CN1137998A - Finless and vertical landing wing jet aero-plane - Google Patents
Finless and vertical landing wing jet aero-plane Download PDFInfo
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- CN1137998A CN1137998A CN 95102539 CN95102539A CN1137998A CN 1137998 A CN1137998 A CN 1137998A CN 95102539 CN95102539 CN 95102539 CN 95102539 A CN95102539 A CN 95102539A CN 1137998 A CN1137998 A CN 1137998A
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Abstract
The improved jet aircraft without wings and being able to take off and land vertically features technically that the longitudinal cross-section of its body is in the shape of cross-section of standard wing and its wing is omitted as lifting force is generated by its body on flying. Rotational primary jet engine is installed to each of both sides of body and rotational secondary jet engine or culvert-type tail wing is installed at the tail of its body. Its advantages include small size, light dead weight, saving fuel and high reliability.
Description
The present invention a kind ofly carries out improved jet plane from the aircraft general design.
Along with developing rapidly of world economy and international association, aviation passenger and freight throughput rate grows with each passing day, this just requires more aircraft to put into operation, but since the aerodrome capacity of a lot of economically developed international cities in the world be tending towards Eat and, depending alone increases the increase that flight satisfies the passenger and freight throughput rate and is restricted, require aircraft unit load carrying ability (passenger capacity or cargo capacity) to increase, therefore large transport airplane of new generation is all being studied by many economically developed industrial states now.At present main research is by way of being to strengthen the fuselage section, and the individual layer main cabin changes double-deck main cabin into, lengthened fuselage, the increasing span etc.So, the increase of aircraft size has proposed new higher requirement to the airport conversely, promptly must strengthen the length and the width of airfield runway, the bearing capacity that live load is worn when improving runway to aircraft takeoffs and landings, " international airline " magazine introduction according to Beijing " aviation press " publication, the design plan of 600 new large aircraft plans (NLA) of Boeing Co., double-deck main cabin, aircraft floor area on the flight runway is 80 * 80 sq ms.Like this certainly will be very strict to the airport infrastructure requirement, most of international airport, the world does not satisfy this requirement at present.Existing in addition passenger/cargo transport, fuselage is elongated fusiformis, the fuselage plane of structure is disconnected to be garden shape or ellipse garden shape, therefore the cabin is all very elongated, under the engine room floor space of arching section not convenient with fuselage from aerodynamic viewpoint analysis, itself can not produce lift, pure broken be carrier, aircraft full weight (aircraft deadweight and load) can only be born by the lift that is installed on the wing or the jet engine of fuselage afterbody is produced by wing when promoting aircraft flight.Its chamber of sailing is located at fuselage foremost, and the control flight status is to pay the wing by the manipulation wing to finish with the horizontal elevating rudder and the vertical direction rudder that are installed in tail.
The present invention is according to aerodynamic principle, at first fuselage is shortened, widens and flattens, make the aspect ratio or the beam length ratio of fuselage be controlled at 1: 2 with interior flat rectangular shape, flat like this cabin plan area is big, and arranging the passenger seat still is that handling goods is all very convenient.The shape of Aircraft Standard wing profile has been adopted in elevation profile that the more important thing is the flattened rectangular fuselage, and when aircraft flew forward, the difference of pressure that the fuselage upper and lower surface produces and form the weight that life force can support aircraft was so can cancel the wing of fuselage two sides.Because fuselage two sides do not have wing, can be easily the center-of-gravity position of fuselage two sides or slightly forward facing position rotatable main turbofan jet engine is installed, this jet engine level when normal flight promotes aircraft flight.When taking off and land, it is jet that jet engine can rotate to vertically jet earthward or oblique ground, can realize the vertical takeoff and landing (VTOL) or the short take-off and landing (STOL) of aircraft.
During certainly owing to the aircraft vertical takeoff and landing (VTOL), the standard of fuselage flying speed does not have or is very little, therefore can not lean on operating aircraft tailplane elevating rudder or vertical tail aspect rudder to control the state of equilibrium of aircraft, must also install rotatable jet inferior turbofan jet engine downwards or the ducted tail rotor of comparison helicopter comes the sweptback moment of balance fuselage at tail.
The alighting gear of aircraft both can have been installed the sort of alighting gear of autogyro, and the alighting gear of general aircraft also can be installed.The former can only vertical takeoff and landing (VTOL), but and both vertical takeoff and landing (VTOL) of the latter, also can be as aircraft running take off and landing on airfield runway like that.
