CN201023656Y - Ground effect aircraft - Google Patents
Ground effect aircraft Download PDFInfo
- Publication number
- CN201023656Y CN201023656Y CNU2007201187966U CN200720118796U CN201023656Y CN 201023656 Y CN201023656 Y CN 201023656Y CN U2007201187966 U CNU2007201187966 U CN U2007201187966U CN 200720118796 U CN200720118796 U CN 200720118796U CN 201023656 Y CN201023656 Y CN 201023656Y
- Authority
- CN
- China
- Prior art keywords
- wing
- ground effect
- fuselage
- effect vehicle
- stage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model discloses a medium-sized land-effective flight device which flies in the land-effective flight area, comprising a device body, a device wing, a tail wing and an engine, wherein the tail part of the flight device is provided with a cruising engine, two sides of the head part of the device body are provided with launching engines, lift-rising air cavities are arranged below the wings which are arranged on two sides of the middle part of the device body, the lift-rising air cavity is a closed cavity which comprises the lower part of the middle section of the device body, the lower wing surface of the main wing, baffle boards which are arranged below the two ends of the main wing, and a flap wing which is arranged on the lower part of the tailing edge of the main wing. The utility model leads a jet flow of the launching engine to come into the lift-rising air cavity through a steering spout, and transforms the kinetic energy of the air current into pressure energy, thereby producing a relatively large pad elevating force, the T-shaped tail wing which is arranged high on the tail part of the flight device is provided with the cruising engine, and an elevating rudder with adjustable sheets are arranged on the tail wing and the flat tail of the tail wing. Therefore the utility model can assure a reasonable match between an attack angle focus and an altitude focus, assure the trim of the rod force of the elevating rudder when in a long time flight, realize the balance and automation in the longitudinal surface, and assure the steady flight when the flight device flies near the water surface.
Description
Technical field
The utility model relates to a kind of aircraft, especially a kind of medium-sized effect aircraft at high speed with effectively power-boosting effect that flies in the movement area is imitated on ground.
Background technology
The effectively power-boosting ground effect vehicle is a kind of high speed means of transport, when aircraft ground proximity or water surface flying, the lift on producing conventional meaning, because of the slype of windstream between wing and the ground or the water surface also can produce additional lift.Ground effect vehicle promptly is to utilize this aerodynamic force ground effect principle and a kind of novel novel traffic transportation means of plunderring ground or plunderring sea flight that grows up.Because ground effect vehicle has the same high-speed of aircraft, though it can nap of the earth flight in theory, in fact can only not have to plunder water surface flying on the rivers,lakes and seas of surface interruptions, therefore, the ground effect vehicle ground effect ship that is otherwise known as.Its basic flight theory of ground effect vehicle and design and manufacturing technology mainly belong to aeronautical technology, but its purposes and environment for use relate to boats and ships and art of navigation field.
Existing small-sized ground effect vehicle, as Chinese patent application number 02115191.1 disclosed small-sized ground effect vehicle, its tonnage and yardstick are little (5 tonnes, 9.8 meters of the spanes, 16 meters of total lengths), the speed of a ship or plane low (150 kilometers/hour), passenger capacity little (only people surplus in the of ten), capacity of anti-storm low (landing wave height is no more than 1 meter, cruise fly height be no more than 1.5 meters) generally only can be in the inland river, use the inland lake.
Summary of the invention
The purpose of this utility model aims to provide a kind of ground effect vehicle that can make full use of the effectively power-boosting effect, it is had can make the passenger-cargo ground effect vehicle in medium-sized sea that lift increases, positive power reduces in the aerial stabilized flight of adjoined water surface.
The utility model adopts following technical scheme for achieving the above object: a kind of ground effect vehicle, comprise fuselage, wing, empennage and driving engine, described aircraft afterbody is provided with cruising engine, the fuselage head both sides are provided with thruseer, middle fuselage two flanks have boosting air cavity, and this boosting air cavity is made up of the cavity that inclined to one side wing flap under the dividing plate of middle fuselage bottom, main wing lower aerofoil, main wing two ends lower aerofoil and the main wing trailing edge constitutes closed.
