CN1351944A - Jet airplane - Google Patents
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- CN1351944A CN1351944A CN 01138239 CN01138239A CN1351944A CN 1351944 A CN1351944 A CN 1351944A CN 01138239 CN01138239 CN 01138239 CN 01138239 A CN01138239 A CN 01138239A CN 1351944 A CN1351944 A CN 1351944A
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Abstract
A jet airplane features its flat rectangular fuselage and the longitudinal section and right and left profiles of the fuselage in the shape of standard airwing section, and all these makes it possible for the fuselage to produce lift during flying. The jet airplane is supperiod in no lift produced by the fuselage, hard-to-utilzie lower part space, slender fuselage and excessive winspan. The present invention makes it possible to reduce airplane length, width, manufacture cost, running cost and the required airport. In addition, some safety device to redue the falling speed of airplane may be installed and the landing stage of the airplane may be utilized to reduce accident.
Description
Technical field
The invention belongs to the aeronautical technology field, particularly a kind of fuselage is a flattened rectangular and each elevation profile and side are the aircraft of pacer wing profile shape.
Background technology
Existing passenger and freight transportation machine is being brought into play enormous function in world economy and international association, further develop along with global economic integration exchanges with international community, and aviation passenger and freight throughput rate grows with each passing day, and requires more aircraft input operation.But the airlift on a lot of all over the world now international metropolis airport hastens towards saturation, the airport that has just had an airplane to rise and fall every 2 minutes, the air market that only depends on the increase flight to satisfy constantly expansion requires to be restricted, so the large-scale and ultra-large type passenger and freight transportation machine of a new generation is being studied by several big aircratfsmans in the world.
Learn from magazines such as " aviation knowledge " and Air Internationals, roughly two kinds of the aircraft schemes that they study, " Boeing Co. " releases a kind of full all-wing aircraft type aircraft, and airworthiness makes moderate progress, oil consumption also decreases, and its 800 passenger plane planar dimensions have reached 75 * 75m
2, manufacturing process is complicated in addition.The scheme that the scheme of " European Airbus SAS " and " Russia " release in the international airline exhibition of the last Moscow, substantially be that fuselage length, diameter and the span of existing aircraft are amplified simultaneously, the main cabin changes two layers by one deck, and other is the same with existing aircraft, does not have improvement." European Airbus SAS " 800 passenger plane planar dimensions reach 80 * 80m especially
2860 of Russia's schemes; its span but reaches 88m; a major defect of these large aircrafts is exactly that the span is too big; and span general trend of events necessity asks width and length, runway bearing capacity, hardstand and the aircraft maintenance storehouse of the international airport runway of existing various countries all will enlarge, so current a lot of international airport can't satisfy these super-huge takeoff and landing and operation requirement.
Why cause existing aircraft design-calculated like this so? below we study from existing interior of aircraft structure and seek answer.
Existing airframe section is circular, and the main cabin accounts for full section 60～65% at upper semi-circle, and fuselage section lower half circle accounts for 25～35%, because the bottom surface of lower half circle is the cylinder curved surface, must establishes the floor again and could stack a small amount of goods.There is following shortcoming in this elongate cylindrical shape fuselage: (1) elongate cylindrical shape fuselage is from aerodynamics analysis, fuselage can not produce any lift at all, its effect is the container of manned loading purely, aircraft own wt and passenger-cargo weight, full wing difference of pressure and produce lift and bear up and down when before driving engine promotes, flying by wing, so wing area wants enough greatly, it is very long to cause wing to be encorbelmented, the wing tip amount of deflection is big, also easily produces the vibration of low frequency wing tip.(2) circular design of this fuselage section, make existing aircraft in order to carry more passenger or goods, fuselage diameter and length continue to increase, in addition from existing passenger and freight transportation machine plane, fuselage intersects vertically very thin and weak " criss-cross " with wing, promptly fuselage fineness ratio reach 10: 1～11: 1, and the slenderness ratio in main cabin also reaches about 6: 1～7: 1, resemble a gallery in the main cabin, the stewardess serves apart from very long.It is the middle fuselage place that the main landing gear of bearing aircraft gross weight about 80% owing to fuselage is long must be located at the aircraft total centre of gravity, and when therefore taking off the big angle of attack and rushing to sky, tail almost wipes ground.Afterbody have to be made bending upwards type for this reason, makes the also bad use in that a part of space of tail.(3) design of elongate cylindrical shape fuselage, design to wing also has requirement, it also is flat and grow making existing aircraft wing, the average aspect ratio is also at 10: 1～11: 1, flat wing root and circle cross section intersect at middle fuselage, it is full machine center-of-gravity position herein, yet support aircraft and need three alighting gears at least, the complete relatively machine size of fuselage diameter is less, can not pacify two main landing gears, two main landing gears have to be laid under the wings of an airplane by wing root portion, main landing gear from two side direction middle fuselages pack up to main landing gear compartment be positioned at the middle fuselage lower half circle, so locate to have to add the tire that large space holds alighting gear, thereby broken through the standard size of the standard wing profile of fuselage garden section and wing root, destroyed fuselage circle cross section continuity from the beginning to the end, increased the resistance that advances, wing root portion has been protruded downwards reduced lift.Because complex structure herein, bulk strength is influenced, the manufacturing process complexity.In addition, the prolate wing length of encorbelmenting is very big, and the wing tip amount of deflection is big, also easily produces the vibration of low frequency wing tip.