If the power of the rotary jet engine of aircraft is regardless of the primary and secondary size, and level do not disturb (as Fig. 1, Fig. 2, Fig. 5) when jet mutually, and then several rotary jet engines can be distributed on fuselage two sides or fuselage afterbody.Promoting aircraft simultaneously when the aircraft horizontal flight flies forward.When aircraft takeoffs and landings, lift aircraft on simultaneously.Quantity and watt level as for jet engine are then determined according to weight, size and the center-of-gravity position of aircraft.
Then the same as for the electric hydraulic driving system of aircraft and automatic computer aircraft control system etc. with existing jet plane.
The passenger and freight transportation machine that the most suitable manufacturing of this explanation is medium-sized or above especially is fit to large-scale or ultra-large type passenger and freight transportation machine.
Below in conjunction with accompanying drawing, be that example (cargo aircraft and passenger plane are similar) is further described the present invention with the passenger plane:
Fig. 1～13rd, the profile scheme drawing of some the no wings that can implement that propose according to the present invention and the jet plane of vertical takeoff and landing (VTOL), various aircraft relative sizes are represented with number of passengers in the bracket.
Fig. 1 is superjumbo plane (600～900 people), no matter its 4 jet engine levels are jet backward or jet vertically downward, jet-stream wind does not all disturb mutually.2 power jet power and 2 jet engine power are can be the same big also can lead big time little.
Fig. 2 is superjumbo plane (800～1000 people), and 5 turbofan jet engines of its installation jet-stream wind when level is jet backward or jet does not vertically downward all disturb mutually.The balance that keeps aircraft when tail 2 desk fan formula ducted tail rotors are used for vertical takeoff and landing (VTOL).When flying forward, the aircraft level can not open.
Fig. 3 is large aircraft (500-700 people), and every group of jet engine of fuselage two sides is to be close to together by 2 fanjets also can rotate fuselage balance when the jet engine of tail is used for aircraft takeoffs and landings around same rotating shaft.
Fig. 4 also is large aircraft (400-600 people), and the jet engine group of fuselage two sides is the same with Fig. 3, and the balance of fuselage adopts the prize of fan attachment formula duct tail during the aircraft vertical takeoff and landing (VTOL).
Fig. 5 is Medium Plane (300-450 people), adorns 3 turbofan jet engines, and 3 driving engines can the while level push away aircraft flight, also can jetly simultaneously make the aircraft vertical takeoff and landing (VTOL) downwards.
Fig. 6 is that Medium Plane (250-400 people) is adorned 4 fanjets.When being illustrated as aircraft landing, the main fanjet of supposing fuselage left side breaks down and when stopping, 2 the EMER emergency parachutes lift-offs in cataplane left side help aircraft landing, improves the fuselage balance and drops to ground.
Fig. 7 is Medium Plane (250～400 people), is characterized in that the shell of main rotary jet engine is consistent with fuselage upper and lower surface curve, the resistance of favourable minimizing aircraft, and rotatable in addition two driving engines are installed in tailplane two rapidss respectively.
Fig. 8 is Medium Plane (200～350 people), and inferior engine installation is in the vertical tail outside, but does not influence the jet-stream wind of power jet, and this specification sheets is that example illustrates technical scheme of the present invention with this kind aircraft emphatically.
Fig. 9 is stream line pattern Medium Plane (200-350 people), and good looking appearance and flight resistance are little, and inferior driving engine is that ducted tail rotor is installed in drive end unit.
Figure 10 is blimp (80～200 people), and fuselage two stresses heart position and adorns two sustainer, main engines, and tail is adorned a ducted tail rotor.
Figure 11 is blimp (4～80 people), and jet engine is arranged same Figure 10, but clear height has only about 1.2～1.4 meters high of roadlice railway carriage in the main cabin.
Figure 12 is an attitude of looking up aircraft normal flight shown in Figure 8.
Figure 13 looks up shown in Figure 8 taking off or the sight when landing, and this moment, undercarriage put down.
Annotate: the number of passengers of aircraft is required for making things convenient for this paper to explain orally the aircraft type size shown in above each figure, and the aircraft that various number of passengers are close during application in shape can be general mutually.
Figure 14～17 are respectively lateral plan, front elevation, the top and bottom perspective views of aircraft configuration shown in Figure 8.
Figure 18～20 are respectively longitudinal diagram, drawing in side sectional elevation and the flat sectional drawings of interior of aircraft structure.
