveling load < 3 and 8>is called the leveling distance, and the distance between the place ahead terminal point < 5>and the rear terminal point < 4>is maximum leveling distance.Under controlling apart from controller < 6>(apart from controller can be jack, also can be elevator), if the place ahead is overweight, the leveling load is rearward moved; If the rear is overweight, the leveling load is forwards moved; System can both leveling.

The leveling load can be special-purpose load, also can be the dual-purpose load, and any have the article of quality to use, for example power supply, oil plant, weapon etc.Wherein best with the requisite load of aircraft (just invalid load) dual-purpose itself, aircraft, zero load even oil plant also can normally be used when being about to use up, and economic benefit is the highest.It between power supply and the consumer electricity consumption wire joint; Belong to and flexibly connect; The motion of power supply can not influence the use of electric power, if periodic inspection (preventing that the electric wire wearing and tearing from causing short circuit), and also power supply (can be a battery pack; Also can be generator set) quality bigger, be fit to very much the double leveling load of doing.

The leveling load can be than heavy load, also can be less load.Because moment equals the product of the power and the arm of force; Leveling moment one is < moment of leveling load generating is called leveling moment>regularly, only needs less leveling distance, the leveling distance that less load must be bigger than heavy load.

The leveling load can be the machine internal burden, also can be the outer load of machine.Because it is identical apart from controller and function that the two all must be equipped with, thus the two should not separately use, can merge shared one apart from controller.

The motion platform of leveling load has influence on the outward appearance and the performance of aircraft thus because of the difference of leveling load is different.Can know according to above analysis: should select for use the outer dual-purpose load of bigger machine as the leveling load; The expendable article can use but not be optimal selection < for example fuel oil, ammunition, food >, and the leveling load generally is applied on the volume type that particularly length is bigger < transport plane for example shown in Figure 17>in the machine.

The pane that the part of leveling load will be designed to < different schemes can be arranged>thickness little < about 10cm>is called base plate, and remainder is fixed on top < leveling load in the machine>or below < the outer leveling load of machine>of base plate.The motion platform of leveling load is to be called track with the inside hollow cuboid of opening that 4 trough material are welded into, and base plate is limited in seesawing in the orbit space, but can not side-to-side movement.So the gap of left and right directions will be designed forr a short time between the two as far as possible, stamp behind the butter and can movable get final product.

The leveling load can only be at the median vertical line vertical section of aircraft with interior motion <balance in pitch face just >, otherwise the torque difference of left and right directions can produce a horizontal distrubing moment, causes the aircraft driftage.

In order to obtain huge leveling moment; Reduce the waste of inner space; Reduce the own wt of aircraft; The leveling load can < contain cockpit>and interior items is held a concurrent post by whole down cabin, and track is held a concurrent post by the undercarriage of leveling frame, is installed in base plate dead aft < following cabin back>apart from controller < jack >.This scheme is the preferred plan of gravity leveling aircraft, applies for <ultra scope>again because of it can not be applicable to power leveling aircraft.

Analyze contrast: the aircraft that uses gravity leveling method for example Figure 17 aroused in interest is the end motion that increases to gravity, is an end motion that reduces to lift from effect.The aircraft of working power leveling method < abbreviation of dynamic trim balance control method>for example the aroused in interest of Figure 15 is an end motion that increases to power; Can be an end motion < anterior instability typing>that increases to gravity from effect, also can be an end motion < stable type>that reduces to gravity.Here it is uses the difference of mechanical characteristic of two kinds of aircrafts of different modus operandis.

Present widely used dynamic trim balance control method will be in long-time internal consumption mass energy, in case power disappears, needed leveling moment reduces to zero at once; And gravity adjustment balance control method only need consume small amount of energy at short notice, and certain article is moved to certain position, so the leveling moment that needs will exist forever; Because gravity is the original power of material, its existence does not need consumes energy.

