CN1439578A - Multifunctional airplane and application thereof - Google Patents
Multifunctional airplane and application thereof Download PDFInfo
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- CN1439578A CN1439578A CN 03105090 CN03105090A CN1439578A CN 1439578 A CN1439578 A CN 1439578A CN 03105090 CN03105090 CN 03105090 CN 03105090 A CN03105090 A CN 03105090A CN 1439578 A CN1439578 A CN 1439578A
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- buoyancy tank
- box body
- auxiliary box
- multifunction
- aircraft
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Abstract
A multifunctional airplane features that it has a left and a right buoyancy tanks for allowing it take off from or land on water surface and a rotation driver mechanism for turning over said buoyancy tanks in order to use them as wings. Said buoyancy tanks can also play the role of armour. Its advantages are high elevating force, stably fly, high load-bearing power and saving fuel oil.
Description
Technical field
The present invention relates to the aircraft manufacturing technology, particularly relate to a kind of multifunction aircraft and application thereof, for allowing take off from or land on water surface buoyancy tank of this aircraft also has the function of aircraft wing.
Background technology
At present, most of aircrafts all do not have the function of water takeoff and landing, because water takeoff and landing need possess buoyancy tank or underbelly is made hull shape, are that the buoyancy tank or the fuselage of hull shape all can increase aloft air resistance.This is owing to be the hull shape of buoyancy tank and underbelly no matter, and the shape below it is just in time opposite with shape below the aircraft wing, and the bottom of this shape not only can not produce thrust upwards awing under the effect of air-flow, can produce downward pulling force on the contrary.Therefore this design all has very big influence to the flying speed and the load of aircraft.The propeller of existing helicopter at work, owing to be subjected to the thrust that air-flow makes progress, paddle base portion to end is inclined upwardly successively, thereby makes the paddle elevation angle partly away from base portion become big, thrust is reduced, influenced the performance of the due enhanced feature of propeller.
Summary of the invention
The objective of the invention is to overcome the shortcoming of prior art, provide a kind of and possess for allowing take off from or land on water surface buoyancy tank, and this buoyancy tank also has the multifunction aircraft of aircraft wing function, purpose of the present invention also relates to the application of multifunction aircraft of the present invention.
For achieving the above object, the buoyancy tank that takes off in the water supply and land is equipped with by support in the fuselage below of multifunction aircraft of the present invention, equate about this buoyancy tank is divided into two, the rotary drive mechanism that buoyancy tank is spun upside down along fuselage outer side also is housed between fuselage and the support, or the rotary drive mechanism that can make buoyancy tank do vertical upset is housed between support and buoyancy tank.The buoyancy tank that so freely overturn takes off on supplying water when the normal position and lands, and can provide the hoisting force that makes progress for aircraft awing by increase actv. wing area after buoyancy tank upwards overturns.Here select arbitrarily in the 180 degree angles that the flip angle of buoyancy tank can be on outer vertical, as run into terrestrial gun and attack with fire and hit, buoyancy tank can also rotate to the direction of attack of artillery fire easily, protects the safety of aircraft as armour tank with buoyancy tank.It is to be noted support of the present invention and buoyancy tank, or buoyancy tank can be installed in removably on fuselage or the support also.
As optimization, the auxiliary box body that can outwards stretch is equipped with in the left side of described buoyancy tank or right side or the left and right sides; Outwardly directed auxiliary box body can be an one-level, also can be above multistage of secondary.Auxiliary box body stretches out the aircraft wing that the back forms super large, can obviously increase buoyancy waterborne and the hoisting force that makes progress in the air.Use the helicopter of the technology of the present invention, if awing engine breakdown or propeller fault, helicopter can lean on buoyancy tank and the auxiliary box body thereof after the upset to glide as wing safely, and Helicopter Safety is landed, thereby avoids fatal crass's bitterness loss.If the effective wing insufficient area that buoyancy tank after launching and auxiliary box body form makes aircraft safety the road, can make aircraft continue to glide a period of time at least aloft, thereby give the enough escape time of crew, thereby ensure persons on board's life security.