Thruseer described in the utility model is provided with the actuating device that makes deflect on the spout.
The actuating device of the elevating rudder deflection of the tailplane trailing edge of wing flap described in the utility model, thruseer spout and aircraft afterbody is equipped with the hydraulic sterring engine that makes the synchronous deflection of three according to the fly-by-wire co-operative control separately.
Wing described in the utility model is the combination wing of being made up of the outer wing of the main wing of low aspect ratio, high aspect ratio and the transition phase between the two.
Outer wing described in the utility model, main wing and outer wing transition phase are tapered airfoil.
Aircraft afterbody described in the utility model is provided with T-tail, and horizontal tail and vertical fin that described T-tail is put by height are formed, and the trailing edge of horizontal tail is provided with elevating rudder, and the trailing edge of vertical fin is provided with yaw rudder.
Fuselage described in the utility model is by forebody, and middle fuselage and rear body are formed, and the sector section with certain ramping angle α of similar glider is adopted in bottom, described fuselage bench section, and ramping angle diminishes from the stem to the afterbody gradually.
Fuselage bottom described in the utility model is multibreak rank layouts, and described multibreak rank layout comprises the main faulted-stage of nosing and be located at main faulted-stage several times faulted-stage and stern faulted-stage afterwards that main faulted-stage is multibreak stage structure with several times faulted-stage and stern faulted-stage; And each faulted-stage trailing edge is distributed in the water reference plane and is on the straight line at certain inclination angle.
Aircraft described in the utility model is provided with the hydroskis device at the fuselage bottom at full machine center of gravity place, and the hydroskis device is made up of hydroskis, the pressurized strut of two bufferings and rubber pneumatic bag.
Be respectively equipped with retractable simple and easy alighting gear before and after the ventral place of fuselage described in the utility model, described alighting gear is made up of the main landing gear of nose-gear that is located at fuselage head and afterbody, and the belly of described wing dividing plate is provided with auxiliary pulley.
The utility model is owing to adopt square under the wings of an airplane design-calculated boosting air cavity and thruseer to turn to reasonable configuration between the spout, the thruseer jet flow is imported boosting air cavity by turning to spout, and the kinetic energy of air-flow is converted into the pressure energy, to produce bigger air-cushion force.In addition, the T type tail of putting at aircraft afterbody height is provided with cruising engine; Empennage and be located at the elevating rudder that has tab on the empennage horizontal tail, both guaranteed reasonably to mate between angle of attack focus and the height focus, the trim of elevating rudder stick force when having guaranteed long-time flight again, realized balance in longitudinal plane and motor-driven, guaranteed that aircraft can be in the aerial stable flight of adjoined water surface.
The passenger-cargo ground effect vehicle in medium-sized sea provided by the utility model is by pneumatic configuration reasonable in design, can make that flight lift increases, resistance reduces, the ground effect vehicle that makes full use of the effectively power-boosting effect has can be in the characteristics of the aerial stabilized flight of adjoined water surface.
Describe structure of the present utility model and principle of work in detail below in conjunction with accompanying drawing:
Description of drawings
Fig. 1 is a three-dimensional structure diagram of the present utility model.
Fig. 2-1, Fig. 2-2 and Fig. 2-3 are respectively front view of the present utility model, right elevation and birds-eye view.
Fig. 3 is a three-dimensional decomposition texture scheme drawing of the present utility model.
Fig. 4 is the fear figure that puts of the complete objective type ground effect vehicle freight space of the utility model embodiment 1.
Fig. 4-1 is the freight space plane of arrangement figure of Fig. 4.
Fig. 4-2,4-3,4-4 are Fig. 4-1C-C, D-D, E-E cutaway view.
Fig. 4-5 is that the part of Fig. 4 M-M face is to view.
