WO1999052759A1 - Hydravion a coque modifie a partir d'un avion - Google Patents

Hydravion a coque modifie a partir d'un avion Download PDF

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Publication number
WO1999052759A1
WO1999052759A1 PCT/CN1999/000048 CN9900048W WO9952759A1 WO 1999052759 A1 WO1999052759 A1 WO 1999052759A1 CN 9900048 W CN9900048 W CN 9900048W WO 9952759 A1 WO9952759 A1 WO 9952759A1
Authority
WO
WIPO (PCT)
Prior art keywords
hull
wing
sides
fuselage
modified
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.)
Ceased
Application number
PCT/CN1999/000048
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English (en)
Chinese (zh)
Inventor
Qinghai Ren
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to AU31361/99A priority Critical patent/AU3136199A/en
Publication of WO1999052759A1 publication Critical patent/WO1999052759A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C37/00—Convertible aircraft
    • B64C37/02—Flying units formed by separate aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion
    • B60V1/08—Air-cushion wherein the cushion is created during forward movement of the vehicle by ram effect
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V3/00—Land vehicles, waterborne vessels, or aircraft, adapted or modified to travel on air cushions
    • B60V3/08—Aircraft, e.g. air-cushion alighting-gear therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/04—Aircraft not otherwise provided for having multiple fuselages or tail booms