In Fig. 1～20, the each several part title is as follows: 1---operator's compartment, and 2---fuselage, 3---cabin door, 4---trip alternation of hosts jet engine, 5---the cabin side window, 6---luggage compartment door, 7---trip changes time jet engine, and 8---vertical tail, 9---tailplane, 10---the vertical tail yaw rudder, 11---the tail elevating rudder, 12---alighting gear, 13---the tailplane elevating rudder, 14---the tailplane support, 15---the alighting gear chamber, 16---alighting gear, 17---instrument cubicle, 18---passenger room (or cargo hold), 19---the passenger seat, 20---boot compartment, 21---fuel tank, 22---tail elevating rudder operation room and canyon, 23---the jet engine rotating shaft, 24---oil tank, 25---passenger room is to the door of water closet, 26---rotary jet engine rotating shaft operation room, 27---canyon, 28---between the pantry service, 29---the sanitary accomodation of washing one's hands, 30---chase, 31---VIP Room, 32---the skylight, 33---promptly launch parachute compartment.34---the fan-type ducted tail rotor
Referring to Fig. 1～20, in the jet plane of the no wing of the present invention and vertical takeoff and landing (VTOL), the visible outline of Aircraft Standard wing profile is adopted in the visible outline in flat fuselage (2) elevation profile, its each bench section is for highly not waiting but the essentially identical flat rectangle of width, the anterior operator's compartment (1) of arranging of fuselage (2), instrument cubicle (17), VIP Room (31), plane, cabin, (28) middle part is square between the pantry service, (cargo aircraft then is a cargo hold to arrange the main cabin, and cancellation hand baggage cabin), fuselage (2) rearward height is lower gradually, so arrange hand baggage cabin (20) backward successively, the sanitary accomodation of washing one's hands (29), fuel tank (21) and tail elevating rudder operation room, fuselage (2) are not held and are made aircraft tail elevating rudder (11).
Because the flat area of fuselage (2) is big, the elevation profile is a standard wing profile shape, when travelling forward under the promotion of aircraft at power jet, fuselage lower surface pressure is big, fuselage upper surface pressure is little, this pressure official post fuselage (2) produces elevate a turnable ladder power, and aircraft is conducted oneself with dignity and lotus is worn heavy sum, promptly liftable aircraft when this elevate a turnable ladder power is equal to or greater than.Therefore this aircraft can be cancelled the wing of general jet plane two sides.
Because of fuselage (2) two sides do not have wing, can aircraft two stress heart position or slightly forward facing position rotatable power jet (4) is installed, the rotating shaft (23) of power jet (4) is placed in the equipment interlayer of fuselage (2) two sides, also has undercarriage chamber (15) in the equipment interlayer, alighting gear (16), fuel tank (21), oil tank (24), equipment room (27), cabin door (3), luggage compartment door (6) promptly launches the equipment interlayer top that parachute compartment (33) also is arranged in fuselage two sides respectively.Pipelines such as the various electric wires from the forebody to the afterbody, oil pipe, water pipe also pass through in the interlayer thus in addition.
During the aircraft normal flight, can control the pitch attitude of aircraft front and back and the balance of aircraft left and right sides by balanced rudder (13) on manipulation tail elevating rudder (11) and the tailplane.And the left and right directions of vertical tail yaw rudder (10) the may command aircraft of control vertical tail (8) because fuselage is flat roomy, can respectively be established a vertical tail (8) in fuselage (2) afterbody two sides.
Aircraft is when taking off vertically or land, and aircraft does not have horizontal velocity, and the steady impassabitity operate lifting rudder and the yaw rudder of fuselage are controlled.Can only rely on power jet (4) to rotate to jet vertically downward rest aircraft weight, rely on time jet engine (7) jet or ducted tail rotor (34) the sweptback moment of balance fuselage of calming the anger downwards downwards.
When the aircraft vertical takeoff and landing (VTOL), two driving engines when a pair of power jet or a pair of jet engine, a tiltedly spray slightly forward, and another is slightly to retreading spray, and the anglec of rotation is the same, and then the component that makes progress of two driving engines equates, horizontal component of force is equal and opposite in direction then, direction is opposite, thereby produce a plane moment of torsion fuselage (2) is rotated in its plane, make hang aloft can change fuselage (2) towards.
Aircraft need slow down when gliding flight, except that reducing cruising thrust, also can make under equidirectional rotation equal angular of a pair of power jet and the oblique forward direction jetly, and aircraft just can very fast deceleration.
Alighting gear during the aircraft normal flight (16) but folding and unfolding in alighting gear chamber (15), can seal the alighting gear chamber by the hydraulic actuated cover plate, so that reduce flight resistance.