Fig. 4-6 is that the part of Fig. 4 L-L face is to view.
Fig. 5 is the fear figure that puts of the shipping type ground effect vehicle freight space of the utility model embodiment 2.
Fig. 5-1 is the freight space plane of arrangement figure of Fig. 5.
Fig. 5-2 is the F-F cutaway view of Fig. 5-1.
Fig. 6 is the fear figure that puts of the searching rescue type ground effect vehicle freight space of the utility model embodiment 3.
Fig. 6-1 is the freight space plane of arrangement figure of Fig. 6.
Fig. 6-2 is the cutaway view of the G-G of Fig. 6-1.
Fig. 7 is the fear figure that puts of customs's anti-smuggling type ground effect vehicle freight space of the utility model embodiment 4.
Fig. 7-1 is the freight space plane of arrangement figure of Fig. 7.
Fig. 7-2, Fig. 7-3 is the J-J of Fig. 7-1, the cutaway view of K-K.
Fig. 8 is the scheme drawing that thruseer jet flow of the present utility model imports boosting air cavity.
Fig. 9 is the utility model fuselage water ski structure drawing of device.
Figure 10 is the utility model take-off and landing device constructional drawing.
Figure 10-1 is the local I enlarged drawing of Figure 10.
Figure 10-2 is the A-A cutaway view of Figure 10-1.
Figure 10-3 is the auxiliary pulley constructional drawing of wing dividing plate.
Figure 10-4 is the local I I enlarged drawing of Figure 10.
Figure 10-5 is the B-B cutaway view of Figure 10-4.
The specific embodiment
Shown in Figure 3 as Fig. 1 Fig. 2, the utility model comprises middle fuselage 2, main wing 6, cruising engine 13, thruseer 12 and spout thereof.Wing flap 4 inclined to one side under described middle fuselage 2 and main wing 6 and dividing plate 14, the trailing edge forms osed top boosting air cavities 18.The thruseer jet flow imports boosting air cavity 18, and air-flow is blocked in the chamber, and kinetic energy changes the pressure energy into, and the additonal pressure that acts on main wing 6 lower surfaces produces the additional lift that hovers.The lift that hovers can lift aircraft, has reduced the area that aircraft contacts with water, thereby has reduced the aircraft resistance of taxing.Above-mentioned boosting air cavity 18 is the cavity that dividing plate 14 below middle fuselage 2 bottoms, main wing 6 lower aerofoils, main wing 6 two ends and main wing 6 trailing edge flaps 4 are formed, and wherein wing flap 4 is provided with the actuating device that it is deflected down along main wing 6 trailing edges.Above-mentioned thruseer 12 is provided with the actuating device that makes deflect on the spout, and this cruising engine 13 is a propeller turbine, is arranged on the midway location top of the horizontal tail 8 of T type tail.
In the time of the spout deflection of wing flap 4 and thruseer 12, will cause the variation of full machine longitudinal moment, the elevating rudder 11 that at this moment needs the deflection central horizontal wing 7 and tailplane outer wing 8 trailing edges is to keep the balance in pitch of full machine.Above-mentioned elevating rudder 11 is provided with the actuating device that makes deflect on it.The actuating device of above-mentioned as shown in Figure 8 wing flap 4, thruseer 12 spouts and elevating rudder 11 deflections is hydraulic sterring engine separately, by the unified control of fly-by-wire, also is that three's deflection is carried out synchronously by chaufeur.Above-mentioned power-boosting system can make ground effect vehicle successfully dried up and carry out the transition to cruising condition, and whole process operation is easy, flight attitude stable.Above-mentioned wing flap 4 is a rectangle, its pivot angle be 0-20 ° adjustable.
Shown in Fig. 2-1, Fig. 2-2 and 2-3, the wing of the utility model ground effect vehicle is by the outer wing 5 of the main wing 6 of low aspect ratio, high aspect ratio and the combination wing of forming between the transition phase between the two 19.Main wing 6, outer wing 5 and transition phase 19 are tapered airfoil.