From above analysis as can be known: the circular design of existing airframe section is to cause aeroplane span big, and wing prolate, fuselage are long, the bad use in underbelly space and tail space, the basic reason of undercarriage project organization complexity and manufacturing process complexity.
Summary of the invention
The objective of the invention is to overcome above-mentioned pacer fuselage section and be that the span that circular design brings is big, weak points such as wing prolate, fuselage are long, undercarriage project organization and manufacturing process complexity, be flattened rectangular and each elevation profile and side are a kind of jet plane of pacer wing profile shape and design a kind of fuselage plane.
For achieving the above object, the present invention adopts following technical scheme: a kind of jet plane, it comprises fuselage 4, wing 27, jet engine 6, drive the cabin 1 of speeding, vertical fin 11, horizontal tail 12,30 and alighting gear 15, wing 27 is installed on fuselage 4 two limits, jet engine 6 is installed on the wing 27, outstanding between two parties layout the in fuselage front driven the cabin 1 of speeding, two vertical fins in fuselage 4 rear portions, 11 supporting horizontal tails 12,30, its special character is: the aspect of described fuselage 4 is a flattened rectangular, fuselage 4 each elevation profile and side are standard wing profile shapes, arrange the landing gear compartment 24 of laying alighting gear 15 for four jiaos of rectangle fuselage 4 bottoms.
The aspect ratio of flattened rectangular fuselage 4 generally is controlled between 1.5: 1～3: 1 and is advisable, and the optimal selection scheme is that aspect ratio is about about 2.5: 1.
Because flattened rectangular fuselage area is big, and its each elevation profile is a standard aerofoil contour shape, and fuselage can produce very big lift, so wing area can reduce, length between its span (width of aircraft) is approximately suitable with fuselage 4 length, and its span length is 60% of existing aircraft approximately.Also favourable passenger's turnover and emergency evacuation.
Wing 27 is installed in machine ceiling hold 5 both sides at fuselage 4 tops, and hatch door 19 and cabin window 21 are offered in fuselage 4 sides, and hatch door 19 and cabin window 21 can not stop passenger's sight line like this below wing 27, makes the passenger can fully view and admire the outer beautiful scenery of machine.
The fuselage head space intercropping machine ceiling hold 5 that fuselage elevation profile middle part is more unnecessary than passenger room 8 clear height, with opportunity ceiling hold 5 can be used as machine top integral tank, the also approximate wing canonical profile of its elevation profile shape, positive good utilisation is as the supporting structure of wing 27.Because the fuselage side also is the plane, therefore wing 27 wing roots dock with fuselage is smooth naturally, simple in structure, do not destroy fuselage and wing root standard shape herein yet, resistance is less when therefore flying, also existing relatively aircraft wing root of manufacturing process and fuselage intersection are simply many, favourable minimizing dead load and manufacturing cost.The space of machine ceiling hold 5 is very big, can be aircraft and loads abundant fuel oil.
Between wing 27 and the jet engine 6, and the rotating shaft 7 that driving engine 6 is rotated is installed between horizontal tail 30 and the jet engine 6 fixedly; Both but level was jet backward to make jet engine 6, it is jet downwards also can to go to the upright position, is the balance aircraft for the aircraft of the present invention that has only two driving engines when the aircraft vertical landing, and fuselage 4 rear portions are equipped with a leveling turbofan 10, the moment of torsion that changes in order to balance fuselage anteversion and retroversion.
The upper surface of fuselage 4 and wing 27 has several to launch parachute compartment 35, lay the controlled pneumatic series connection parachute 38 that launches in each cabin, there is the flat air blast nozzle 34 of row's fine setting at fuselage 4 base plates, 17 front and rear edges and wing 27 two ends simultaneously, and these devices are urgent rescue and vertical landing equipment therefor.
Structure with existing passenger and freight transportation machine is compared with performance, and the present invention has following advantage:
(1). because the wing fuselage of flattened rectangular can produce lift in-flight, carry under capacity or the cargo capacity condition equal, it is about about 40% that the length and width of aircraft of the present invention and Gao Douke reduce, and floor area reduced 50% approximately when aircraft was parked, and saved fuel oil about 15%.
(2). four alighting gears directly bear the aircraft gross weight, and are stressed even, make full use of standard aerofoil contour leading edge and the trailing edge space shorter than the people and do landing gear compartment, and landing gear compartment does not destroy the standard profile of fuselage and wing, and manufacturing process is simple, and flight resistance is little.
(3). the fuselage base plate is smooth, fine arrangement passenger seat and stack goods, the free from worry practicality in rectangle main cabin, stewardess's service radius is short, the efficiency of service height.The fuselage base plate is smooth, when aircraft landing, can obtain bigger ground and imitate, favourable take off to increase rise up into, slow down, shorten ground run distance during also favourable aircraft landing.