As optimization, be equipped with to the flexible auxiliary box body of a side front and back end of described buoyancy tank, and be equipped with to the flexible auxiliary box body of opposite side at the middle part of buoyancy tank.So the auxiliary box body that is provided with respectively more helps adapting to various aircraft models, and helps equilibrium of forces between buoyancy tank and auxiliary box body and the support, and is promptly symmetrical stressed.
As optimization, the auxiliary box body of buoyancy tank front and back end is positioned at the inboard of buoyancy tank when buoyancy tank is positioned at body upper, and the auxiliary box body at buoyancy tank middle part is positioned at the outside of buoyancy tank when buoyancy tank is positioned at body upper.So design-calculated auxiliary box body mechanical strength is big, is convenient to operation, and helps the balance flight of aircraft, is specially adapted to autogyro.
As optimization, the telescopic drive mode of described auxiliary box body is a hydraulic pressure.Hydraulic driving mode is safe and reliable, and handled easily.
As optimization, described rotary drive mechanism comprises major diameter flower wheel and the minor diameter driving wheel that is engaged with coaxial with support.So the design-calculated transmission device is simple in structure, handled easily, and the moment of transmission is big.
As optimization, the following alighting gear that also is equipped with of described buoyancy tank.This alighting gear can rise and fall for helicopter.
As optimization, sliding wheel also is housed below the described fuselage.So the design-calculated sliding wheel can supply aircraft to take off under sliding state and land.
As optimization, this aircraft is a helicopter, and the end of its propeller blade is equipped with balance weight body; Or jet engine is equipped with in the below of empennage; Or jet engine is equipped with in the below that the end of propeller blade is equipped with balance weight body and empennage.Described balance weight body can lean on gravity to force down the inclined height of propeller blade end downwards on the one hand, the own wt of balance weight body also helps to increase the centnifugal force of propeller blade on the other hand, propeller blade is evened up as much as possible, reduce the sinuousness of paddle, thereby also can reduce the inclined height of propeller blade end, making up current approaching as much as possible vertical with the blade face of propeller blade, is to increase the hoisting force of propeller by reducing the in-flight distortion of propeller in a word.The jet engine that installs additional can increase flying power for aircraft on the one hand; On the other hand can be for buoyancy tank upset back and the auxiliary box body helicopter after stretching out provide flying power, thus make autogyro possess the function of aerodone, make aircraft have higher flying speed.
As optimization, it also can be applicable to jet plane, preposition propeller aircraft and aerodone except that being used for autogyro.Present technique is applied to various existing aircrafts and all helps fuel saving, increases the load of aircraft, improves the airworthiness of aircraft, ensures flight safety better.The technology of the present invention is mainly used in the equipment helicopter.As be used for small stationary wing aircraft, can make aircraft do low-speed operations, and can not cause the accident because of stall.
In the employing after the technology technical scheme, multifunction aircraft of the present invention makes one case many usefulness of buoyancy tank, promptly has landing function waterborne, can do gliding flight again, can improve the flight safety of aircraft greatly, the buoyancy tank of position of rotation can also stop the attack of enemy's artillery fire as armour tank arbitrarily; The terminal balance weight body that is provided with of propeller blade reduces the flexural deformation of propeller blade by reducing the elevation angle of propeller blade end, increases the hoisting force of propeller greatly; The jet engine that installs additional can increase flying power for aircraft, more helps adapting to the flight environment of vehicle of various complexity, is used for helicopter and has multiple speed and multi-functional characteristics.The speed of existing autogyro generally about 290 kilometers/hour, install jet engine additional after, flying speed can be brought up to about 500 kilometers/hour.Therefore; the buoyancy tank of multifunction aircraft innovative design of the present invention promptly can be used for take-off and landing on aquathenics; can be used as the wing of expansion again; can also be as the armour tank of protection fuselage; it has waterborne, land rising and falling; performance with helicopter, aerodone and common jet plane; and flight lift is big; have a smooth flight; the energy fuel saving, the load of increase aircraft can make aircraft safety when running out of steam the road; improve the airworthiness of aircraft greatly, the safety that more helps adapting to the flight environment of vehicle of various complexity and ensure aircraft and crew.