Passenger room (18) in the fuselage (2) is flat roomy, and nacelle top has skylight (32) daylighting.Guarantee the available light abundance in the cabin on daytime.
According to aerodynamic principle, if fuselage (2) Front-end Design becomes the outstanding forward profile of Fig. 2, Fig. 4, Fig. 7 and fuselage shown in Figure 9, favourable like this minimizing resistance and increase flight stability forward.
In sum, jet plane of the present invention with etc. the general jet airplane of load (passenger capacity or cargo capacity are identical) compare, have following advantages.
1, because fuselage produces lift, cancels two wings, alleviated the aircraft deadweight, reduce manufacturing cost, save oil consumption relatively and increased voyage.
2, the cabin is flat is square, and super-huge aircraft need not arranged two layers of main cabin yet, and favourable arrangement passenger seat and goods are stacked and loading and unloading, the safely and fast evacuation of also favourable passenger when emergency situation.
3, this machine captain, machine width (span of quite existing general aircraft) and the high size of machine dwindle 40～45% than existing aircraft, the aircaft configuration compactness, relatively complete machine intensity is bigger, can avoid general aircraft arm length and accident that wing shake that thin wing produces when flight and wing shatter.
4, fuselage upper and lower surface area is big, and jet engine is contained in fuselage two sides, so the air-flow of upper and lower surface can be realized the large tracts of land laminar flow, reduces the frictional resistance that the flight turbulent flow causes, favourable raising aircraft overall efficiency.
5, the arc section space of aircraft as none under the engine room floor, directly perforate is observed the earth or is thrown in article, favourable aerial photography, aerial application, functions such as the air rescue of dusting crops with an insecticide perfect.
But 6, both vertical takeoff and landing (VTOL) of this machine also can be as aircraft in the airfield runway short take-off and landing (STOL), and the mode of rising and falling is flexible.If vertical takeoff and landing (VTOL) can directly drop to terminal or the corridor of waiting near, saved aircraft entered and withdrawed from airstrip in the airport time.
7, add up according to data at home and abroad, aircraft take off and the landing process in accident that landing period took place to account for the ratio of all aircraft accidents the highest, many aircrafts are to cause owing to the action of alighting gear is malfunctioning, and aircraft of the present invention is because can vertical takeoff and landing (VTOL), descending speed can be very slow during near ground, both made a jet engine disaster shutdown.Can be by launching the EMER emergency parachute lift-off that the accident of being arranged in is started pusher side, the life force that the accident driving engine of remedying partly loses is realized relative stable landing.Fail to lay down if certain alighting gear is malfunctioning, the landing but complete machine fuselage base plate directly lands can reduce the degree of causality loss.Occur in the flight way in addition under the few situation of the fault that can not get rid of or fuel oil, aircraft can be selected a smooth field or level land landing, thereby can safeguard the safety of passenger, crew, aircraft and goods.
8, because vertical takeoff and landing (VTOL) or short take-off and landing (STOL), and aircraft length three-dimensional size all dwindles a lot, relatively to length, width and the bearing capacity of airfield runway require less.The hangarage size also can correspondingly reduce.Can save the investment of the many Infrastructure in airport.Therefore existing many large-scale international airports do not need to transform and enlarging, and the ultra-large type passenger/cargo transport just can rise and fall.
Although jet plane of the present invention has been done many improvement of general design than existing aircraft, except that the technical requirements that jet engine need rotate, the difficulty of other aircraft manufacturing does not increase.Therefore the producer that can produce big-and-middle-sized jet plane originally can make.
Claims (4)
1. the wing body jet aeroplane that does not have the wing and a vertical takeoff and landing (VTOL) belong to a kind of from the general design to the existing improved jet plane of jet plane, the shape of Aircraft Standard wing profile is adopted in the elevation profile that it is characterized in that the fuselage (2) of flat rectangular, fuselage (2) two sides do not have wing, but rotatable power jet (4) is installed, and rotatable jet engine (7) is installed fuselage (2) afterbody or ducted tail rotor (34) fuselage (2) afterbody also is equipped with vertical tail (8) and tailplane (9).
2,, it is characterized in that in fuselage (2) the two side apparatus interlayers alighting gear chamber (15) being arranged, alighting gear (16) according to the jet plane of the described no wing of claim 1 and vertical takeoff and landing (VTOL), power jet rotating shaft operation room (26), fuel tank (21), cabin door (3), oil tank (24).Interlayer top also is provided with and promptly launches parachute compartment (33).
