KR101755109B1 - Aircraft with Rotational Cockpit - Google Patents

Aircraft with Rotational Cockpit Download PDF

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Publication number
KR101755109B1
KR101755109B1 KR1020150120086A KR20150120086A KR101755109B1 KR 101755109 B1 KR101755109 B1 KR 101755109B1 KR 1020150120086 A KR1020150120086 A KR 1020150120086A KR 20150120086 A KR20150120086 A KR 20150120086A KR 101755109 B1 KR101755109 B1 KR 101755109B1
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KR
South Korea
Prior art keywords
flight
cockpit
propeller
pilot
base
Prior art date
Application number
KR1020150120086A
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Korean (ko)
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KR20170018292A (en
Inventor
김철희
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김철희
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Publication of KR101755109B1 publication Critical patent/KR101755109B1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
    • B64D11/0639—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with features for adjustment or converting of seats
    • B64D11/064—Adjustable inclination or position of seats
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
    • B64D11/0689—Arrangements of seats, or adaptations or details specially adapted for aircraft seats specially adapted for pilots
    • B64C2700/6267—

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

Abstract

The present invention relates to a flight direction control method of a flying object in which at least one propeller for generating lift is installed and a pilot on board a pilot controls a pilot while flying a gas, and a flying object using the flying direction, A turning flight mode in which the flight direction is controlled while the gas is turning by the adjustment of the pilot, and a rotational flight mode in which the cockpit is rotated in the flight direction by the adjustment of the pilot, Let's fly.
Therefore, in general, a flight to a destination causes a rapid flight in a turning flight mode, and in a flight space requiring a narrow flight space and observation and visibility, only a cockpit or a sight camera is rotated in the flight direction And controlling the main propeller and the auxiliary propeller so as to enable the aircraft to fly in the flight direction, thereby providing easy observation and securing the view of the airplane.

Description

Aircraft with Rotational Cockpit

The present invention relates to a flight direction control method of a flying object in which at least one propeller for generating lifting force is installed and a pilot on board a pilot controls a pilot while flying a gantry and a flight body using the control method. In the flight space where the narrow flight space and observation and vision are required, only the cockpit or the sight camera is rotated in the flight direction without the rotation of the gas, and then the main propeller And a sub-propeller so as to allow the aircraft to fly in the direction of flight, thereby facilitating easy observation and securing of visibility.

For a fixed-wing aircraft, turning can be accomplished by turning. In the case of a rotary-wing aircraft that gains lift by a rotating wing, it can be divided into two types: a helicopter The same flywheel unit can achieve redirecting through the rotation of the aircraft during stopping flight or moving flight, and can be used for a helicopter UAV (MAV (Micro Air Vehicle), a small unmanned aerial vehicle For example, a recently developed drone) is configured to proceed in a desired direction without rotating the gas.

In the case of the fixed wing or the rotating wing, the flying body such as the helicopter has a disadvantage in that it is difficult to start or operate when airtight flight or activity area is relatively narrow in terms of maneuverability and size. However, when the unmanned air vehicle is made small, It is possible to use it as a spy or surveillance flight vehicle as well as a toy.

While the research of the above mentioned unmanned aerial vehicle is being rapidly activated, the one or two manned aerial vehicle using the lift is also progressing with the activation of the above mentioned unmanned aerial vehicle.

However, in all existing aircraft, the cockpit is fixed on the airframe in a fixed direction. In addition, the direction of flight is defined by forward flight in which the aircraft flew in front of the pilot in a fixed posture in a fixed cockpit, lateral flight in which the aircraft flew to the left and right sides of the pilot, and backward flight in which the aircraft flew to the rear of the pilot can do. Therefore, existing aircraft must be redirected before the forward flight of the aircraft is established. If the aircraft does not move forward and the forward flight of the aircraft is not ahead of the pilot, it is not a forward flight.

However, when the unmanned aerial vehicle and the manned airplane described above fly while changing the direction of the flight, since the aircraft flies along the flight direction, a path corresponding to the turning angle necessarily occurs. The space utilization is not efficient due to the fact that the direction change is performed only when the space of the space is secured.