Description of drawings
Fig. 1 is the main TV structure scheme drawing of multifunction aircraft of the present invention;
Fig. 2 is the side-looking structural representation of multifunction aircraft of the present invention;
Fig. 3 is the plan structure scheme drawing behind the multifunction aircraft buoyancy tank flip vertical of the present invention;
Fig. 4 is the structural representation of the buoyancy tank part of multifunction aircraft of the present invention.
The specific embodiment
Be further described below.As shown in the figure, multifunction aircraft of the present invention is by support 2 buoyancy tank 3 that takes off in the water supply and land to be housed below helicopter hull 1, equate about this buoyancy tank 3 is divided into two, between fuselage 1 and the support 2 rotary drive mechanism that buoyancy tank is spun upside down along fuselage outer side is housed also.Be equipped with to the flexible auxiliary box body 4 of a side front and back end of described buoyancy tank 3, be equipped with to the flexible auxiliary box body 4 of opposite side at the middle part of buoyancy tank 3, and the auxiliary box body 4 of buoyancy tank 3 front and back ends is positioned at the inboard of buoyancy tank 3 above buoyancy tank 3 is positioned at fuselage 1 time, and the auxiliary box body 4 at buoyancy tank 3 middle parts is positioned at the outside of buoyancy tank 3 above buoyancy tank 3 is positioned at fuselage 1 time.The telescopic drive mode of described auxiliary box body 4 is a hydraulic pressure, and the auxiliary box body 4 of buoyancy tank 3 front and back ends respectively is equipped with a hydraulic actuating cylinder 5, and the auxiliary box body 4 at buoyancy tank 3 middle parts is equipped with two hydraulic actuating cylinders 5.Described rotary drive mechanism comprises major diameter flower wheel 6 and the minor diameter driving wheel 7 that is engaged with coaxial with support 2, and described major diameter flower wheel 6 is semicircular gears of an inboard breach.The following alighting gear 8 that also is equipped with of described buoyancy tank 3.Below the described fuselage 1 sliding wheel 9 is housed also.The end of its propeller blade 10 is equipped with balance weight body 11, and jet engine 13 is equipped with in the below of empennage 12.
Claims (10)
1, a kind of multifunction aircraft, the buoyancy tank that takes off in the water supply and land is equipped with by support in its fuselage below, it is characterized in that equating about this buoyancy tank is divided into two, the rotary drive mechanism that buoyancy tank is spun upside down along fuselage outer side also is housed between fuselage and the support, or the rotary drive mechanism that can make buoyancy tank do vertical upset is housed between support and buoyancy tank.
2, multifunction aircraft according to claim 1 is characterized in that the left side of described buoyancy tank or right side or the left and right sides be equipped with the auxiliary box body that can outwards stretch; Outwardly directed auxiliary box body can be an one-level, also can be above multistage of secondary.
3, multifunction aircraft according to claim 2 is characterized in that the front and back end of described buoyancy tank is equipped with to the flexible auxiliary box body of a side, and be equipped with to the flexible auxiliary box body of opposite side at the middle part of buoyancy tank.
4, multifunction aircraft according to claim 3 is characterized in that the auxiliary box body of buoyancy tank front and back end is positioned at the inboard of buoyancy tank when buoyancy tank is positioned at body upper, and the auxiliary box body at buoyancy tank middle part is positioned at the outside of buoyancy tank when buoyancy tank is positioned at body upper.