Above-mentioned outer wing 5 trailing edges are provided with the deflectable pair of wing 15.That such combination wing layout and geometric parameter have is simple in structure, the effect of imitating strong, mate rational characteristics.Above-mentioned T type tail comprises horizontal tail and the vertical fin 9 that the central horizontal wing 7, tailplane outer wing 8 are formed.For reducing the wash interference of wing to empennage, described horizontal tail adopts the setting that height is put and area is bigger.Be provided with a pair of elevating rudder 11 that is used to control vertical flight attitude and realizes balance in pitch about above-mentioned horizontal tail trailing edge edge, its rudder face is provided with tab 17.Above-mentioned elevating rudder 11 mainly provide fore-and-aft control moment, guarantees effectively power-boosting ground effect aircraft longitudinal moment balance, realizes effectively power-boosting ground effect aircraft motor-driven in longitudinal plane.Different with general aircraft, when effectively power-boosting ground effect aircraft flies, two focuses are arranged in ground effect region, i.e. angle of attack focus and height focus.Press effectively power-boosting ground effect aircraft longitudinal movement judgement of stability, when having only the center-of-gravity position reasonable disposition when angle of attack focus, height focus and ground effect vehicle, the longitudinal movement of effectively power-boosting ground effect aircraft is only stable.And adopt the high T type tail of putting and the reasonable disposition of other parts, and can in the speed range of regulation, have good stable, guarantee the rational Match of angle of attack focus and height focus.Above-mentioned vertical fin 9 trailing edges are provided with deflectable yaw rudder 10.
Forebody 1, middle fuselage 2 and rear body 3 are formed fuselage.The sector section with certain ramping angle α of similar glider is adopted in bottom, described fuselage bench section.Ramping angle diminishes from the stem to the afterbody gradually.Described fuselage bottom is multibreak rank layouts.Described multibreak rank layout comprises the main faulted-stage 112 of nosing and is located at main faulted-stage 112 several times faulted-stage 111 and stern faulted-stage 113 afterwards.Main faulted-stage 112 is multibreak stage structure with several times faulted-stage 111 and stern faulted-stage 113, and requires each faulted-stage trailing edge to be distributed in level reference to be on the straight line at certain inclination angle.Layout like this, planing surface will longitudinally be divided into a plurality of planing surfaces, increase the aspect ratio of planing surface, reduce friction drag, improve hydrodynamic performance, strengthen stability of motion; Adopt multibreak rank, a plurality of planing surfaces occur, the impact of hydrodynamic force to structure disperseed, improved structural stress state; Take multibreak rank, guarantee that ground effect vehicle is dried up with the identical pitch angle in each faulted-stage trailing edge line inclination angle, for ground effect vehicle provides advantage to the cruising condition transition flight.
The profile of dividing plate 14 bottom planing surfaces is similar to fuselage bottom.Dividing plate 14 planing surfaces except that play a part identical with the fuselage planing surface because it is far away at main wing two end distance fuselages, lateral stability when also playing a part to increase substantially the skage sailing of the utility model ground effect vehicle.
Above-mentioned fuselage sliding body bottom and dividing plate bottom transverse cross section are the sector section that has horizontal ramping angle α shown in Fig. 4,5,6,7.The rational bottom transverse ramping angle in fuselage and dividing plate 14 bottoms, planing surface produces suitable righting moment about making when effectively power-boosting ground effect aircraft is in sliding state, guarantees that effectively power-boosting ground effect aircraft has good horizontal planing stability.
