Patent Description:
Referring to <FIG>, a control input device of a helicopter, which is a general vertical take-off and landing aircraft, is described. Helicopters include a control input device including a cyclic control stick <NUM> for controlling a pitch and roll attitude, a tall rotor control pedal <NUM> for controlling a direction, and a collective control stick <NUM> for inputting an engine thrust and a collective pitch angle of the rotor blades. Meanwhile, a fixed-wing aircraft is configured such that when both sides of the tall rotor control pedal <NUM> are stepped on at the same time, a brake function operates.

<CIT> discloses a method and apparatus for a control system for an aircraft. The control system comprises a grip, a set of feedback components connected to the grip, and a set of sensors. The set of feedback components transmit a restoring force opposite to a movement of the grip. The set of sensors are capable of detecting pitch input, roll input, and yaw input in response to the movement of the grip. <CIT> discloses an air vehicle including a flight computer, a fuselage, and two rotors mounted symmetrically with respect to the fuselage. Each of the two rotors includes a servo mechanism to tilt a respective rotor of the two rotors about two axes of the respective rotor. The flight computer is configured to send control parameters to each of the two rotors, the control parameters including a rotational speed, a first tilt angle about a first axis of the two axes of the respective rotor, and a second tilt angle about a second axis of the two axes of the respective rotor. A method for operating the air vehicle is also provided. <CIT> discloses a vehicular control system which can include a control device including one or more control inputs, and a control switch operatively connected to the control device for receiving control input signals from the control device, the control switch configured to switch between a vehicle control mode such that the control input signals control one or more vehicle motion control components and at least one mission mode such that the control input signals control one or more other devices.

Because flight control using cyclic control sticks, pedals, and collective control sticks of these helicopters is mostly performed manually, pilots need a lot of training time and high-level control skills to learn helicopter flight control.

In the related art case, an automatic flight control system (autopilot) of a manned aircraft or a ground control system of an unmanned aircraft is provided with an automatic system that automatically maintains constant altitude, speed, heading, etc. to reduce the pilot's control burden, and is configured to input an input value through a knob input device. In general, the knob input device of the manned aircraft may be located on a control instrument panel separate from the control stick input device and is provided to input a target altitude, speed and heading commands by turning a knob dial or applying a beep trim button of the control stick after pressing altitude (ALT), speed (IAS) and heading (HDG) buttons. In addition, in the case of an unmanned aerial vehicle, altitude, speed, and heading commands may be input using a knob window and a dial input device of the ground control system (GCS).

In the case of an electric-powered vertical take-off and landing (eVTOL) personal aircraft, flight control may be performed by an ordinary person with a level of flight experience and control skills that are much less than those of a professional pilot. To this end, most of the flight control should be performed automatically, and manual control of an occupant is required only in emergencies, such as failure situations, but an autopilot allowing for a safe landing without a very high level of control skills should be provided.

Accordingly, there is a need for a control input device allowing a pilot who is an ordinary person to easily operate the flight control.

An exemplary embodiment of the present invention is directed to providing a device capable of performing flight control using a single control device to simplify and facilitate a flight operation, compared with an existing control device, and easily inputting a control command through a control device, so as to be used in an electric vertical take-off and landing personal aircraft having an automatic flight control system.

This task is solved by the features of independent claims. Features of the dependent claims define embodiments.

According to the aircraft control input device and the command input method using the same of the present invention according to the configuration as described above, unlike the related art in which flight control is performed using a plurality of control sticks in an existing aircraft, flight of an aircraft may be manipulated using one control device, so that even an unskilled pilot may more easily perform flight control, thereby improving work efficiency. In addition, by configuring a command value for automatic flight control to be input using the control device, the number of parts installed in the aircraft may be reduced, and the convenience of manipulation may be improved, thereby achieving an effect of improving the pilot convenience and stability of a flight operation through simple and accurate flight control. The above-described altitude command input method, speed command input method, heading command input method, and roll command input method can be performed with one and the same control input device.

Prior to the description, it should be understood that the terms used in the specification and the appended claims should not be construed as limited to general and dictionary meanings, but interpreted based on the meanings and concepts corresponding to technical aspects of the present invention based on the principle that the inventor is allowed to define terms.