In addition, in a conventional air vehicle, an advance forward flight can not be established when the direction of the airplane is changed unless the aircraft rotates. That is, in order to observe and observe the left and right sides and the back of the vehicle except for the front when the direction of the flight is changed to the right or left, the space and the path required by the vehicle are required as described above. In such a case, it is difficult to ensure visibility. In such a case, the pilot must secure his / her field of view by rotating the head directly in a state where the gas is not moving.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a general flight direction control method for switching a flight direction while a vehicle is turning in response to a request of a pilot, By turning the main propeller and auxiliary propeller suitable for the direction of flight of the aircraft when the direction of flight is changed after the rotation in the direction of flight, it is possible to rotate the aircraft without turning the aircraft, So that it is possible to efficiently view and observe a narrow flight space even in a narrow flight space.

The above object is achieved by a control apparatus for an airplane in which at least one propeller for generating lift is installed and a pilot 104 mounted on a base 102 controls a flight direction control In the turning flight mode in which the flight direction is controlled while the airframe 102 is being turned by the adjustment of the pilot 106 and the adjustment of the pilot 106 is carried out by the adjustment of the pilot 106, 110) is selected to select one of the rotational flight modes in which the vehicle is rotated in the direction of flight.

When the pilot 106 is adjusted by the pilot 104, the control unit controls the propeller so that the base 102 is switched to the stop state. It is preferable to rotate the cockpit 110 in an angle and direction adjusted by the control section 106 and to control the rotation and direction of the propeller which is switched in accordance with the direction to fly.

If the propeller is composed of at least two propellers, it is preferable that at least one main propeller and at least one or more auxiliary propellers are reset in accordance with the direction of flight of the airframe 102.

The main propeller and the auxiliary propeller are controlled immediately before the direction change of the base 102 to change the direction of flight so that the base 102 is stopped from flying and the main propeller and auxiliary propeller It is preferable to reset the main propeller and the auxiliary propeller which are reset and fly.

In addition, the cockpit 110 may be installed on either the upper or lower part of the base 102.

By turning on and off the rotary direction switch and the rotation angle switch, which are provided on the control panel 108 provided on the cockpit 110 and stored in different rotational directions and different rotational angles, respectively, It is preferable to immediately switch to the flight direction.

According to another aspect of the present invention, there is provided a cockpit in which a cockpit of the present invention rotates includes a base 102 configured to fly with at least one propeller for generating lifting force; And a cockpit 110 installed to be rotatable 360 degrees independently from the base 102. A pilot 104 boarded on the cockpit 110 adjusts a cockpit 106 installed in the cockpit 110, The aircraft 102 does not rotate but only rotates in the flight direction of the cockpit 110 to fly.

According to the present invention, it is possible to adjust the flight direction while the aircraft turns in accordance with a desired turning flight mode. When the pilot selects the rotation flight mode, the propeller is controlled and stopped during the flight direction control through the pilot, The cockpit is rotated in the direction in which the cockpit is rotated, and the propeller is reset and rotated so as to fly in the adjusted direction, so that the cockpit is rotated in the adjusted flight direction in the state where the gas is not rotated, So that it is possible to change the direction immediately without turning the vehicle so as to change the direction of flight, so that the flight space can be efficiently utilized.

In addition, in order to secure visibility during flight, only the cockpit can be rotated in the desired direction and angle while maintaining the direction of flight, thereby enabling forward, reverse, and side flight.

1 is a schematic view showing a flying body according to the present invention flying at 12 o'clock.
FIG. 2 is a diagram illustrating a process in which a flying object according to the present invention changes direction while flying in a swivel mode; FIG.
FIG. 3A is a view showing a state in which the air vehicle according to the present invention is stopped to change direction at 3 o'clock in the state of FIG. 1; FIG.
FIG. 3B is a view showing a state where the cockpit is rotated at 3 o'clock and stopped after the airframe of the aircraft according to the present invention is not rotated.
4 is a view showing a state in which the cockpit is rotated and stopped when the air vehicle according to the present invention is turned in the direction of 5 o'clock without rotating the gas in the state of Fig.

