WO2012113158A1 - Helicopter - Google Patents

Helicopter Download PDF

Info

Publication number
WO2012113158A1
WO2012113158A1 PCT/CN2011/071328 CN2011071328W WO2012113158A1 WO 2012113158 A1 WO2012113158 A1 WO 2012113158A1 CN 2011071328 W CN2011071328 W CN 2011071328W WO 2012113158 A1 WO2012113158 A1 WO 2012113158A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuselage
helicopter
cylinder
propeller
according
Prior art date
Application number
PCT/CN2011/071328
Other languages
French (fr)
Chinese (zh)
Inventor
王万强
Original Assignee
Wang Wanqiang
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 Wang Wanqiang filed Critical Wang Wanqiang
Priority to PCT/CN2011/071328 priority Critical patent/WO2012113158A1/en
Publication of WO2012113158A1 publication Critical patent/WO2012113158A1/en

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/04Helicopters
    • B64C27/08Helicopters with two or more rotors

Abstract

A helicopter includes a fuselage (1) and propellers (3). The propellers (3) are provided under the fuselage (1). The helicopter solves the problem of prior art that the low carrier capacity is caused by the low lifting capacity and improves the carrier capacity remarkably.

Description

 TECHNICAL FIELD The present invention relates to an aircraft. Specifically a helicopter. BACKGROUND OF THE INVENTION A vertical take-off and landing propeller aircraft, that is, a helicopter, includes a fuselage and a propeller mounted to the fuselage. The airflow generated by the propeller operation provides the aircraft with the propulsion power for raising the aircraft and the forward power for moving the aircraft horizontally. The propeller of the current vertical take-off and landing aircraft is installed above the fuselage. The airflow generated when the propeller is running has both the lifting force for lifting the fuselage and the pressure for lowering the fuselage, because the upward lifting force is greater than the downward pressure. Therefore, the aircraft can be lifted up while the propeller is running. At the same time, however, since the downward pressure offsets part of the upward lifting efficiency, the propeller's lifting efficiency is not high, resulting in the current carrying capacity of the helicopter is low. SUMMARY OF THE INVENTION The technical problem to be solved by the present invention is to overcome the shortcomings of the existing helicopter lifting efficiency and resulting in low carrying capacity, and to provide a helicopter that greatly improves the carrying capacity.

 The helicopter provided by the present invention includes a fuselage and a propeller, and the propeller is disposed below the fuselage.

 Preferably, a plurality of the propellers are disposed below the fuselage.

 As a further preferred embodiment, a plurality of the propellers are symmetrically disposed below the fuselage, and the propellers in the symmetrical position rotate in opposite directions.

 Preferably, the two sides of the fuselage are symmetrically disposed with the body stabilization wings along the body. As a further preferred, the fuselage stabilizing wings are flexible.

 Preferably, both sides of the fuselage are provided with horizontal thrust means for providing forward power to the aircraft.

As a further preferred embodiment, the horizontal thrust means are symmetrically disposed on both sides of the fuselage. Preferably, a plurality of length adjustable legs are disposed under the fuselage. Preferably, the leg comprises a cylinder, the cylinder comprises a cylinder connected to the fuselage, the cylinder is provided with a piston, the piston is connected with a piston rod, and the piston rod is further One end is a free end, and the helicopter further includes a pneumatic adjustment device that delivers compressed gas to the cylinder of the cylinder.

 Preferably, the body is provided with a boarding gate, the boarding gate is located at an end of the fuselage, and the gate of the boarding gate is opened downward.

 Compared with the prior art, the helicopter provided by the invention has the following beneficial effects:

1. The helicopter of the present invention has a propeller disposed on the bottom plate of the fuselage. Since the propeller is disposed below the fuselage, the airflow generated by the propeller operation exerts an upward lifting force on the airframe and a forward power for advancing the fuselage. The downward pressure on the fuselage, compared with the technical solution of placing the propeller above the fuselage, can greatly improve the lifting efficiency of the propeller, thereby greatly improving the carrying capacity of the helicopter.

 2. A plurality of the propellers are symmetrically arranged under the fuselage, so that the overall force of the fuselage is uniform, and the propellers in the symmetrical position rotate in opposite directions, eliminating the rotational torque generated by the rotation of the propeller, thereby improving the stability of the propeller aircraft.

 3. The two sides of the fuselage are symmetrically arranged along the fuselage to provide an organic body stable wing to improve the stability of the aircraft.