Therefore, the description proposed herein is just a preferable example for the purpose of illustration only, and is not intended to limit the scope of protection, which is intended to be limited only by the appended claims.

Hereinafter, the present invention will be described in more detail with reference to the accompanying drawings.

Referring to <FIG>, an aircraft control input device of the related art includes a cyclic control stick <NUM> for pitch and roll attitude control, a tall rotor control pedal <NUM> for direction control, and a collective control stick <NUM> for inputting a collective pitch angle of engine thrust and rotor blades, and the aircraft is configured to perform a corresponding mission by inputting a flight control command by using the plurality of control sticks in combination.

The present invention relates to a control input device that commands an operation for flight control of an aircraft. Unlike the related art, the present invention is configured to input control commands necessary for flight control, such as a pitch attitude, roll attitude, direction control, engine thrust, blade pitch angle, wireless communication and a brake of an aircraft through one control stick. Therefore, even a pilot who is not proficient in controlling an aircraft may perform flight control more easily, and thus, because an ordinary person with a level of flight experience, control skills, and desired pay that is much more modest than those of a professional pilot may perform control, work efficiency may be improved and an effect of contributing to the popularization of vertical take-off and landing personal aircraft as a means of transportation in the future may be achieved. In particular, the control input device of the present invention may be applied to an eVTOL aircraft, which is an electric powered vertical take-off and landing aircraft, and is intended to provide a device capable of performing flight control through the automatic control system and one control input device in an aircraft equipped with an automatic control system.

The present invention relates to a control input device for inputting a control command for an operation of at least one of the pitch attitude, roll attitude, direction control, engine thrust, blade pitch angle, wireless communication, and brake of the aircraft for the control of a distributed propulsion electric-powered vertical take-off and landing aircraft having an automatic flight control device. Therefore, the control input device <NUM> of the present invention may include a body portion <NUM> formed in the shape of a bar that may be gripped by hand to input the control command by an operation of pushing or pulling in every direction and a twisting operation in an axial direction and at least one position <NUM>, <NUM>, <NUM>, and <NUM> formed in the body portion to input the control command by a manipulation operation. In addition, the aircraft of the present invention may include the control input device <NUM> for inputting an input value for an operation of the aircraft, a flight information monitor (FIM) <NUM> inputting commands by drawing or touching for a plurality of modules according to the flight information and automatic flight module of the aircraft, and a flight control computer controlling the aircraft according to input values.

The body portion <NUM> is formed so that a pilot may grip it with any one of a left hand or a right hand to use it, and is formed in a bar shape having a length in one direction so that the pilot may use the bar by holding it with his hand. Referring to <FIG>, the body portion <NUM> is connected to the aircraft on the other side and extends in one direction, so that one end of the body portion <NUM> may be gripped by the user. The body portion <NUM> may be formed to be inclined at a certain angle on one side when extending in a length direction so that the pilot may grip the body portion <NUM> with his hand and easily use another device provided in the body portion <NUM> by using his fingers. In an exemplary embodiment of the present invention, the body portion <NUM> may have a form having an angle inclined toward the front from a central portion to one end in the length direction while the other end is vertically extended.

Referring to <FIG>, the body portion <NUM> of the present invention may be movable in every direction and may be formed to allow a twisting operation in the axial direction of the body portion <NUM>, and according to a movement or twisting operation of the body portion <NUM> in each direction, a certain control command may be input to a flight control computer, and the aircraft may perform an operation according to the command. In an exemplary embodiment of the present invention, a control command may be input to the body portion <NUM> through a pushing or pulling operation in a front-rear direction (Y-axis), and the control command at this time may be set as a control command for the pitch attitude of the aircraft. In addition, a control command may be input to the body portion <NUM> through a pushing or pulling operation in a left-right direction (X-axis), and the control command at this time may be set as a control command for the roll attitude of the aircraft. In addition, a control command may be input to the body portion <NUM> through a clockwise or counterclockwise twisting operation (Z axis) in the axial direction, and the control command at this time may be set as a control command for the direction control of the aircraft. For example, when the pilot wants to fly the aircraft to the right, the pilot may grip the body portion <NUM> with his hand and then push the body portion <NUM> to the right to input a command for the roll attitude of the aircraft, or may perform flight control by inputting a command so that the aircraft heads in the right direction by rotating the body portion <NUM> clockwise during stationary flight or low-speed flight.