(4). for the very high aircraft of security requirement, the present invention installs rotatable jet driving engine downwards at wing two ends, " air cushion encloses " established in fuselage base plate surrounding, also is provided with " leveling turbofan ", " finely tuning flat air blast nozzle " and devices such as " launching the series connection parachute ".Improved the safety control of passenger and aircraft greatly.
In sum, aircraft overall structure layout of the present invention is simple, reasonable, compact, each position shape criteria, no redundant space in the machine, outer the no unnecessary prominent form of machine, flight resistance are little, therefore existing relatively aircraft, and airworthiness can be better, operate simple and easy, simplified manufacturing process, cost economic adds that passenger traffic or shipping function are single-minded, service management is convenient, and operating cost is lower.
Description of drawings
Fig. 1 is the vertical profile comparison diagram of existing aircraft under aircraft of the present invention and the equal load;
Fig. 2 overlooks the profile comparison diagram for aircraft of the present invention and the existing aircraft under the equal load;
Fig. 3 is the air flow line comparison diagram of fuselage transversal surface when landing of aircraft of the present invention and existing aircraft;
Fig. 4 aircraft plan structure of the present invention scheme drawing;
Fig. 5 aircraft of the present invention is looked up structural representation;
Fig. 6 is the vertical sectional structure chart of aircraft of the present invention;
Fig. 7 is an aircraft plane sectional structure chart of the present invention;
Fig. 8 is the horizontal sectional structure chart of aircraft of the present invention;
But Fig. 9 overlooks the profile scheme drawing for ultra-large type vertical landing aircraft of the present invention;
Figure 10 is the vertical sectional structure chart of the double-deck main cabin aircraft of ultra-large type of the present invention;
Figure 11 is an airplane emergency vertical landing constitution diagram of the present invention;
Figure 12 is airplane emergency landing state plane scheme drawing of the present invention;
Figure 13 airplane emergency short distance of the present invention landing state figure.
The following P of the title of each position and parts among Fig. 1 to Figure 13---expression center of gravity of airplane position 18, seat 1, drive the cabin 19 of speeding, hatch door 2, Avionics Equipment Bay 20, column 3, sanitary accomodation 21, cabin window 4, fuselage 22, tail fuel tank 5, machine ceiling hold 23, undercarriage door 6, driving engine 24, landing gear compartment 7, rotating shaft 25, stair 8, passenger room 27, wing 9, boot compartment 28, aileron 10, leveling turbofan 29, wing flap 11, vertical fin 30, fixedly horizontal tail 12, activity horizontal tail 31, elevating rudder 13, yaw rudder 32, crown luggage locker 14, tail wing flap 33, air cushion plate washer 15, alighting gear 34, finely tune flat air blast nozzle 16, kitchen 35, launch parachute compartment 17, fuselage base plate 38, launch the series connection parachute
The specific embodiment
At first in conjunction with principle of design of the present invention, theoretical basis of the invention process and implementation result are described below.
The present invention is improved from the aircraft total arrangement according to aerodynamic principle.Now compare example research with U.S.'s " Boeing 777 passenger planes ".
At first imagine the space that will have the cargo hold that is unwilling to do very much under the base plate of main cabin in the airframe circle cross section now and remove, the fuselage height just can reduce about 40% like this.Then the existing elongated fuselage of aircraft is cut into two sections, again these two sections fuselage combined cost invention fuselage germules, the aspect ratio on fuselage then of the present invention plane can become 2.5: 1 by original fuselage at 10: 1, the passenger room plane also became 1.5: 1 by former 6: 1, obviously passenger room 8 is no longer as a gallery, and conference hall of picture, if group's chartered plane travelling also can be opened conference during the journey, be given a report in the cabin.Kitchen and sanitary accomodation needn't longitudinally divide several places simultaneously, but centralized arrangement has shortened the distance that the stewardess walks, and has alleviated their work capacity.
Flattened rectangular fuselage 4 aspect ratios generally are controlled between 1.5: 1～3: 1 is advisable, about 2.5: 1 of optimal aspect.Again the fuselage elevation profile is made into standard wing profile form again, fuselage leading edge slyness then, the fuselage trailing edge is sharp-pointed, the oblique point of fuselage trailing edge just in time is tail wing flap l4, when taking off and land in order to increase lift.Because of leading edge with by trailing edge place insufficient height, bad arrangement seat, but the space of four jiaos on rectangle fuselage also just in time is used to do landing gear compartment 24.Therefore alighting gear is enough laid in these landing gear compartment spaces, and can not break through fuselage standard section scope, and very aerodynamic forms the condition of laminar flow, and resistance is less during flight, and its structure standard, and manufacturing process is also simple.
Because flattened rectangular fuselage area is big, fuselage can produce very big lift, wing area can reduce more, after deliberation and calculate the wing planform of " Boeing 777 passenger planes ", its wing wing root is relatively big and thick, and wing tip is little and thin, if remove 1/2 length of encorbelmenting to the wing root direction from wing tip, wing area only reduces about 1/3, therefore with regard to unit area, the air flow line variable density is big in wing root portion, and difference of pressure is also big up and down, the lift nature of its generation is bigger than the lift of wing tip place unit area, through calculating that wing cuts down 1/2 length of encorbelmenting from wing tip, though the corresponding minimizing 1/3 of wing area, and lift only reduces about 1/4.Become flattened rectangular wing body horizontal area of the present invention and Boeing 777 approximately to equate as the preceding aircraft general improvements of chatting at the fuselage area under the condition on year-on-year basis, so the lift that fuselage of the present invention produces not only can remedy 1/4 of airfoil lift minimizing, should remedy the back and also have a lot of lift more than needed.