Shown in Fig. 4,4-1, for the passenger-carrying version freight space arrangement plan of the utility model embodiment 1, in the cabin, be distributed with three seats of a row, one side the seat is set to have one in the cabin, another side is provided with two, the afterbody in the cabin is provided with the lavatory; Shown in Fig. 5,5-1, for the shipping type freight space arrangement plan of the utility model embodiment 2, in the cabin cabin of arrangement of goods, the side in the cabin is provided with the hatch door that large cargo loads and unloads, and at front fuselage, is provided with the lounge of staff's rest at random; Shown in Fig. 6, Fig. 6-1, searching rescue type freight space arrangement plan for the utility model embodiment 3, in the cabin, be provided with the first-aid applicance that first aid is used, under the seriously injured situation of the wounded, also be provided with the operating table that is used as simple operation in the cabin, top at head section, be provided with the observation ward that actual monitored is provided, compare with boats and ships rescue or helicopter rescue, this rescue type ground effect vehicle can be resisted stormy waves, and stability is high, the situation that can't implement to rescue that stormy waves causes when reducing rescue occurs; Shown in Fig. 7, Fig. 7-1, customs's anti-smuggling type freight space arrangement plan for the utility model embodiment 4, in the cabin, be provided with office desk and chair, top at fuselage, be provided with aerial ladder, providing the coast guard to go on board fast closes down, at the fuselage top radar is housed, the tracking to smuggling boat is provided, compare with existing revenue cutter, this ground effect vehicle is on the interception smuggling boat, have higher maneuvering performance, and do not have the influence of stormy waves, save the loiter time, enlarge the patrol scope, effectively crack down on smuggling.
When the ground effect vehicle landing water surface, wave can arrive the several times of own wt greatly to the impulsive force of ground effect vehicle.As Fig. 3, shown in Figure 9, hydrodynamic load is to the impact of ground effect vehicle structure when slowing down water, and the fuselage bottom at full machine center of gravity place is provided with hydroskis device 16.Hydroskis device 16 is made up of hydroskis 20, the pressurized strut 21 of two bufferings and some rubber pneumatic bags 22.Rubber pneumatic bag 22 plays buffering and the sealing function of avoiding the two direct contact between airframe structure and hydroskis structure.Buffering pressurized strut 21 has folding and unfolding hydroskis 20 to be in it to pack up or open position and the effect that absorbs hydrodynamic(al) load impacting energy.When hydroskis 20 touches water, buffering pressurized strut 21 absorbs the hydrodynamic impact load that hydroskis 20 is subjected to come in apace, in the floating condition after the ground effect vehicle landing, buffering pressurized strut 21 slowly releases energy stored again, has so just alleviated the impact of hydrodynamic load to structure widely.Hydroskis 20 profiles are similar to the very little water skiing flat board of width.Hydroskis 20 to be lowered into open position when water, make its even water.Hydroskis 20 profiles mainly act near the pillar that connects buffering pressurized strut 21 hydrodynamic impact load, keep simultaneously aircraft at hydroskis 20 behind the water, fuselage and dividing plate 14 coast period that do not touch water as yet stably navigates by water, and make fuselage and dividing plate 14 bottom planing surfaces equably water.Hydroskis 20 earlier water also delayed the time that dividing plate 14 and fuselage touch water, the speed when having reduced dividing plate 14 and fuselage and touching water has reduced the impact of hydrodynamic load.
To shown in the 10-5, the utility model ground effect vehicle adopts the setting of bikini alighting gear, is provided with retractable simple and easy take-off and landing device respectively, nose-gear 711 and main landing gear 712 at fuselage head and afterbody ventral plane of symmetry place as Figure 10, Figure 10-1.Nose-gear 711 is provided with it is turned during in ground taxi with the control ground effect vehicle around the steering hardware of self axis tilt.Nose-gear 711 and main landing gear 712 are equipped with the jack that makes it pack up and put down.Nose-gear 711 is provided with a skid steering wheel body 713, main landing gear 712 is provided with two and slides wheel body 714, ventral place at fuselage, be provided with cavity 1111,1112 for undercarriage control, but the outer both sides of cavity are provided with the undercarriage door 715,716 of opening and closing, when wheel body 713,714 put down, undercarriage door 715,716 was opened simultaneously.Under normal flight and water skiing state, nose-gear and main landing gear all are in the stowed position.Only change disembarkation over to when sliding the ramp by the water skiing state when ground effect vehicle, just nose-gear and main landing gear are put down, rely on engine thrust to slide disembarkation voluntarily and enter and stop the base, be provided with auxiliary pulley 717 at the belly of wing dividing plate 14.