At least one position is formed on the body portion <NUM>, and a control command is input to the aircraft by a manipulation operation of the position. The position may be provided in plurality according to the user's needs, and each position may be set to input a different command value. The positions <NUM>, <NUM>, <NUM>, and <NUM> are preferably arranged according to the shape of the body portion <NUM>, and the positions <NUM>, <NUM> and <NUM> may be located in a portion where each finger is located when the pilot grips the body portion <NUM> with his/her hand, or the position <NUM> may be located in a position that may be controlled using a finger, so that the pilot may easily and conveniently operate the position. The position may be used without limitation as long as it is a device capable of inputting input values to the flight control computer by any operation, and it is preferable to select and provide an appropriate operation according to the user's needs and purposes.

Referring to <FIG>, in an exemplary embodiment of the present invention, in the control input device <NUM>, the pilot may grip the bar portion of the body portion <NUM> such that all of the fingers excluding the thumb wraps the bar portion and the thumb contacts the other fingers. At this time, the first position <NUM>, the second position <NUM>, and the third position <NUM> may be formed in a portion in which the pilot's thumb is located in a state where the pilot grips the body portion <NUM>, and the fourth position <NUM> may be formed at a position of one or more of the fingers other than the pilot's thumb. More specifically, the control input device <NUM> of the present invention may have four positions <NUM>, <NUM>, <NUM>, and <NUM>, and among the four positions, three positions including the first, second, and third positions <NUM>, <NUM>, and <NUM> may be located at one end side of the body portion <NUM>, and the remaining one position, which is the fourth position <NUM>, may be located in a length portion of the body portion <NUM>. The first, second, and third positions <NUM>, <NUM>, and <NUM> may be formed adjacent to each other at one end of the body portion <NUM>, and may be arranged vertically in parallel to each other, but in an exemplary embodiment of the present invention, the first, second, and third positions <NUM>, <NUM>, and <NUM> are arranged side by side on the left and right of each other. The fourth position <NUM> may be formed at a position where the index or middle finger of the pilot's four fingers with smooth force control is located, and in an exemplary embodiment of the present invention, the fourth position <NUM> may be formed in a front direction of the body portion <NUM>.

The respective positions <NUM>, <NUM>, <NUM>, and <NUM> may input different flight control commands according to operations. The flight control command at this time may include commands, such as engine thrust, wireless communication on/off, and brake.

More specifically, the first position <NUM> of the present invention may be formed in a form that may be operated in an up-down direction, and the first position <NUM> may be set to input a control command for the engine thrust of the aircraft when manipulated in the up-down direction. At this time, the first position <NUM> may be located on the leftmost side of one end of the body portion <NUM>. For example, when the pilot wants to increase thrust, the first position <NUM> may be manipulated upward using the pilot's thumb to input a higher value of thrust so that the aircraft may fly with a higher value of thrust.

The second position <NUM> may be formed in the form of a joystick capable of moving the bar up, down, left, and right, and the second position <NUM> may be set to input a control command set by the user by moving the bar of the second position <NUM>. At this time, the second position <NUM> may be located adjacent to the right side of the second position <NUM>. The second position <NUM> may be formed to input a flight control command as needed, but as an exemplary embodiment of the present invention, the second position <NUM> is set to be used to input a command value for setting in a flight mode to be described later.

In addition, the third position <NUM> of the present invention may be formed in the form of a button to be pressed, and may be set to input a control command to turn on or off wireless communication by pressing the third position <NUM>. For example, the third position <NUM> may be a button type in which a button is inserted when pressed once and protrudes to an existing height when the inserted button is pressed again. Accordingly, when the third position <NUM> protruding with the existing height is pressed once using the pilot's thumb, the wireless communication of the aircraft is commanded to be ON and an operation to be connected to perform wireless communication with the outside may be performed. Alternatively, it may be set to be ON only when the third position <NUM> is pressed, and OFF when not pressed.