The wing of the present invention length of encorbelmenting is only got original aircraft by 1/2 of wing root portion, and is promptly constant by wing root portion each several part size and thickness.Therefore, wing of the present invention seems more sturdy, has kept lift 3/4 like this under equal flying speed, and it is few that the integral wing tank capacity is reduced.Wing of the present invention is short relatively, and wing rigidity is big and thick, can exempt the wing phenomenon of shaking, and also 7 driving engines 6 that rotate become possibility in order to install around the shaft at the wing tip place.
Through above these modifications to " Boeing 777 passenger planes " plane, fuselage 4 length of the present invention have only existing aircraft half, fuselage 4 is wide but to be wide 2 times of existing fuselage, add wing of the present invention encorbelment length for existing aircraft half.Consider to drive outstanding fuselage one segment distance in the cabin of speeding again, tailplane is again than fuselage trailing edge slow astern segment distance, and two aspects of the length overall of aircraft of the present invention and the span all reduce about 40% than the length overall and the span of existing " Boeing 777 passenger planes " after the COMPREHENSIVE CALCULATING.The height of fuselage 4 also reduces about 40% than existing aircraft, and that the total floor area of aircraft reduces is about 50%, so aircraft opposite planar compactness of the present invention is not thin and weak criss-cross.Can but this shape fly up into the sky? as long as we observe the ancestors of present generation aircraft---kite just can understand that kite is to originate from China before more than 2000 year, and by universally acknowledged for being human artificial aircraft the earliest.China's kite among the people is in different poses and with different expressions, has squarely, has circularly, has leg-of-muttonly, also has the picture butterfly, flying bird, various animals, also have picture Sun Wukong or the like, but under their wind effect on high, can both steadily let fly away.Since these various kites can both balance be let fly away on high, existing in addition B-2 shape bomber made in U.S.A, F117 type scout, " criss-cross " that F22 fighter plane made in U.S.A neither be thin and weak.According to aerodynamics analysis the present invention, can infer that fully flattened rectangular wing body jet aeroplane of the present invention can steadily fly blue sky again.
Existing aircraft is three alighting gears, because fuselage is tall and thin, two main landing gears of Zhi Chengyue 80% loading can not be placed on the fuselage, generally is arranged in wing by about 1/3 place of root.The aircraft loading reaches fuselage earlier, reaches wing again, is passed to ground by main landing gear again, so the wing root must bear very big moment of flexure.Aircraft flies to lay up behind the sky, main landing gear again folding and unfolding in the landing gear compartment of wing root and middle fuselage intersection.The nose-gear position is stressed little by head, and the major control aircraft turns to ground motion.
Fuselage base plate of the present invention all on a plane, is therefore arranged passenger seat 18 and stack goods well than existing aircraft from the head to the tail.Passenger room is arranged in the part broad in the middle position that clear height in the fuselage elevation profile meets human body height needs.Fuselage 4 rear portions, free height is lower than people's height, and past more tail height is more little, is zero until tail.Therefore the present invention will lean on the higher local arrangement hand baggage of passenger room 8 clear height cabin 9, and be followed successively by tail fuel tank 22 and tail wing flap 14 backward, and several parts are had a role to play, and have made full use of these spaces, and not waste is also very practical.The forward edge spatial altitude of fuselage is higher than tail, can utilize and arrange to do Avionics Equipment Bay 2.The smooth picture city motor bus of passenger room 8 two sides, bigger than existing aircraft two side circular arc lateral space, the passenger takes advantage of seat comfortable.For middle part, the fuselage elevation profile fuselage head space intercropping machine ceiling hold 5 more unnecessary than passenger room 8 clear height, with can be used as the also approximate wing canonical profile of its elevation profile shape of machine top integral tank opportunity on the ceiling hold, positive good utilisation is as the supporting structure of wing.Because the fuselage side also is the plane, therefore wing 27 wing roots dock with fuselage is smooth naturally, simple in structure, do not destroy fuselage and wing root standard shape herein yet, resistance is less when therefore flying, also existing relatively aircraft wing root of manufacturing process and fuselage intersection are simply many, favourable minimizing dead load and manufacturing cost.The space of machine ceiling hold 5 is very big, can be aircraft and loads abundant fuel oil.
Though fuselage of the present invention 4 does not have under the base plate of existing airframe circular cross sections main cabin the not cargo space of good utilisation, enough space shipment passengers' luggage is at random arranged at the boot compartment 9 of fuselage afterbody.Transporting on an equal basis when carrying capacity, it is about 20% that the total load of aircraft of the present invention can reduce, favourable minimizing wing area, dead load and aircraft cost.Then go to finish as for the shipping function by special air truck, function singleness, airline company's operation management is also convenient.