A method of controlling a direction of a flying object according to the present invention and a flying object 100 using the same will be described with reference to FIGS. 1 to 4. FIG.

The air vehicle 100 according to the present invention is generally provided with one or a plurality of rotor blades (hereinafter referred to as propellers), and a steering device (not shown) for adjusting a flow direction of air is mounted on the propeller, The pilot 104 operated by the pilot 104 controls the flight direction by operating the pilot 106 so that the steering directions of the air can be adjusted by adjusting the flow directions of the respective steering devices.

FIG. 1 is a view showing a state in which a flight body 100 according to the present invention is viewed from above. According to the present invention, a cockpit 110 is installed on a base 102 so as to be rotatable by 360 degrees, The driving mechanism for rotating the cockpit 110 can be easily adopted by a person having ordinary skill in the art in a conventional manner, A detailed description thereof will be omitted.

Hereinafter, the control method for controlling the flying direction of the flying body 100 and the flying body 100 according to the present invention will be described, and the description of the flying body 100 will be described while explaining the flying direction control method.

First, the air vehicle 100 according to the present invention will be described on the assumption that four propellers W, X, Y, and Z are installed and driven as shown in FIG. 1 in consideration of flight stability of the base 102 , Which can be installed and driven by one or more than one, so that it is not limited thereto.

As shown in FIG. 1, the base 102 travels in the direction of the arrow (12 o'clock). At this time, the cockpit 110 is also adjusted to watch the direction of the arrow.

Therefore, when the base 102 according to the present invention is selected to fly in the circling flight mode, when the pilot 104 manipulates the control plane 106 to adjust the flight direction as shown in FIG. 2, By flying along, high-speed flight is possible.

At this time, the cockpit 110 is maintained in a fixed state, and a steering device installed on each of the propellers W, X, Y, and Z controls the flow direction of the air in accordance with a direction control signal by the steering wheel 106 Thereby enabling the base 102 to pivot along the locus (turning path) of the arrow shown in Fig.

On the other hand, when the base body 102 shown in Fig. 1 is flying in the direction of the arrow, the propellers W and X positioned in front of the flight direction among the propellers become the main propellers W and X as the main shafts, The propellers Y and Z become auxiliary propellers Y and Z serving as an auxiliary to fly the airframe 102.

When the pilot 104 is adjusted to the 3 o'clock position as shown in FIG. 3A after the pilot 104 is selected, the control unit (not shown) controls the propellers W, X, Y, Z) is driven to cause the propeller W, X, Y, Z to control the flow of air, thereby stopping the flying body 102 in flight, The cockpit 110 is rotated in the direction of 3 o'clock to stop the pilot 104 so that the pilot 104 can watch the front of the flight direction.

In addition, the control unit resets the main propeller of the auxiliary propellers (Y, Z) that have assisted with the propellers (W, X) that have become main axes until immediately before the direction control by the control point 106 to X, Z, W, and Y to drive and control the steering apparatus, thereby allowing the base 102 to fly in the 3 o'clock direction.

Meanwhile, when the pilot rotates the steering wheel 106 to the right by about 30 degrees while flying in the state of FIG. 3B after selecting the rotational flight mode, the pilot is adjusted to the 5 o'clock direction as shown in FIG. 4, (W, X, Y, Z) controls the flow of air by driving the steering devices installed on the respective propellers W, X, Y, Z so that the propeller W, 4, the control unit rotates the cockpit 110 to the right by about 30 degrees so as to face the 5 o'clock direction, and stops the pilot 104 so that the pilot 104 can see the front of the flight direction.

In this case, the control unit also sets the main propeller among the auxiliary propellers (W, Y) that has assisted the propeller (X, Z) that has become the main shaft until just before the direction control by the control unit 106 as at least two of X, And the auxiliary propeller is reset by the auxiliary propeller to either or both of the propellers W and Z to drive and control the steering device so that the base 102 can fly at 5 o'clock.

The pilot vehicle 100 according to the present invention drives and controls the steering device installed on each of the propellers W, X, Y and Z when the pilot 104 adjusts the pilot 106 in the rotational flight mode, (102) is stopped, the cockpit (110) is rotated in the direction to be adjusted, and the main propeller and the auxiliary propeller are reset to drive and control the steering device so that the airframe (102) So that the flight space can be efficiently utilized.