If the aircraft of the present invention is a distributed electric-powered vertical take-off and landing (eVTOL) aircraft, it adopts a wing such as a fixed wing for a long flight, and should be able to slide and land in a fixed wing mode in an emergency, such as when a motor fails. At this time, a brake is required to stop after sliding on the ground. Therefore, the fourth position <NUM> of the present invention is formed on the front portion of the body portion <NUM>, and may be formed at a position where at least one finger of the pilot's index and middle fingers is located, and is formed in a button type to be pressed, so that the aircraft may be set to input a brake control command through an operation of pressing the fourth position <NUM>. At this time, the fourth position <NUM> may be formed to be perceived by distinguishing sensitivity of pressing the button type, and may be formed such that the degree of brake use of the aircraft is adjusted according to the pressure with which the pilot presses the fourth position <NUM>. For example, when the pilot needs an emergency braking operation, the fourth position <NUM> may be pressed hard with a pressure higher than a certain level, and when an input value received by the flight control computer from the fourth position <NUM> is identified as a pressure equal to or higher than a certain level, the brake may be operated at a certain level or higher to perform the emergency braking operation of the aircraft. Alternatively, it may be programmed in a computer so that a force of the break command is accumulated according to ON or OFF of the switch at the fourth position <NUM>.

In the present invention, when a plurality of automatic flight modes included in an automatic flight control device of the aircraft are executed using the control input device <NUM> having the above characteristics, a command value necessary for each mode may be input through the control input device <NUM>. Hereinafter, a method of inputting different command values by manipulating the position of the control input device <NUM> according to each mode will be described in more detail.

The aircraft of the present invention may include a monitor <NUM> displaying flight information on a screen so that a pilot may check various information inside the aircraft. In this case, the monitor <NUM> may check flight information, but may be a touch screen capable of switching a controller to perform a selected mission or mode by touching the screen. Referring to <FIG>, the monitor <NUM> may have a plurality of modes formed as buttons on the monitor <NUM> for automatic flight control, and by touching a button of any mode according to the pilot's need, the flight control computer of the aircraft may be formed to be switched to perform the operation of the corresponding button.

In an exemplary embodiment of the present invention, the aircraft may include an altitude speed maintenance mode <NUM> that maintains a constant altitude speed desired by the pilot. Referring to <FIG>, the altitude speed maintenance mode <NUM> may be displayed on the monitor <NUM> and may be activated by a pilot's touch. When the pilot touches the altitude speed maintenance mode <NUM>, a screen for inputting an altitude speed maintenance command including at least one or more of altitude and speed may be executed. At this time, in order to input the altitude speed maintenance command, the present invention may use a position, and may be configured to input an altitude command value by manipulating the first position <NUM>. The first position <NUM> of the present invention may be formed to input a command value in a first range by manipulating up and down, and in the altitude input, a high altitude may be input as a command value by manipulating the first position <NUM> upward. That is, when the pilot presses the altitude speed maintenance mode button <NUM> of the monitor <NUM> to activate the altitude speed maintenance mode, an altitude command value may be input by manipulating the first position <NUM> up or down, and according to the input command value, the aircraft may perform the altitude speed maintenance mode at a corresponding altitude. In addition, in order to input the altitude speed maintenance command, the present invention may use a position, and may be configured to input a speed command value by manipulating the second position <NUM>. The second position <NUM> of the present invention may be in the form of a joystick capable of moving up and down, left and right, and may be configured to input a command value by moving the bar up and down. For example, in a speed input, a high speed may be input as a command value by moving the second position <NUM> up. That is, when the altitude speed maintenance mode is activated by the pilot pressing the altitude speed maintenance mode button <NUM> of the monitor <NUM>, the speed command value may be input by moving the second position <NUM> up or down, and according to the input command value, the aircraft may perform the altitude speed maintenance mode at the corresponding speed. At this time, for the altitude and speed, a reference value that appears first on the monitor <NUM> may be an altitude and speed of the currently flying aircraft, and other values may be set according to the user's selection. The altitude speed maintenance mode may be released by the pilot by pressing the altitude speed maintenance mode button <NUM> of the monitor <NUM> once again, and according to the user's setting, the altitude speed maintenance mode may be set to be performed only for a certain period of time and released after a certain period of time.