The fuselage two side faces is smooth as the city motor bus side, fine door 19 and the cabin window 21 of opening the cabin, and more favourable cargoliner is opened the gate handling goods.For attractive in appearance and increase side intensity, lateral surface also can be made slightly outwards slick and sly giving prominence to.Because wing 27 hangs to two sides from the fuselage top, passenger room institute door window is side under the wings of an airplane all, and during the journey, people can see the ground scene that ground is magnificent from window, can't be blocked sight line by wing, the also favourable quick emergency evacuation of people in unusual accident.For super-huge passenger plane two layers of main cabin are arranged, two layers of cabin door plane projection alignment up and down, the vehicle-mounted special-purpose gangway ladder in favourable airport is evacuated two layers of passenger simultaneously.Fuselage base plate lower surface is the plane, and when taking off with landing distance ground when very near, the air cushion of fuselage and ground effect effect are stronger than existing airframe circle cross section, favourable rising and falling.
For large-scale and super-huge passenger and freight transportation machine, in order to reduce the engine room structure span, thereby reduce dead load and save cost, can establish row's aluminum alloy column 20 at the cabin longitudinal centerline, these columns arrange passenger seat 18 influences not too big to passenger room, but cost can reduce.Certainly for the air truck of the relatively large equipment of transportation, the centre does not set up post passable yet, and just cost wants height a bit.
Wing of the present invention stretches out to two limits at the passenger room top, and the wing of existing aircraft is to stretch to two limits from the passenger room floor below, so driving engine 6 is hung face under the wings of an airplane by the same manner, then the engine installation position of aircraft of the present invention exceeds the distance of passenger room clear height than the engine location of existing aircraft, and four alighting gears are directly installed on four jiaos under the fuselage base plate, therefore main landing gear length of the present invention can reduce, and does not more exist engine case to wipe ground-surface problem.
The present invention can make large, medium and small type aircraft, be fit to do the passenger and freight transportation machine of medium-sized (60～300), be more suitable for doing large-scale (300～600) and super-huge (600～1000 s') passenger and freight transportation machine, simultaneously also can make fighter plane, this paper discusses with passenger plane, and for air truck as long as the equipment such as passenger seat and corresponding kitchen and sanitary accomodation of not establishing in the cabin have just become air truck, only need good bomb of reasonable Arrangement or guided missile to get final product for fighter plane.
Because large-scale and super-huge passenger plane personnel are many, in case Casualties are heavy-losses arising from death and wounds for the personnel that have an accident.For accident disaster degree being reduced to minimum, for passenger plane, the present invention is special to consider that awing aircraft can't fly to the landing at the airport that closes on most in case run into certain accident, and perhaps aircraft itself breaks down and can not far fly, and aircraft have to be saved oneself.The present invention also emphasis consider passenger plane is designed in case of emergency can short distance or vertical landing, because of the relatively thick shape of wing of the present invention, the wing tip place area of section also bigger, have ready conditions engine shaft 7 is installed, both but level was jet backward to make jet engine 6, it is jet downwards also can to go to the upright position, directly goes up to lift airframe and realize the aircraft vertical takeoff and landing.This just requires only to adorn the aircraft of two driving engines, two driving engine center of gravity lines must by or near the center of gravity of whole aircraft, a little bias can produce some moments of torsion verts fuselage forward or backward, the present invention installs a leveling turbofan 10 at fuselage afterbody and pushes away fuselage for this reason, because this leveling turbofan is away from the center of gravity of airplane, " though title stick together little pressure very heavy " or cry " art is good for strength ", the special-purpose moment of torsion that it comes balance fuselage 4 front and back to vert.
As for the left and right directions balance, the fuel charge of two jet engines about control then, two engine thrusts are identical to come balance thereby control.These all are the coarse balance means, for more stable must fine setting, also need to regulate the size of jet amount with regard to may command fine setting moment in that some finely tune flat air blast nozzle 34 by airframe front and rear edge and two wing wing tip edge placement for this reason, make fuselage more steady when landing.
These Self-saving equipment for airplane measures have been arranged not enough, reliable for greater safety, the present invention launches parachute compartment at fuselage and uniform several of upper surface of the airfoil, and is provided with air cushion baffle plate 33 at the fuselage lower surface by four limits, handles these air cushion baffle plates by hydraulic actuator.These air cushion baffle plates are pressed on the fuselage base plate skeleton and make aircraft skin at ordinary times.When aircraft breaks down, in the time of need promptly saving oneself, except that driving engine 6 transfers jet earthward, leveling turbofan 10 to and finely tunes flat air blast nozzle 34 system's inputs, drives the cabin 1 of speeding and handle and put down all air cushion baffle plates 33 below the fuselage, these air cushion baffle plates 33 and undercarriage door 23, tail wing flap 14 is formed " air cushion encloses " jointly, and air is bigger to the shock damping action of fuselage when having " air cushion encloses " aircraft to fall.Open all parachute hatchcovers then and launch series connection parachute 38, under these measure combineds action, can make the passenger plane that breaks down select level land or smooth farmland landing nearby, if can find the highway wideer then to take the short distance landing better, in the hope of safety that ensures all passengers, crew and aircraft or the degree that can reduce disaster at least to greatest extent than fuselage.