 4. The horizontal thrust device for providing forward power to the aircraft is symmetrically arranged on both sides of the fuselage. The horizontal thrust device can increase the forward power of the aircraft and increase the flight speed.

 5. There are also multiple legs under the fuselage to provide stable support when the aircraft is parked.

6. The door of the gate is opened toward the propeller so that the door can block the operation of the propeller when it is opened. The airflow generated by the passenger affects the passengers to get on or off the aircraft or the operator. BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a side elevational view of one embodiment of a helicopter of the present invention;

2 is a bottom plan view of one embodiment of a helicopter of the present invention. 1 is a side elevational view of one embodiment of a helicopter of the present invention, and FIG. 2 is a bottom plan view of one embodiment of a helicopter of the present invention. As shown in FIG. 1 and FIG. 2, the helicopter provided by the present invention comprises a fuselage 1 and a propeller 3 for powering the aircraft, the propeller 3 is disposed below the body 1. In the present embodiment, the propeller 3 is provided on the bottom plate of the body 1. Since the propeller 3 is disposed below the fuselage 1, the airflow generated by the operation of the propeller 3 exerts an upward lifting force on the fuselage 1 and a forward power for advancing the fuselage 1, and does not exert downward pressure on the fuselage 1, and Compared with the technical solution in which the propeller 3 is disposed above the fuselage 1, the lifting efficiency of the propeller 3 can be greatly improved, thereby greatly improving the carrying capacity of the helicopter.

 In the above embodiment, a plurality of the propellers 3 are symmetrically disposed under the fuselage 1 , and the lift generated by the plurality of the propellers 3 uniformly acts on the fuselage 1 to uniformly force the whole body 1 to prevent the machine. The body 1 loses balance due to uneven force and turns over. The symmetrical position of the propeller rotates in the opposite direction, which eliminates the torque generated by the rotation of the propeller and makes the helicopter fly. The number and size of the propellers 3 can be determined according to the size of the fuselage 1 and the required carrying capacity. As shown in Fig. 2, twelve propellers are disposed under the fuselage 1, and twelve propellers are arranged in four rows and three columns symmetrically with respect to the center line on the bottom plate of the body 1.

 In the above embodiment, the two sides of the fuselage 1 are symmetrically disposed with the living body stabilizing wing 2 along the fuselage 1 , and the fuselage stabilizing wing 2 increases the force receiving area of the fuselage 1 . The fuselage 1 is more evenly stressed. On the other hand, by changing the flow direction of the airflow, the helicopter's left and right tilt in flight can be reduced, so that the stability of the helicopter can be improved. In the present embodiment, the fuselage stabilizing wing 2 has a certain flexibility, so that the force change of the fuselage 1 is more moderate, and at the same time, the stability of the flight of the aircraft is further improved.

 In the above embodiment, the two sides of the fuselage 1 are symmetrically provided with a horizontal thrust device 5 for providing forward power to the aircraft, and the horizontal thrust device 5 can increase the forward power of the aircraft and increase the flight speed. The number of horizontal thrust devices 5 can be determined based on the size of the fuselage 1 and the required flight speed. The forward power of the helicopter provided by the present invention may be provided only by the horizontal thrust device 5 or the propeller 3, or may be provided by the horizontal thrust device 5 and the propeller 3.

In the above embodiment, a plurality of length adjustable legs are disposed under the fuselage. As shown in Figures 1 and 2, the legs 4 are provided on the floor of the helicopter and are located in the gap between the plurality of said propellers 3. The leg 4 includes a cylinder, the cylinder includes a cylinder connected to the fuselage, a piston is disposed in the cylinder, a piston rod is connected to the piston, and the other end of the piston rod is a free end. Can be supported on the ground directly or through other support devices On. The helicopter further includes a pneumatic adjusting device for conveying compressed gas to the cylinder of the cylinder, such as using an air pump to deliver compressed gas pressure to the cylinder cylinder of each leg to push the piston and the piston rod to move downward, the piston rod from the cylinder The extension of the body lengthens the length of the leg. Similarly, when the piston rod is retracted into the cylinder, the length of the leg is shortened. When the airplane is falling, part of the legs 4 first land, and the gas in the first landing 4 is squeezed out and squeezed into the unlanded legs 4, causing the length of the unlanded legs 4 to increase as soon as possible, preventing the first The landing leg 4 is concentrated and deformed. In addition, when landing, the length of the leg 4 can cushion the force of the landing body, not only protect the fuselage, but also reduce the passengers or cargo in the fuselage. In addition, in the case where the helicopter is parked, it is inevitable that there will be unevenness. As mentioned above, the adjusting device can support each leg 4 to be evenly supported on the ground, preventing partial leg 4 from being concentrated, and also making the aircraft Parking is more stable. The adjusting device may also be a hydraulic adjusting device, and accordingly, the leg is a cylinder.