In addition, in the altitude speed maintenance mode <NUM>, the altitude command value may be input by simultaneously manipulating the body portion <NUM> together with the first position <NUM>, and the speed command value may be input by simultaneously manipulating the body portion <NUM> together with the second position <NUM>. More specifically, as an altitude input method, an altitude command value in a second range may be input by pushing or pulling the body portion <NUM> forward and backward while operating the first position <NUM> in the up-down direction. At this time, the command value in the second range that may be input by simultaneously manipulating the first position <NUM> and the body portion <NUM> may be greater than the command value in the first range that may be input by manipulating only the first position <NUM>.

For example, when only the first position <NUM> is pushed up, a single click may increase an altitude command of <NUM>, and when the first position <NUM> and the body portion <NUM> are simultaneously pushed or pulled in the front-rear direction, an altitude command by <NUM> may be increased. In addition, as a speed input method, a speed command value in the second range may be input by pushing or pulling the body portion <NUM> in the front-rear direction, while operating the second position <NUM> in the up-down direction. At this time, the command value in the second range that may be input by simultaneously manipulating the second position <NUM> and the body portion <NUM> may be greater than the command value in the first range that may be input by manipulating only the second position <NUM>. For example, when only the second position <NUM> is pushed upward, a speed command of <NUM>/h may be increased with a single click, and a speed command of <NUM>/h may be increased by simultaneously pushing the second position <NUM> and the body portion <NUM> in the front-rear direction.

In an exemplary embodiment of the invention, the aircraft may include a heading maintenance mode <NUM> that constantly maintains a heading desired by the pilot. Referring to <FIG>, the heading maintenance mode <NUM> is displayed on the monitor <NUM> and may be activated by a pilot's touch. When the pilot touches the heading maintenance mode <NUM>, a screen for inputting a heading maintenance command may be executed. At this time, in order to input the heading maintenance command, the present invention may use a position, and a heading command value in a first range may be input by manipulating the second position <NUM> in the left-right direction. The second position <NUM> of the present invention may be in the form of a joystick in which the bar may move up and down, and left and right, and a command value may be input by moving the bar in the left-right direction. For example, in inputting a heading command value, a high heading value may be input as a command value by moving the second position <NUM> to the right. That is, when the pilot activates the heading maintenance mode by pressing the heading maintenance mode button <NUM> of the monitor <NUM>, a heading command value may be input by moving the second position <NUM> to the left or right, and according to the received command value, the aircraft may perform the heading maintenance mode. In this case, a reference value that appears first on the monitor <NUM> for the heading value may be a heading value of the currently flying aircraft, and other values may be set according to the user's selection. The heading maintenance mode may be released by the pilot by pressing the header maintenance mode button <NUM> of the monitor <NUM> once again, and according to the user's setting, the heading maintenance mode may be set to be performed only for a certain period of time and may be released after the lapse of a certain period of time.

In addition, in the heading maintenance mode <NUM>, a heading command value may be input by simultaneously manipulating the body portion <NUM> together with the second position <NUM>. More specifically, as a heading input method, a heading command value in the second range may be input by pushing or pulling the body portion <NUM> in the left-right direction, while operating the second position <NUM> in the left-right direction. Alternatively, as a heading input method, a heading command value in the second range may be input by twisting and rotating the body portion <NUM> in the left-right direction, while manipulating the second position <NUM> in the left-right direction. At this time, the command value in the second range that may be input by simultaneously manipulating the second position <NUM> and the body portion <NUM> may be greater than the command value in the first range that may be input by manipulating only the second position <NUM>.

For example, when only the second position <NUM> is pushed to the right, a single click may increase a heading command or roll by <NUM> degree, and a heading command or roll command may be increased by <NUM> degrees when the second position <NUM> and the body portion <NUM> are simultaneously pulled to the right. Alternatively, when the second position <NUM> and the body portion <NUM> are twisted to the right at the same time, the heading command or roll command may be increased by <NUM> degrees.