For super-huge passenger plane, because of four driving engines being housed altogether, notice that wing and two sustainer, main engines should move forward as far as possible at wing 27 and horizontal tail 12,30 2 ends, wing is made forward swept for this reason, makes it farther from the center of gravity of airplane, so that four driving engine loads are more approaching.Because of there being four driving engines to be distributed in the preceding left side of center of gravity of airplane P, the preceding right side and a left side, back, right 4 points in back, so do not need " leveling turbofan 10 " to be installed at the fuselage tail.But other measure, as " finely tuning flat air blast nozzle 34 ", " air cushion encloses " and " launching series connection parachute 38 " still the same need the setting with the big-and-middle-sized aircraft of adorning two driving engines.
Fault that fails to lay down in four alighting gears occurring, also can handle like this, clear-cut four alighting gears do not put down, because of fuselage base plate 17 of the present invention is planes, the landing so can the fuselage base plate directly contact to earth, but note selecting dense growth crops or just ploughed soon, the farmland of loosing soil lands.Slow down when landing impulsive force to the fuselage base plate, thus protection passenger and crew's safety.
Describe performance of the present invention in detail in conjunction with Figure of description more below:
From Fig. 1, Fig. 2 as can be known: the captain of aircraft of the present invention, the span and fuselage height all reduce about 40% than existing aircraft, and the aircraft deadweight reduces 15～20% approximately, and aircraft is parked floor area and is reduced 50% approximately.Fuselage 4 width of the present invention are wide two times of existing aircraft, and it is about 20% that the space spaciousness main cabin in, cross sectional area on average increase, but do not have the not space of good utilisation, existing second garden of aircraft passenger compartment base plate, comprehensive space utilization efficient raising.Passenger plane or cargo aircraft function can be single-minded, the management of convenient airline company.
As can be seen from Figure 3: to the air flow line analysis of two kinds of fuselage transversal surfaces when the aircraft landing as can be known, fuselage 4 suffered air resistance of the present invention are bigger, and the speed of favourable minimizing aircraft landing shortens sliding distance of running on adrm.No matter take off and still land, the ground effect effect of the flat fuselage of the present invention is all stronger, both favourable taking off, also favourable aircraft landing.If set up air cushion and enclose, then air cushion and the ground effect effect during aircraft landing is stronger.
From Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8 as can be known: fuselage 4 of the present invention is a flattened rectangular, and its each longitudinal profile is the wing profile shape of standard, and fuselage itself just can produce lift awing like this, because the fuselage area is big, so lift is also very big.
Drive the cabin 1 of speeding and be positioned at fuselage 4 leading edge centers and outstanding forward, make driver's seat open.Wing 27 stretches to two sides from the arched top of fuselage 4, driving engine 6 still can be hung below wing 27 or is installed in wing 27 two ends as existing aircraft, wing 27 trailing edges are provided with aileron 28 and wing flap 29, and fuselage 4 rear portions are provided with two vertical fins 11 by two sides, and each vertical fin 11 all is with yaw rudder 13.Two vertical fins support long horizontal tail, and wherein activity horizontal tail 12 is between two vertical fins 11, and it can rotate around self rotating shaft, and encorbelmenting in vertical fin 11 outsides has fixedly horizontal tail 30 and elevating rudder 31.
For short distance and vertical takeoff and landing (VTOL) medium or large passenger plane, in order to improve passenger safety or to reduce the disaster degree when the accident as far as possible.Install and 7 to turn to jet driving engine 6 around the shaft at more sturdy solid wing 27 2 ends of the present invention.Two driving engine lines should be tried one's best near center of gravity of airplane P, and slightly forward.When the aircraft vertical landing, driving engine 6 is jet down, regulates the left and right sides balance of the thrust may command aircraft of these two driving engines.The thrust of then controlling leveling turbofan 10 as for the balance before and after the aircraft realizes.Fuselage base plate 17 4 limits are provided with the air cushion baffle plate 33 that is driven by hydraulic actuator.Open downwards simultaneously when air cushion plate washer 33 and undercarriage door 23 and tail wing flap 14, then form " air cushion encloses ", the air resistance when strengthening aircraft landing, favourable minimizing aircraft falling speed and kinetic energy with the sheet rubber sealing each other.If it is open the flat air blast nozzle 34 of fine setting again, then more steady during aircraft landing.
From Fig. 9, Figure 10 as can be known: when aircraft of the present invention will be made super-huge passenger plane (600～1000), because of the passenger is many, fuselage length and width, height were all corresponding very long, the passenger room 8 in the fuselage 4 can be divided into two layers, were communicated by stair 25 between two layers of passenger room 8.Aircraft is always great, need adorn four driving engines 6 and could advance aircraft.Super-huge in addition birdman is a lot, in case airplane crash takes place, disaster is too big.Be the protection passenger safety, the present invention is installed in wing 27 and fixing horizontal tail 30 2 ends respectively with four driving engines 6, and can be around the shaft 7 rotate jet down.In order to make four driving engine load-bearing more even, the present invention is designed to forward swept with wing, and two sustainer, main engine 6 positions are moved forward from center of gravity of airplane P one segment distance as far as possible.Simultaneously jet downwards when four driving engines 6 like this, and the air cushion of opening fuselage base plate 17 lower ends encloses and finely tunes flat jet system, realizes vertical landing by these device combineds action, and the power of jet engine 6 must be enough greatly certainly.Because of there being four jet engines to be distributed in four angles of center of gravity of airplane P, as long as regulating the downward thrust size of four driving engines, computer just can realize the vertical landing of aircraft, keep fuselage steady when descending and needn't establish leveling turbofan 10.If after taking said apparatus, the aircraft descending speed is still too big,, realize safe falling for guaranteeing Passenger On Board and aircraft safety, can restart that launching parachute system further slows down the aircraft falling speed.