 In the above embodiment, the gate is located at the end of the body 1 to allow sufficient space for passengers to board the aircraft. In this embodiment, the aircraft has a gate at both ends, as shown in Figure 2.

 In the above embodiment, the aircraft door 6 of the gate is opened downward to allow the aircraft door 6 to block the air flow generated by the operation of the propeller 3 when it is opened, affecting the passengers to get on or off the aircraft or the operation of the operator.

 The above embodiments are merely exemplary embodiments of the invention, and are not intended to limit the invention, and the scope of the invention is defined by the claims. A person skilled in the art can make various modifications or equivalents to the invention within the spirit and scope of the invention, and such modifications or equivalents are also considered to be within the scope of the invention.

Claims

Rights request
 A helicopter comprising a fuselage and a propeller, characterized in that: said propeller is disposed below said fuselage.
 2. The helicopter according to claim 1, wherein: a plurality of said propellers are disposed below said fuselage.
 3. The helicopter according to claim 2, wherein: said plurality of said propellers are symmetrically disposed below said fuselage, and said symmetrical positions of said propellers rotate in opposite directions.
 4. The hoist according to claim 1; wherein: the two fuselage bodies of the fuselage are symmetrically disposed along the body.
 5. The helicopter according to claim 4; wherein: the fuselage stabilizing wing has flexibility.
 6. The helicopter according to claim 1, wherein: both sides of the fuselage are provided with horizontal thrust devices for providing forward power to the aircraft.
 7. The helicopter j according to claim 6, wherein: the horizontal thrust device is symmetrically disposed on both sides of the fuselage.
 8. The lift j of claim 1 wherein: a plurality of length adjustable legs are disposed beneath the fuselage.
 9. The lift j according to claim 8, wherein: the leg comprises a cylinder, the cylinder comprises a cylinder connected to the fuselage, the cylinder is provided with a piston, and the piston is connected There is a piston rod, the other end of which is a free end, and the helicopter further includes a pneumatic adjusting device for delivering compressed gas to the cylinder of the cylinder.
 10. The helicopter according to claim 1, wherein: the body is provided with a gate, the gate is located at an end of the fuselage, and the gate of the gate is opened downward .
PCT/CN2011/071328 2011-02-25 2011-02-25 Helicopter WO2012113158A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2011/071328 WO2012113158A1 (en) 2011-02-25 2011-02-25 Helicopter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2011/071328 WO2012113158A1 (en) 2011-02-25 2011-02-25 Helicopter

Publications (1)

Publication Number Publication Date
WO2012113158A1 true WO2012113158A1 (en) 2012-08-30

Family

ID=46720103

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2011/071328 WO2012113158A1 (en) 2011-02-25 2011-02-25 Helicopter

Country Status (1)

Country Link
WO (1) WO2012113158A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013000168A1 (en) * 2013-01-09 2014-07-10 microdrones GmbH Aerodynamic Multicopter / Quadrocopter
US10239615B2 (en) 2014-01-07 2019-03-26 4525612 Canada Inc. Personal flight vehicle

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5178344A (en) * 1991-09-13 1993-01-12 Vaclav Dlouhy VTOL aircraft
CN2366355Y (en) * 1999-01-15 2000-03-01 李世震 Rotary wings helicopter
US20060266881A1 (en) * 2005-01-14 2006-11-30 Hughey Electricopter Corporation Vertical takeoff and landing aircraft using a redundant array of independent rotors

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5178344A (en) * 1991-09-13 1993-01-12 Vaclav Dlouhy VTOL aircraft
CN2366355Y (en) * 1999-01-15 2000-03-01 李世震 Rotary wings helicopter
US20060266881A1 (en) * 2005-01-14 2006-11-30 Hughey Electricopter Corporation Vertical takeoff and landing aircraft using a redundant array of independent rotors

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013000168A1 (en) * 2013-01-09 2014-07-10 microdrones GmbH Aerodynamic Multicopter / Quadrocopter
US10239615B2 (en) 2014-01-07 2019-03-26 4525612 Canada Inc. Personal flight vehicle
US10464671B2 (en) 2014-01-07 2019-11-05 4525612 Canada Inc. Personal flight vehicle

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