5, multifunction aircraft according to claim 4 is characterized in that the telescopic drive mode of described auxiliary box body is a hydraulic pressure.
6, multifunction aircraft according to claim 1 is characterized in that described rotary drive mechanism comprises major diameter flower wheel and the minor diameter driving wheel that is engaged with coaxial with support.
7, multifunction aircraft according to claim 1 is characterized in that the following alighting gear that also is equipped with of described buoyancy tank.
8, multifunction aircraft according to claim 1 is characterized in that below the described fuselage sliding wheel being housed also.
9, according to claim 1,2,3,4,5,6,7 or 8 described multifunction aircrafts, it is characterized in that this aircraft is a helicopter, the end of its propeller blade is equipped with balance weight body; Or jet engine is equipped with in the below of empennage; Or jet engine is equipped with in the below that the end of propeller blade is equipped with balance weight body and empennage.
10, the application of multifunction aircraft of the present invention is characterized in that it except that being used for autogyro, also can be applicable to jet plane, preposition propeller aircraft and aerodone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03105090 CN1206130C (en) | 2003-03-07 | 2003-03-07 | Multifunctional airplane and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03105090 CN1206130C (en) | 2003-03-07 | 2003-03-07 | Multifunctional airplane and application thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1439578A true CN1439578A (en) | 2003-09-03 |
| CN1206130C CN1206130C (en) | 2005-06-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 03105090 Expired - Fee Related CN1206130C (en) | 2003-03-07 | 2003-03-07 | Multifunctional airplane and application thereof |
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| CN (1) | CN1206130C (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101417182B (en) * | 2007-09-15 | 2013-04-17 | 美泰有限公司 | Toy helicopter having a stabilizing bumper |
| CN103057700A (en) * | 2011-10-19 | 2013-04-24 | 孙龙骧 | Impeller wing aircraft |
| CN104554714A (en) * | 2014-12-05 | 2015-04-29 | 张立 | Splitting type undercarriage for helicopter model |
| CN104627357A (en) * | 2014-11-29 | 2015-05-20 | 韩俊峰 | Shape of small plane buoy with trapezoid and rectangle combined cross section |
| CN106458320A (en) * | 2014-04-30 | 2017-02-22 | 飞洋航空机制造开发株式会社 | Device for suppressing pitch angle fluctuation in seaplane |
| CN108275250A (en) * | 2018-03-14 | 2018-07-13 | 武汉大学 | A kind of automatically cleaning unmanned boat and its self cleaning method |
| CN111674546A (en) * | 2020-06-19 | 2020-09-18 | 南京航空航天大学 | Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft |
-
2003
- 2003-03-07 CN CN 03105090 patent/CN1206130C/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101417182B (en) * | 2007-09-15 | 2013-04-17 | 美泰有限公司 | Toy helicopter having a stabilizing bumper |
| CN103057700A (en) * | 2011-10-19 | 2013-04-24 | 孙龙骧 | Impeller wing aircraft |
| CN106458320A (en) * | 2014-04-30 | 2017-02-22 | 飞洋航空机制造开发株式会社 | Device for suppressing pitch angle fluctuation in seaplane |
| CN104627357A (en) * | 2014-11-29 | 2015-05-20 | 韩俊峰 | Shape of small plane buoy with trapezoid and rectangle combined cross section |
| CN104554714A (en) * | 2014-12-05 | 2015-04-29 | 张立 | Splitting type undercarriage for helicopter model |
| CN108275250A (en) * | 2018-03-14 | 2018-07-13 | 武汉大学 | A kind of automatically cleaning unmanned boat and its self cleaning method |
| CN108275250B (en) * | 2018-03-14 | 2019-02-19 | 武汉大学 | A kind of automatically cleaning unmanned boat and its self cleaning method |
| CN111674546A (en) * | 2020-06-19 | 2020-09-18 | 南京航空航天大学 | Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1206130C (en) | 2005-06-15 |
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