In an exemplary embodiment of the present invention, the aircraft may include a roll maintenance mode <NUM> whereby the pilot constantly maintains a desired roll attitude. Referring to <FIG>, the roll maintenance mode <NUM> is displayed on the monitor <NUM> and may be activated by a pilot's touch. When the pilot touches the roll maintenance mode <NUM>, a screen for inputting a roll maintenance command may be executed. At this time, in order to input the roll maintenance command, the present invention may use a position, and by manipulating the second position <NUM>, a roll attitude command value in a first range may be input. The second position <NUM> of the present invention may be in the form of a joystick in which the bar may move up and down, left and right, and a command value may be input by moving the bar in the left-right direction. For example, in the roll attitude command value input, a high roll attitude value may be input as a command value by moving the second position <NUM> to the right. That is, when the pilot activates the roll maintenance mode by pressing the roll maintenance mode button <NUM> of the monitor <NUM>, the roll attitude command value may be input by moving the second position <NUM> to the left or right, and according to the input command value, the aircraft may perform the roll maintenance mode. At this time, a reference value first displayed on the monitor <NUM> for the roll attitude command value may be a roll attitude value of the currently flying aircraft, and other values may be set according to the user's selection. The roll maintenance mode may be released by the pilot by pressing the roll maintenance mode button <NUM> of the monitor <NUM> once again, and the roll maintenance mode may be set to be performed only for a certain period of time and may be released after the certain period of time according to the user's setting. In addition, when the heading maintenance mode button <NUM> is pressed while the roll maintenance mode is applied, the roll maintenance mode may be switched to the heading maintenance mode, and conversely, when the roll maintenance mode button <NUM> is pressed in a state in which the heading maintenance mode is applied, the heading maintenance mode may be switched to the roll maintenance mode.

In addition, in the roll maintenance mode <NUM>, a roll command value may be input by simultaneously manipulating the body portion <NUM> together with the second position <NUM>. More specifically, as a roll input method, a roll command value in the second range may be input by pushing or pulling the body portion <NUM> in the left-right direction, while operating the second position <NUM> in the left-right direction. At this time, the command value in the second range that may be input by simultaneously manipulating the second position <NUM> and the body portion <NUM> may be greater than the command value in the first range that may be input by manipulating only the second position <NUM>.

Hereinabove, although the present invention has been described by specific matters, such as detailed components, exemplary embodiments, and the accompanying drawings, they have been provided only for assisting in the entire understanding of the present invention. Therefore, the present invention is not limited to the exemplary embodiments. Various modifications and changes, which remain within the scope of the appended claims, may be made by those skilled in the art to which the present invention pertains from this description.

Claim 1:
A command input method for inputting an altitude speed maintenance command using a control input device (<NUM>) comprising: a body portion (<NUM>) formed in a bar shape grippable by hand and configured for inputting the control command through an operation of pushing or pulling in every direction and a twisting operation in an axial direction; and at least one position (<NUM>, <NUM>, <NUM>, <NUM>) formed in the body portion (<NUM>) to input the control command by a manipulation operation, wherein
an altitude speed maintenance mode of the aircraft is performed by selecting an altitude speed maintaining module from a monitor (<NUM>) showing flight information of the aircraft and inputting at least any one of an altitude command value and a speed command value by operating the at least one position (<NUM>, <NUM>, <NUM>, <NUM>) of the control input device (<NUM>),
the monitor includes a plurality of modules for automatic flight control to be a touch screen switched into a selected module when the touch screen is touched for the selected module,
the at least one position includes a first position (<NUM>) formed in a portion in which the thumb is located in a state in which the body portion (<NUM>) of the control input device (<NUM>) is gripped, and operating while moving in an up-down direction,
an altitude command value in a first range is input by manipulating the first position (<NUM>) in the altitude speed maintenance mode,
an altitude command value in a second range is input by pushing or pulling the body portion (<NUM>) in a front-rear direction, while manipulating the first position (<NUM>) in the up-down direction, and
the second range is a value greater than the first range.