Actual mechanical process of the present utility model is achieved in that special-purpose visitor, the dual-purpose harbour of goods that ground effect vehicle rests in similar airport finish on visitor, the goods behind the machine, starts cruising engine 13, the aircraft entry of gliding along the ramp.Slide in the process, turn to control to turn with nose-gear.After the ground effect vehicle entry, nose-gear and main landing gear are all packed up, and simultaneously, start thruseer, and aircraft enters the water skiing state, and " thrust is poor " control of available left and right thruseer is turned.Aircraft at first in the bay special-purpose taxiway take off.If bay taxiway curtailment or condition do not allow, also can slide the position of special delimitation and take off to the off-lying sea.In the process of sliding, hydroskis 20 is in the stowed position.After beginning to take off, cruising engine 13 and thruseer 12 are all driven to maximum rating.Simultaneously, wing flap 4 deflects down, and thruseer 12 spouts turn to, and jet cutting car flow is guided under the wing with the generation lift that hovers.When ground effect vehicle accelerates to get away speed, body carries away the water surface.After finishing the transition flight state, thruseer 12 cuts out, and wing flap 4 is packed up, and changes the average flight state in the ground effect height over to.
At ground effect vehicle from flying to the whole transition flight stage that changes cruising flight over to, chaufeur turns to the hydraulic sterring engine of spout, wing flap 4 and elevating rudder 11 to implement harmonious synchronous operation by fly-by-wire to thruseer 12, can make ground effect vehicle successfully carry out the transition to average flight state from takeoff condition, whole process operation is easy, reliable.
In flight course, if meet obstacle, ground effect vehicle ground effect region to the 150 meter height clear an obstacle that flies out of can climbing.
After arriving the destination, put down wing flap 4, ground effect vehicle slows down, and puts down hydroskis 20 simultaneously.When aircraft speed is being reduced to water speed, hydroskis 20 at first clashes into the water surface, absorbs jolt capacity, and body does not progressively have in the entry, is entering neatly row order section.After hydroskis 20 touched water, wing flap 4 was promptly progressively packed up, and enters idling rating by cruising engine 13 aircraft is slided supreme bank slope road, and hydroskis 4 is packed up, and puts down nose-gear and main landing gear simultaneously, and aircraft slides to landing pier along the ramp voluntarily.
The utility model ground effect vehicle can make lift increase, resistance reduce in the aerial stabilized flight of adjoined water surface.Its maximum take-off weight can reach 19 tons, passenger capacity 45 people, and cruising speed is 200-290 kilometer/hour, can landing under the high 1.25-1.6 rice of wave sea condition, the coastal lines that is particularly suitable in 600 kilometers uses.
Claims (10)
1. ground effect vehicle, comprise fuselage, wing, empennage and driving engine, it is characterized in that: described aircraft afterbody is provided with cruising engine (13), the fuselage head both sides are provided with thruseer (12), middle fuselage (2) two flanks have boosting air cavity (18), and this boosting air cavity (18) is made up of the cavity that wing flap (4) inclined to one side under the dividing plate (14) of middle fuselage (2) bottom, main wing (6) lower aerofoil, main wing (6) two ends lower aerofoil and main wing (6) trailing edge constitutes closed.
2. ground effect vehicle according to claim 1 is characterized in that: described thruseer (12) is provided with the actuating device that makes deflect on the spout.
3. ground effect vehicle according to claim 1 and 2 is characterized in that: the actuating device of elevating rudder (11) deflection of the tailplane trailing edge of described wing flap (4), thruseer (12) spout and aircraft afterbody is equipped with the hydraulic sterring engine that makes the synchronous deflection of three according to the fly-by-wire co-operative control separately.