When being equal to existing aircraft for safety requirements certainly, four driving engines of the double-deck passenger plane of ultra-large type of the present invention still can be hung under the wings of an airplane just as existing aircraft, and wing still adopts the swept-back, can not vertical landing, still adopt airport sliding race mode landing, can save and make and operating cost.
From Figure 11, Figure 12, Figure 13 as can be known: if aircraft has driving engine 6 disaster shutdowns or other unforeseeable faults midway suddenly in cruising flight, and aircraft is all far from the most contiguous airport, aircraft is difficult to fly to contiguous landing at the airport, at this moment, must make aircraft transfer the forced landing state to.
Close another driving engine 6 in working order for this reason earlier, make aircraft enter deceleration gliding flight state, put down aileron 28, wing flap 29 and tail wing flap 14, and activity horizontal tail 12 is gone to and the help deceleration of fuselage 4 upright positions.Drop hatch door 23 and all air cushion baffle plates 33 are formed " air cushion encloses " with tail wing flap 14 again.Glide simultaneously at aircraft, go to down or, put down whole alighting gears 15 towards the front lower place closing those driving engine 6 spouts of still getting well.At this moment open above the aircraft all that remove near intact driving engine again and launch parachute compartment 35, launch series connection parachute 38 then automatically.It is jet down meanwhile also to open intact driving engine 6 gradually.Unite by above these devices and to slow down the aircraft speed of landing forward and downwards, drive at last that the person of speeding is careful selects the landing slowly of hithermost level land, highway or smooth farmland, in the hope of protecting passenger, crew and aircraft safety.
Certainly since aircraft weight big, take above these measures after, the aircraft falling speed may be still bigger, accident also can take place unavoidably, but owing to there is above measure can significantly reduce aircraft falling speed and kinetic energy, can make accident disaster degree reduce to minimum at least as far as possible.
Because of 4 driving engines are arranged, generally two et out of orders can not arranged simultaneously as for super-huge passenger plane, land or look for nearest landing at the airport in the destination of still should flying to.Just in case two driving engine simultaneous faultss or other unpredictalbe very accident occur, also can take to drop to smooth ground with the much the same emergency schedule of medium or large passenger plane that only possess two driving engines.
As for big-and-middle-sized and super-huge air truck, because of persons on board are few, can assemble corresponding apparatus and urgent rescue device as required, as driving engine 6 being hung side under the wings of an airplane, adopt the sliding landing mode of running in airport as existing aircraft, in the hope of saving cost and operating cost.
Need to prove: for one skilled in the art, under the prerequisite of inventive principle, can also make some improvement and distortion to the present invention, this belongs to protection scope of the present invention equally.
Claims (10)
1, a kind of jet plane, it comprises fuselage (4), wing (27), jet engine (6), drives the cabin of speeding (1), vertical fin (11), horizontal tail (12,30) and alighting gear (15); Fuselage (4) two side faces is installed wing (27), jet engine (6) is installed on the wing (27), outstanding between two parties layout the in fuselage (4) front driven the cabin of speeding (1), fuselage (4) two vertical fins in rear portion (11) supporting horizontal tail (12,30), the aspect that it is characterized in that described fuselage (4) is a flattened rectangular, and each elevation profile of fuselage (4) and side are standard wing profile shapes, arrange for four jiaos of fuselage (4) bottom and lay the landing gear compartment (24) of alighting gear (15).
2, a kind of jet plane according to claim 1 is characterized in that: the aspect ratio of described rectangle fuselage (4) is 1.5: 1-3: 1, and optimal aspect is about 2.5: 1.
3, a kind of jet plane according to claim 1 and 2 it is characterized in that the length between the span is suitable with fuselage (4) length, and span length is 60% of described existing aircraft under identical load.
4, according to claim 1 or 2 described a kind of jet plane, it is characterized in that: wing (27) is installed in machine ceiling hold (5) both sides at fuselage (4) top, hatch door (19) and cabin window (21) are offered in fuselage (4) side, and hatch door (19) and cabin window (21) are in wing (27) below.
5, a kind of jet plane according to claim 3, it is characterized in that: the rotating shaft (7) that driving engine (6) is rotated is installed between wing (27) and jet engine (6), the rotating shaft (7) that driving engine (6) is rotated fixedly also can be installed between horizontal tail (30) and the jet engine (6) simultaneously.
6, a kind of jet plane according to claim 1 and 2 is characterized in that: leveling turbofan (10) is equipped with at fuselage (4) rear portion.
7, a kind of jet engine according to claim 5 is characterized in that: the upper surface of fuselage (4) and wing (27) launches parachute compartment (35), lays the controlled pneumatic series connection parachute (38) that launches in each cabin.