Definitions

  • the invention relates to a sea spacecraft modified by an aircraft.
  • high-speed ships that can fly at low altitudes on the sea include hydrofoil, hovercraft and powered hovercraft.
  • the ground-effect wing sea low-altitude spacecraft is a special-powered air-cushioned ground-effect wing ship.
  • the speed will be doubled or faster, and the speed can exceed 400 kilometers per hour.
  • this type of spacecraft lacks high reserve and can only Flying above the ground effect height within ten meters, it will stall and crash when it crosses the ground effect height; it is also because it can only fly within a limited ground effect height area, and it cannot avoid the morning fog on the sea, ships and sudden Strong winds and waves.
  • the authorization notice number is CN2258855Y
  • the Chinese utility model patent named "Low-Altitude Airship” discloses a hull modified by removing a landing gear by a jet engine, and connected to the hull as the main body of the hull, that is, the front end below the hull head.
  • a pontoon and a low-altitude spacecraft made of buoys connected to both sides of the bottom middle part of the hull through a support frame and buoys fixed to the side walls of the pontoon. It is the product of a combination of an aircraft and a ground-effect wing ship. Flying in the ground effect zone of 3 to 10 meters above the sea, it can also fly beyond the ground effect altitude. It overcomes the fundamental shortcomings of dynamic air cushion ground effect wing ships.
  • the object of the present invention is to provide a floating, cushioning and high-speed low-altitude navigation flight in the ground effect area and beyond the ground effect height, with stronger flight capability, higher speed, simple production, and low cost. Spaceship at sea.
  • An maritime spacecraft modified by an aircraft includes a fuselage including a fuselage, a steering tail, a horizontal tail, a wing and an engine, and It is characterized by: It consists of an aircraft body, steering fins and horizontal fins at the rear of the fuselage, jet engines located on both sides of the rear of the fuselage, and wings on both sides of the rear of the fuselage, fixed to the hull at the bottom of the fuselage, fixed to Jet engines with adjustable downtilt angles on both sides of the hull head, air walls located on both sides of the hull and connected to the lower wing surface of the wing through the connecting body, and ground effects fixed between the hull and the air walls on both sides of the hull Wing composition.
  • the invention can also be a double-body maritime spacecraft modified by two jets and sharing an air wall in the middle.
  • the invention can make cushion-like helicopter flight under static or dynamic conditions, and can flexibly avoid morning fog on the sea, ships and sudden strong winds and waves; and the speed is faster; especially when it is made into a catamaran, Passenger and cargo volume can be greatly increased. Tests prove that the present invention achieves the intended design purpose.
  • Figure 1 is a front view of a monolithic maritime spacecraft modified with a jet.
  • Figure 2 is a top view of a monolithic maritime spacecraft modified by a jet.
  • Figure 3 is a left side view of a monolithic maritime spacecraft modified with a jet.
  • Figure 4 is a front view of a catamaran maritime spacecraft modified with two jets.
  • Figure 5 is a top view of a catamaran maritime spacecraft modified with two jets.
  • Figure 6 is a left side view of a catamaran maritime spacecraft modified with two jets.
  • Fig. 7 is a schematic diagram of a rotation mechanism of a jet engine with adjustable downtilt angle.
  • the present invention includes an aircraft body 1, steering fins 2 located on both sides of the fuselage 1, horizontal fins 3 mounted on the steering fins 2, jet engines 4 located on both sides of the rear portion of the fuselage 1, and the fuselage 1
  • the wing 5 on the two sides of the middle and rear, the above-mentioned components together constitute a complete aircraft fuselage, as long as the landing gear of the aircraft is removed, a complete fuselage can be obtained. It can be converted from various retired and intact aircraft, and its safety factor is sufficient to make the fuselage of a maritime spacecraft.
  • the invention also includes a hull 6 fixed to the bottom of the hull 1, a jet engine 7 with an adjustable downtilt fixed to both sides of the head of the hull 6, and located on both sides of the hull 6 and connected to the underside of the wing 5 through the connecting body 8 and the wing 5.
  • Air walls 9 fixed on the airfoil are ground effect wings 10 and passenger cabins 16 fixed between the hull 6 and the air walls 9 on both sides. These parts are made of aluminum alloy and are riveted to each other.
  • the present invention can also be modified with two aircrafts and shared between them A double-body maritime spaceship with an air wall 9.
  • the rotation mechanism of the jet engine 7 with adjustable downtilt of the present invention includes: a connecting rod 11, a hydraulic cylinder 12, a piston push rod 13, a connection point 14, a pivot point 15, and a hydraulic cylinder 12 through the piston push rod 13 That is, the jet engine 7 can be tilted down by an angle.
  • This kind of maritime spacecraft can not only perform low-altitude flight in the ground effect zone but also beyond the height of the ground effect; it can not only be used for floating drainage and low-altitude high-speed navigation, but also can be used for static or dynamic padding and non-stop flying. It does not need a certain speed to take off. As long as the air is compressed by an engine with adjustable downtilt and blown into the ground effect wing 10 to form a power increase, you can use the two sides of the ground effect wing 10 to increase power.
  • the air chamber formed by the air wall 9 and the flaps of the wing 5 allows air to flow through the wing 5 to cause negative pressure lift, so that the spacecraft can be statically or dynamically lifted to avoid obstacles encountered when sailing at high speed on the sea surface. Thing.
  • this spacecraft adopts the overall aircraft transformation plan. As long as the performance is intact, even retired jets can be used, so the manufacturing is simple and the cost is low.
  • the main engine The jet engine 4 is a HK-8 type, and the jet engine with adjustable downtilt angle 7 is a HK-12 type.
  • the total power is 104KN ⁇ 2 and 11750KW ⁇ 2, of which ⁇ is dimensionless transport efficiency, the average speed is 300-350km / h, the range is 170km, the take-off weight is 200 tons, and the passenger capacity is 360 people.
  • ⁇ dimensionless transport efficiency
  • the average speed is 300-350km / h
  • the range is 170km
  • the take-off weight is 200 tons
  • the passenger capacity is 360 people.
  • the invention is modified by an aircraft, which can perform cushioned helicopter flight under static or dynamic conditions, and can flexibly avoid morning fog on the sea, ships and sudden strong winds; moreover, the speed is faster; especially when made When the spacecraft is built, the passenger and cargo volume can be greatly increased.
  • the invention can be widely used in various sea passenger and freight transportation.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un hydravion à coque modifié à partir d'un avion qui comprend un cadre d'avion dépourvu de train d'atterrissage arrière, une coque fixée à la partie inférieure de la cellule d'avion, un réacteur à inclinaison réglable vers le bas et relié aux deux parties de la coque, des parois à gaz placées sur les deux côtés de la coque et reliées aux ailes de l'avion et des ailes à effet de sol fixées entre la coque et les deux parois de gaz. L'hydravion peut voler dans la zone à effet de sol ou au-dessus de cette zone en état de flottaison, à basse altitude, à haute vitesse ou sur un coussin d'air. L'hydravion est spécialement conçu pour affronter un brouillard en pleine mer, des vents violents et une mer houleuse. Lors d'un vol à haute vitesse au-dessus de la zone à effet de sol, l'hydravion assure un vol sans danger à des vitesses élevées. L'invention trouve une application dans le domaine du transport de marchandises et de passagers par voie maritime.
PCT/CN1999/000048 1998-04-08 1999-04-07 Hydravion a coque modifie a partir d'un avion Ceased WO1999052759A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU31361/99A AU3136199A (en) 1998-04-08 1999-04-07 A seaplane modified from an airplane