4. ground effect vehicle according to claim 1 is characterized in that: described wing is by the main wing (6) of low aspect ratio, the outer wing (5) of high aspect ratio and the combination wing that the transition phase between the two (19) is formed.
5. ground effect vehicle according to claim 4 is characterized in that: described outer wing (5), main wing (6) and outer wing transition phase (19) are tapered airfoil.
6. ground effect vehicle according to claim 1, it is characterized in that: described aircraft afterbody is provided with T-tail, horizontal tail that described T-tail is put by height (8) and vertical fin (9) are formed, and the trailing edge of horizontal tail (8) is provided with elevating rudder (11), and the trailing edge of vertical fin (9) is provided with yaw rudder (10).
7. ground effect vehicle according to claim 1, it is characterized in that: described fuselage is by forebody (1), middle fuselage (2) and rear body (3) are formed, the sector section with certain ramping angle α of similar glider is adopted in bottom, described fuselage bench section, and ramping angle diminishes from the stem to the afterbody gradually.
8. ground effect vehicle according to claim 1, it is characterized in that: described fuselage bottom is multibreak rank layouts, described multibreak rank layout comprises the main faulted-stage (112) of nosing and is located at main faulted-stage (112) several times faulted-stage (111) and stern faulted-stage (113) afterwards that main faulted-stage (112) is multibreak stage structure with several times faulted-stage (111) and stern faulted-stage (113); And each faulted-stage trailing edge is distributed in the water reference plane and is on the straight line at certain inclination angle.
9. ground effect vehicle according to claim 1, it is characterized in that: described aircraft is provided with hydroskis device (16) at the fuselage bottom at full machine center of gravity place, and hydroskis device (16) is made up of hydroskis (20), the pressurized strut (21) of two bufferings and rubber pneumatic bag (22).
10. ground effect vehicle according to claim 1, it is characterized in that: be respectively equipped with retractable simple and easy alighting gear before and after the ventral place of described fuselage, described alighting gear is made up of the main landing gear (712) of nose-gear that is located at fuselage head (711) and afterbody, and the belly of described wing dividing plate (14) is provided with auxiliary pulley (717).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201187966U CN201023656Y (en) | 2007-03-02 | 2007-03-02 | Ground effect aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201187966U CN201023656Y (en) | 2007-03-02 | 2007-03-02 | Ground effect aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201023656Y true CN201023656Y (en) | 2008-02-20 |
Family
ID=39097507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007201187966U Expired - Fee Related CN201023656Y (en) | 2007-03-02 | 2007-03-02 | Ground effect aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201023656Y (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103192989A (en) * | 2013-04-08 | 2013-07-10 | 孙亮 | Land ground effect aircraft |
| CN107792359A (en) * | 2017-10-19 | 2018-03-13 | 西北工业大学 | A kind of empty dual-purpose unmanned plane of water |
| CN110576970A (en) * | 2018-06-09 | 2019-12-17 | 天津大学（青岛）海洋工程研究院有限公司 | Hydrofoil and air bag combined type water surface lifting device |
| CN112249298A (en) * | 2020-10-10 | 2021-01-22 | 郑州海王实业有限公司 | Efficient ground effect wing ship elevator counterweight device |
| CN113093807A (en) * | 2021-04-07 | 2021-07-09 | 中国船舶科学研究中心 | Ground effect flight control device of unmanned ground effect wing ship |