The big oar of first generation autogyro is designed to the movable screw propeller that the inefficiency blade dances in the air; Be the needs of under the limited hardware condition, sacrificing the performance adaptation software < power leveling method>of hardware, so the increase of the waste of the energy and fault has just become the fact that can't avoid.The present invention has developed special-purpose leveling hardware < leveling frame >, and the performance that need not sacrifice hardware just can adapt to the needs of various softwares < power leveling method or gravity leveling method >, has therefore avoided the distinctive defective of first generation autogyro.

In Figure 18: the 1st, tail vane, the 2nd, two-way positioning control system, the 3rd, leveling load, the 4th in the machine, rear terminal point, the 5th, the place ahead terminal point, the 6th, apart from controller, the 7th, optimum balance line, the 8th, the outer leveling load, the 9th of machine, cockpit.

Tail vane < 1>is welded on the sleeve below < seeing Figure 13>of two-way positioning control system < 2 >.In order to increase the steering torque of tail vane, must strengthen the area of tail vane as far as possible; In order to reduce the horizontal distrubing moment of tail vane, must reduce the area of tail vane as far as possible; The effective way that solves this contradiction just is to use two cover steering hardwarees < to comprise tail vane and two-way positioning control system, increase a tail pipe thus>that the tail pipe of this pair of tail pipe type is installed in the both sides at leveling frame undercarriage rear and < sees Fig. 2 >.

Two rudders must use synchronously in the same way during steering operation, in case of necessity can synchronous incorgruous utilization.Be exactly to produce negative lift with tail vane in case of necessity.Concrete operations are following: the motor circuit of one of them two-way positioning control system is connect make this motor counter-rotating on the contrary.Tail vane left-handed turning during two cover steering hardware synchronous operations; The inevitable right-hand turning of another tail vane, so two steering torques are just offset, aircraft neither can turn left and also can not turn right; But obtaining a negative lift moment, this method can be used for correcting the overweight state in the place ahead of aircraft.Certainly, this way can slacken the steering capability of aircraft.

Compare Figure 18 and Figure 17 can know: the difference of two kinds of types < tail-rotor type and tail vane type>only is that steering control mechanism is different, and concrete the application is substantially the same.

The parking space of this type is little, and no matter the indoor and outdoor is military civilian all the same, and need not extra duties work < tail-rotor type aircraft must be packed up the tail-rotor system just has onesize parking space >, has very high economy and commonality.Be specially adapted to the carrier aviation and be not suitable for the fighter plane of ground force, because break tail vane during short and small tail vane type fighter plane nap of the earth flight easily.So the life-cycle cost effectiveness of this type is apparently higher than the life-cycle cost effectiveness of tail-rotor type aircraft, value of service is higher.Certainly this conclusion is invalid for example air and land troop for the certain user.

The present invention is the principle of work that example is described second generation autogyro with the transport plane, therefore has only transport plane directly to get into the subsequent design stage with reference to drawing.And that the needs between the different user are difference is very big; Exploiting entity should combine user's specific requirement to apply in a flexible way, and could obtain desirable result of use < military version or civil version, high speed machine or low-speed machine, tail slurry type or tail vane type, power leveling or gravity leveling >.For the ease of understanding, following routine reference scheme combines drawing to write.

Example 1: sport plane need not freight house, and following the fuselage of institute needs only combines leveling load < 3>and motion space thereof in cockpit < 1>and the machine, and generator set is double does the leveling load.Configuration in the last cabin is identical with the configuration of power leveling aircraft shown in Figure 15, and the aircraft that comprises other type of tail vane type shown in Figure 180 also is identical configuration, no longer repeat specification when giving an example later on.

Example 2: domestic aeroplane and sport plane all belong to miniplane <used load do not surpass 1 ton; Consider also to design too greatly from economy >; Therefore extending the cockpit of sport plane slightly < just increases by 3 seats of a row; With 5 of positive copilots altogether 2 rows >, uniting two into one container and leveling load gets final product.Just adopt integrated design, certain space loading < can adorn the people in case of necessity>is reserved in the leveling load, and goods is double does the leveling load.