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN98101163.2 1998-04-08
CN98101163A CN1075012C (zh) 1998-04-08 1998-04-08 利用飞机改装的海上飞船

Publications (1)

Publication Number Publication Date
WO1999052759A1 true WO1999052759A1 (fr) 1999-10-21

Family

ID=5216510

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN1999/000048 Ceased WO1999052759A1 (fr) 1998-04-08 1999-04-07 Hydravion a coque modifie a partir d'un avion

Country Status (3)

Country Link
CN (1) CN1075012C (fr)
AU (1) AU3136199A (fr)
WO (1) WO1999052759A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003080436A1 (fr) * 2002-03-22 2003-10-02 Sopravia Inc. Avion a trois fuselages et familles d'avions de ce type
GB2434785A (en) * 2003-06-24 2007-08-08 John Edward Randell Twin fuselage aircraft

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1116196C (zh) * 1999-11-03 2003-07-30 北海达洋翼船有限公司 兼有高飞功能的地效飞行器
CN109109873A (zh) * 2017-06-24 2019-01-01 赵润生 气垫式悬浮列车及整体路基轨道系统
CN109606676A (zh) * 2018-12-14 2019-04-12 中国特种飞行器研究所 一种串列翼式水陆两栖飞机

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2120990A (en) * 1982-05-28 1983-12-14 Kjoelseth Paul Ground effect vehicle or aerofoil boat
US4705234A (en) * 1985-04-10 1987-11-10 Bourn Ronald L Ram wing surface effect vehicle
US4712630A (en) * 1984-08-01 1987-12-15 Albert Blum Ground effect vehicle
FR2623468A1 (fr) * 1987-11-24 1989-05-26 Armand Georges Avions et hydravions multifuselages a trois surfaces portantes
CN1047056A (zh) * 1989-05-12 1990-11-21 柏晓钟 飞艇(又名：地表效应飞机)
GB2247216A (en) * 1990-08-20 1992-02-26 Tomishige Osako Altitude control apparatus for a ground effect winged vehicle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2120990A (en) * 1982-05-28 1983-12-14 Kjoelseth Paul Ground effect vehicle or aerofoil boat
US4712630A (en) * 1984-08-01 1987-12-15 Albert Blum Ground effect vehicle
US4705234A (en) * 1985-04-10 1987-11-10 Bourn Ronald L Ram wing surface effect vehicle
FR2623468A1 (fr) * 1987-11-24 1989-05-26 Armand Georges Avions et hydravions multifuselages a trois surfaces portantes
CN1047056A (zh) * 1989-05-12 1990-11-21 柏晓钟 飞艇(又名：地表效应飞机)
GB2247216A (en) * 1990-08-20 1992-02-26 Tomishige Osako Altitude control apparatus for a ground effect winged vehicle

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003080436A1 (fr) * 2002-03-22 2003-10-02 Sopravia Inc. Avion a trois fuselages et familles d'avions de ce type
GB2434785A (en) * 2003-06-24 2007-08-08 John Edward Randell Twin fuselage aircraft

Also Published As

Publication number Publication date
AU3136199A (en) 1999-11-01
CN1075012C (zh) 2001-11-21
CN1231247A (zh) 1999-10-13

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