The air vehicle 100 according to the present invention is provided with at least one rotation direction switch (not shown) and a rotation angle switch (not shown) on the control panel 108 provided in the cockpit 110, 104 and the desired rotation direction (clockwise or counterclockwise direction) and the angle (0 to 360) to be rotated are turned on respectively so that the desired direction and angle The cockpit 110 is rotated and stopped to allow the base 102 to fly in a desired direction and angle.

In addition, when a rotation angle switch having rotation angles such as 90 °, 180 °, 270 ° and 360 ° is provided and the rotation angle switch is turned on, the cockpit 110 is rotated and stopped according to the set direction and the rotation angle , It is possible to reconfigure the main propeller and auxiliary propeller of each propeller from the current direction of flight so that a convenient and safe flight can be achieved.

As a result, the flying body 100 according to the present invention rotates only the cockpit 110 without rotation of the body 102, so that it is possible to immediately and freely change the direction of the flight in the forward and diagonal directions, Only the cockpit 110 is rotated by 360 degrees, so that the field of view in the front, rear, and right directions can be easily secured.

In addition, it is also desirable that a switch that stores various rotation angles and flight modes is configured on the control panel so that low-speed flight can be maintained in various patterns, thereby enabling efficient forward gazing and observation and securing a view.

100: Flight 102: Gas
104: Pilot 106: Pilot
108: control panel 110: cockpit

Claims (7)

A gas (102) configured to generate lift and configured to be flown with at least one propeller equipped with a steering device; And
A cockpit 110 installed to be rotatable by 360 degrees independently from the base 102;
/ RTI >
When the pilot 104 mounted on the cockpit 110 adjusts the cockpit 106 installed on the cockpit 110, the base 102 rotates only the cockpit 110 in the flight direction, Including flight mode,
When the rotational flight mode is selected, the steering device mounted on the propeller installed on the base is operated to adjust the direction of flight,
In the rotational flight mode,
When the pilot 104 is adjusted by the pilot 104, the propeller is controlled so that the base 102 is switched to the stop state. Thereafter, the cockpit 110 installed in the base 102 is rotated by 360 degrees, ) Is rotated in the adjusted angle and direction, and the rotation and direction of the propeller, which is switched according to the direction of flight,
Wherein the cockpit (110) is installed on either the upper or lower portion of the base body (102). delete The method according to claim 1,
Wherein at least one main propeller and at least one auxiliary propeller are reset in accordance with the direction of flight of the airframe 102 when the propeller is composed of at least two or more propellers. The method of claim 3,
The main propeller and the auxiliary propeller are controlled immediately before the direction change of the base 102 and the main body 102 is stopped to fly and the main propeller and the auxiliary propeller according to the direction to be switched are reset And controlling the main propeller and the auxiliary propeller to be re-set, thereby flying the cockpit. delete The method according to claim 1,
By selecting the rotation direction switch and the rotation angle switch, which are provided on the control panel 108 installed in the cockpit 110 and stored in different rotation directions and different rotation angles, respectively, the pilot direction So that the cockpit rotates immediately. delete
KR1020150120086A 2015-08-09 2015-08-26 Aircraft with Rotational Cockpit KR101755109B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020150112061 2015-08-09
KR20150112061 2015-08-09

Publications (2)

Publication Number Publication Date
KR20170018292A KR20170018292A (en) 2017-02-17
KR101755109B1 true KR101755109B1 (en) 2017-07-07

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KR1020150120086A KR101755109B1 (en) 2015-08-09 2015-08-26 Aircraft with Rotational Cockpit

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114889378A (en) * 2022-06-01 2022-08-12 佛山市神风航空科技有限公司 Air-ground dual-purpose aerocar

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5454531A (en) * 1993-04-19 1995-10-03 Melkuti; Attila Ducted propeller aircraft (V/STOL)

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5454531A (en) * 1993-04-19 1995-10-03 Melkuti; Attila Ducted propeller aircraft (V/STOL)

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