Example 3: special plane need hold the large space and big power of more personnel and large numbers of items.Comprise some important officials, entourage, the communication apparatus, weapons and ammunitions, food, medicine, sanitary fixture, conditioning unit or the like; Therefore must reequip < like Figure 15, Figure 16, Figure 17, Figure 18>with transport plane; Also have only transport plane that large space and big power could be provided simultaneously, secondly flowing of a large amount of personnel and article is convenient at the roomy back door of transport plane.

Example 4: fighter plane is similar with the sport plane structure, and following front fuselage is a cockpit, and postmedian is leveling load and motion space thereof.The leveling load is held a concurrent post by generator set, part fuel oil, weapons and ammunitions etc.; Difference is that weapons and ammunitions are that belly is plug-in.And; Fighter plane needs nap of the earth flight < to comprise power leveling aircraft shown in Figure 15 >; For anticollision and defense sector effect, 45 ° of the necessary upwards knuckles in the rear end of tail-rotor type fighter plane tail pipe < part that big oar can not cover>make tail-rotor and big oar height identical <being convenient to park in the storehouse >.Reason is: 1, the fighter plane bodily form is short and small, to do during nap of the earth flight turn to motor-driven, the easy collision obstacle of tail-rotor.When 2, short and small fighter plane pastes ground or agio flight, the high speed wake flow that big oar blows afloat on ground or the water surface stop that rearward reaching the left and right sides down spreads at a high speed; The tail-rotor of in wake flow, working causes aircraft handling malfunctioning because the velocity contrast of own and wake flow reduces and stall or part stall.

Example 5: the frequency of utilization of general-purpose aircraft is very high, needs very high task comformability.But very high task comformability often causes the individual event performance of aircraft to be not so good as particularly economy of general aviation aircraft.Unique way of solving a problem adopts layering unitized design method exactly, just can significantly improve the economic index of general-purpose aircraft.

Concrete grammar is: adopt the fighter plane Design Pattern, make aircraft have big power, small size, high-intensity characteristics, make aircraft carry out tasks such as general fight, training, scouting, rescue, transportation in economical and efficient ground.The leveling load is done so that the plug-in mode of belly is double in bigger main task storehouse, and the task storehouse will divide size, branch kind, front end to carry fairing.Size and kind according to task when carrying out complex task are selected corresponding with it task storehouse.The own wt and the used load of aircraft can be adjusted according to the needs of task, make aircraft have very high commonality and economy.In emergency circumstances can also lose the task storehouse and avoid the things that some is unwilling to face, for example enemy's situation, blast, heavy rain, voyage are not enough or the like, avoid loss or reduce the loss with this.

Leading the specification in general-purpose aircraft and task storehouse thereof and the specification of existing standard freight container adapt down in government, just can form the land, sea and air three through transport mechanism of dwelling, and the social benefit of up-to-date technology is maximized.

Example 6: toy airplane can fly to get final product, and the valency height is then profitless.Therefore up and down cabin can secure bond together, can save the productive costs of leveling frame like this.

Example 7: the design of power leveling aircraft < Figure 15>is simpler, and whether size, shape and the power supply of confirming time cabin according to user's specific requirement plug-in getting final product.

Figure of description is suggested plans and is just described the necessary scheme of second generation autogyro principle of work, is not equal to second generation autogyro principle of work and can only be applicable to these schemes, for example the said preferred plan of preamble.

It is the theoretical foundation that is used for proving science of the present invention that the principles of science of in research process, finding < is seen the explanation of Figure 15 and Figure 16 >.I and failed call should theory patent < see claims >.

Claims (4)

1. Use the aircraft that second generation autogyro principle of work produces and the common trait of existing aircraft to be: to take off vertically, spot hover and turning to.

   1. adjustment equalizer bar, the front end that it is characterized in that putting on the shelf with undercarriage combines with recliner with an axle combination, rear end.
2. 2. close coupled type axle system is characterized in that the cireular frequency of interior axle and outer shaft running is equal, in the opposite direction.
3. 3. the vertical helical oar is characterized in that whole blades are installed in the same vertical plane surface.
4. 4. gravity adjustment balance control method is characterized in that using the operated by weight aircraft.

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