8, a kind of jet plane according to claim 6 is characterized in that: base plate (17) front and rear edge of fuselage (4) and the lower surface of wing (27) two ends have row's fine setting flat air blast nozzle (34).
9, a kind of jet plane according to claim 4 is characterized in that: the horizontal tail (12) on the vertical fin (11) is rotatable horizontal tail; Hatch door (19) on the fuselage (4) is for being rotated downward to be the movable door of gangway ladder.
10, a kind of jet plane according to claim 9 is characterized in that: the described following air cushion baffle plate (33) of fuselage base plate (17) and undercarriage door (23), the common composition of tail wing flap (14) " air cushion encloses " of being positioned at.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01138239 CN1351944A (en) | 2001-11-30 | 2001-11-30 | Jet airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01138239 CN1351944A (en) | 2001-11-30 | 2001-11-30 | Jet airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1351944A true CN1351944A (en) | 2002-06-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01138239 Pending CN1351944A (en) | 2001-11-30 | 2001-11-30 | Jet airplane |
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| Country | Link |
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| CN (1) | CN1351944A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101213130B (en) * | 2005-06-30 | 2010-05-19 | 空中客车法国公司 | Device for fixing a seat rail on a floor, and aircraft equipped with such a fixing device |
| CN101804865A (en) * | 2010-03-16 | 2010-08-18 | 北京航空航天大学 | Small multi-purpose unmanned aerial vehicle |
| WO2010099730A1 (en) * | 2009-03-04 | 2010-09-10 | Liu Shiying | Amphibious large aircraft without airstairs |
| CN101312875B (en) * | 2005-11-21 | 2010-09-29 | 空中客车法国公司 | Landing gear casing provided with a box structure |
| CN102336269A (en) * | 2011-08-10 | 2012-02-01 | 彭红云 | Vertical taking off and landing (VTOL) technology of full-thrust vertical taking off and landing vector fighter airplane |
| CN102955478A (en) * | 2012-10-24 | 2013-03-06 | 深圳一电科技有限公司 | Unmanned aerial vehicle flying control method and unmanned aerial vehicle flying control system |
| CN103303474A (en) * | 2010-03-16 | 2013-09-18 | 北京航空航天大学 | Small-size multi-purpose unmanned aerial vehicle |
| CN103770937A (en) * | 2014-03-03 | 2014-05-07 | 武汉蓝天翔航空科技有限公司 | Airplane capable of vertically taking off and landing with short distance |
| CN103786881A (en) * | 2014-02-28 | 2014-05-14 | 武汉蓝天翔航空科技有限公司 | Tilting rotor wing helicopter |
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2001
- 2001-11-30 CN CN 01138239 patent/CN1351944A/en active Pending
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101213130B (en) * | 2005-06-30 | 2010-05-19 | 空中客车法国公司 | Device for fixing a seat rail on a floor, and aircraft equipped with such a fixing device |
| CN101312875B (en) * | 2005-11-21 | 2010-09-29 | 空中客车法国公司 | Landing gear casing provided with a box structure |
| EP2404826A4 (en) * | 2009-03-04 | 2014-04-02 | Shiying Liu | Amphibious large aircraft without airstairs |
| WO2010099730A1 (en) * | 2009-03-04 | 2010-09-10 | Liu Shiying | Amphibious large aircraft without airstairs |
| EP2404826A1 (en) * | 2009-03-04 | 2012-01-11 | Shiying Liu | Amphibious large aircraft without airstairs |
| US8453963B2 (en) | 2009-03-04 | 2013-06-04 | Shiying Liu | Amphibious large aircraft without airstairs |
| CN103303474A (en) * | 2010-03-16 | 2013-09-18 | 北京航空航天大学 | Small-size multi-purpose unmanned aerial vehicle |
| CN101804865A (en) * | 2010-03-16 | 2010-08-18 | 北京航空航天大学 | Small multi-purpose unmanned aerial vehicle |
| CN102336269A (en) * | 2011-08-10 | 2012-02-01 | 彭红云 | Vertical taking off and landing (VTOL) technology of full-thrust vertical taking off and landing vector fighter airplane |
| CN102336269B (en) * | 2011-08-10 | 2015-04-29 | 彭红云 | Full-thrust vertical taking off and landing vector fighter airplane |
| CN102955478A (en) * | 2012-10-24 | 2013-03-06 | 深圳一电科技有限公司 | Unmanned aerial vehicle flying control method and unmanned aerial vehicle flying control system |
| CN102955478B (en) * | 2012-10-24 | 2016-01-20 | 深圳一电科技有限公司 | UAV flight control method and system |
| CN103786881A (en) * | 2014-02-28 | 2014-05-14 | 武汉蓝天翔航空科技有限公司 | Tilting rotor wing helicopter |
| CN103770937A (en) * | 2014-03-03 | 2014-05-07 | 武汉蓝天翔航空科技有限公司 | Airplane capable of vertically taking off and landing with short distance |
| CN103770937B (en) * | 2014-03-03 | 2016-06-22 | 武汉蓝天翔航空科技有限公司 | The aircraft of vertical and STOL |
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