| CN117262214A (en) * | 2023-10-11 | 2023-12-22 | 哈尔滨工业大学 | Amphibious short-distance take-off and landing ground effect aircraft |
| US11987402B2 (en) | 2021-03-29 | 2024-05-21 | The Boeing Company | Vertical air vehicle takeoff and landing stabilization apparatuses, systems, and methods |
| US11993409B2 (en) | 2021-03-29 | 2024-05-28 | The Boeing Company | Vertical air vehicle takeoff and landing stabilization apparatuses, systems, and methods |
| US12116143B2 (en) | 2021-03-29 | 2024-10-15 | The Boeing Company | Vertical air vehicle takeoff and landing stabilization apparatuses, systems, and methods |
-
2007
- 2007-03-02 CN CNU2007201187966U patent/CN201023656Y/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103192989A (en) * | 2013-04-08 | 2013-07-10 | 孙亮 | Land ground effect aircraft |
| CN103192989B (en) * | 2013-04-08 | 2016-08-24 | 孙亮 | Land ground effect vehicle |
| CN107792359A (en) * | 2017-10-19 | 2018-03-13 | 西北工业大学 | A kind of empty dual-purpose unmanned plane of water |
| CN110576970A (en) * | 2018-06-09 | 2019-12-17 | 天津大学（青岛）海洋工程研究院有限公司 | Hydrofoil and air bag combined type water surface lifting device |
| CN112249298A (en) * | 2020-10-10 | 2021-01-22 | 郑州海王实业有限公司 | Efficient ground effect wing ship elevator counterweight device |
| US11987402B2 (en) | 2021-03-29 | 2024-05-21 | The Boeing Company | Vertical air vehicle takeoff and landing stabilization apparatuses, systems, and methods |
| US11993409B2 (en) | 2021-03-29 | 2024-05-28 | The Boeing Company | Vertical air vehicle takeoff and landing stabilization apparatuses, systems, and methods |
| US12116143B2 (en) | 2021-03-29 | 2024-10-15 | The Boeing Company | Vertical air vehicle takeoff and landing stabilization apparatuses, systems, and methods |
| CN113093807A (en) * | 2021-04-07 | 2021-07-09 | 中国船舶科学研究中心 | Ground effect flight control device of unmanned ground effect wing ship |
| CN117262214A (en) * | 2023-10-11 | 2023-12-22 | 哈尔滨工业大学 | Amphibious short-distance take-off and landing ground effect aircraft |
| CN117262214B (en) * | 2023-10-11 | 2024-07-05 | 哈尔滨工业大学 | Amphibious short-distance take-off and landing ground effect aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201023656Y (en) | Ground effect aircraft | |
| US8657226B1 (en) | Efficient control and stall prevention in advanced configuration aircraft | |
| Yun et al. | WIG craft and ekranoplan | |
| US7793884B2 (en) | Deltoid main wing aerodynamic configurations | |
| US6113028A (en) | Amphibious aircraft | |
| US9545993B2 (en) | Aircraft stability and efficient control through induced drag reduction | |
| US4691881A (en) | High performance amphibious airplane | |
| CN108045575B (en) | Short-distance take-off vertical landing aircraft | |
| US5105898A (en) | Hovercraft ground-effect vehicle | |
| CN201010045Y (en) | Ground-effect aircraft | |
| CN113232832A (en) | Amphibious aircraft | |
| US3614032A (en) | Aircraft | |
| US12017770B2 (en) | Electric-propulsion aircraft comprising a central wing and two rotatable lateral wings | |
| CN100475649C (en) | Ground effect flyer | |
| RU2668000C1 (en) | Amphibious aircraft of "flying wing" scheme | |
| RU2391254C2 (en) | Supersonic aircraft (versions) | |
| CN200985092Y (en) | Pneumatic arrangement for ground effect aircraft | |
| US2761634A (en) | Verttcally rising airplane | |
| RU112154U1 (en) | MULTI-PURPOSE PLANE | |
| CN205602117U (en) | Novel high lift VTOL aircraft | |
| CN212501033U (en) | Light-duty sport aircraft of firefly | |
| RU196671U1 (en) | Supersonic Passenger Aircraft | |
| RU196109U1 (en) | Supersonic Civil Aircraft | |
| CN210911921U (en) | Land, sea and air all-round type hovercar with excellent safety | |
| RU2328413C1 (en) | Lightweight amphibian aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080220 Termination date: 20160302 |