3, according to the jet plane of the described no wing of claim 1 and vertical takeoff and landing (VTOL), operator's compartment (1) is established in fuselage (2) front portion, instrument cubicle (7), fuselage (2) middle part is passenger room or cargo hold (18), its rear portion is followed successively by boot compartment (20), fuel tank (21), tail lifting cabin operation room (22), fuselage (2) are not held and are made tail elevating rudder (11)
4, according to the jet plane of the described no wing of claim 1 and vertical takeoff and landing (VTOL), rotatable jet engine (7) is installed in fuselage (2) and do not hold, also can be installed on vertical tail (8) or the tailplane (9).Duct tail pipe (34) is installed in fuselage (2) and does not hold.
Tailplane (9) is installed on the vertical tail (8), or extends into tailplane (9) from fuselage (2) afterbody to two sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 95102539 CN1137998A (en) | 1995-06-15 | 1995-06-15 | Finless and vertical landing wing jet aero-plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 95102539 CN1137998A (en) | 1995-06-15 | 1995-06-15 | Finless and vertical landing wing jet aero-plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1137998A true CN1137998A (en) | 1996-12-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 95102539 Pending CN1137998A (en) | 1995-06-15 | 1995-06-15 | Finless and vertical landing wing jet aero-plane |
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| CN (1) | CN1137998A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102001446A (en) * | 2010-11-11 | 2011-04-06 | 韦斯豪 | Structure of vertical take-off and landing rotor aircraft |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN103754372A (en) * | 2013-10-01 | 2014-04-30 | 魏伯卿 | Airplane capable of vertically taking-off and landing as well as staying and inversely flying in air |
| 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 |
| CN104085527A (en) * | 2014-07-09 | 2014-10-08 | 李庆宏 | Cuboid-shaped aircraft with upper support large flat plate |
| CN104943847A (en) * | 2015-06-23 | 2015-09-30 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle body and unmanned transport plane with unmanned aerial vehicle body |
| CN105584631A (en) * | 2016-02-23 | 2016-05-18 | 天峋创新（北京）科技有限公司 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
| CN106005394A (en) * | 2016-07-22 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Rescue aircraft |
| CN108248847A (en) * | 2018-02-09 | 2018-07-06 | 北京白米科技有限公司 | Power wing body multi-rotor unmanned aerial vehicle |
| CN111003172A (en) * | 2018-10-08 | 2020-04-14 | 苏郁夫 | Jet type vertical lifting pneumatic system |
| CN111516859A (en) * | 2020-05-09 | 2020-08-11 | 中国北方工业有限公司 | Low-temperature invisible multi-nozzle aircraft |
-
1995
- 1995-06-15 CN CN 95102539 patent/CN1137998A/en active Pending
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102001446A (en) * | 2010-11-11 | 2011-04-06 | 韦斯豪 | Structure of vertical take-off and landing rotor aircraft |
| CN102001446B (en) * | 2010-11-11 | 2013-08-28 | 韦斯豪 | Structure of vertical take-off and landing rotor aircraft |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN103754372B (en) * | 2013-10-01 | 2015-09-09 | 魏伯卿 | Vertical takeoff and landing can stop the aircraft with inverted flight in the air |
| CN103754372A (en) * | 2013-10-01 | 2014-04-30 | 魏伯卿 | Airplane capable of vertically taking-off and landing as well as staying and inversely flying in air |
| 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 |
| CN104085527A (en) * | 2014-07-09 | 2014-10-08 | 李庆宏 | Cuboid-shaped aircraft with upper support large flat plate |
| CN104943847A (en) * | 2015-06-23 | 2015-09-30 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle body and unmanned transport plane with unmanned aerial vehicle body |
| CN105584631A (en) * | 2016-02-23 | 2016-05-18 | 天峋创新（北京）科技有限公司 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
| CN106005394A (en) * | 2016-07-22 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Rescue aircraft |
| CN108248847A (en) * | 2018-02-09 | 2018-07-06 | 北京白米科技有限公司 | Power wing body multi-rotor unmanned aerial vehicle |
| CN111003172A (en) * | 2018-10-08 | 2020-04-14 | 苏郁夫 | Jet type vertical lifting pneumatic system |
| CN111003172B (en) * | 2018-10-08 | 2021-07-27 | 苏郁夫 | Jet type vertical lifting pneumatic system |
| CN111516859A (en) * | 2020-05-09 | 2020-08-11 | 中国北方工业有限公司 | Low-temperature invisible multi-nozzle aircraft |
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