Morphing head aircraft and method of controlling morphing head part thereof

Abstract

The present invention relates to a variable head aircraft and a method for controlling the variable head portion thereof, wherein the variable head aircraft may include: a variable head portion; a fuselage portion provided at the rear of the variable head portion and separated from the variable head portion; a variable actuation device connecting the variable head portion and the fuselage portion, provided such that vertical rotation with respect to the fuselage portion is possible with respect to the variable actuation device with respect to the left-right direction of the variable head portion as an axis; and a control unit for controlling the variable actuation device for vertical rotation of the variable head portion.

Description

Technology Field

[0001] The present invention relates to a variable head aircraft and a method for controlling the variable head section thereof. For example, the present invention can be applied to passenger aircraft, military aircraft, UAM, space launch vehicles, etc., and can be utilized as a technology for securing visibility in the cockpit, securing visibility in the cabin, or supplementing blind spots of radar / cameras. Background Technology

[0002] Conventional aircraft have a structure in which the nose is fixed to the fuselage. The cockpit is typically equipped in the nose, ensuring the pilot's visibility during flight. However, because the nose is fixed to the fuselage, the cockpit's field of view varies depending on the aircraft's attitude during takeoff, landing, and flight.

[0003] The prior art forming the background of the present invention is disclosed in Korean Patent Publication No. 10-2329760 ("Tail-sitter aircraft with a rotating cockpit"). However, the aforementioned prior art has a structure in which the cockpit rotates while located inside the aircraft fuselage, which has the aspect that the pilot's view may be obstructed by other structures (such as the head or airframe) in front of the cockpit.

[0004] Based on this technological background, research has been required to improve visibility of aircraft cockpits, aircraft, or projectile cameras and radars. The problem to be solved

[0005] The present invention aims to solve the problems of the aforementioned conventional technology by providing a variable head aircraft and a method for controlling the variable head unit thereof, which can increase maneuverability and prevent safety accidents by more appropriately securing a field of view of the cockpit, camera, radar, etc., in a desired direction.

[0006] In addition, the present invention aims to provide an aircraft and a method for controlling its variable head section, which can increase stability by shifting the center of gravity of the aircraft forward or increase ascent performance and efficiency by shifting it backward depending on the conditions during operation.

[0007] However, the technical problems that the embodiments of the present invention aim to solve are not limited to the technical problems described above, and other technical problems may exist. means of solving the problem

[0008] As a technical means for achieving the above-mentioned technical problem, a variable head aircraft according to one embodiment of the present invention may include: a variable head portion; a fuselage portion provided at the rear of the variable head portion and separated from the variable head portion; a variable actuation device connecting the variable head portion and the fuselage portion, provided such that vertical rotation with respect to the fuselage portion is possible with respect to the variable head portion with respect to the left-right direction of the variable head portion as an axis; and a control unit for controlling the variable actuation device for vertical rotation of the variable head portion.

[0009] In one embodiment of the present invention, the variable head aircraft may be a passenger aircraft, a military aircraft, an Urban Air Mobility (UAM), or a space launch vehicle.

[0010] In one embodiment of the present invention, the vertical rotation range of the variable head part may be set to ensure a field of view that reduces the lower blind spot occurring during head-up flight of the variable head aircraft compared to the normal state when the variable head part is not rotated vertically.

[0011] In one embodiment of the present invention, the lower blind spot may include one or more of the lower blind spot of the pilot in the cockpit provided in the variable head unit and the lower blind spot of the camera or radar provided in the variable head unit.

[0012] In one embodiment of the present invention, the variable head aircraft further includes a variable skin structure provided to surround the variable space so as to prevent external exposure of the variable operating device installed in the variable space between the variable head part and the fuselage part when the variable head part rotates relative to the fuselage part, and the variable skin structure may be provided with a stretchable material that is capable of extending and contracting within the vertical rotation range and does not produce wrinkles.

[0013] In one embodiment of the present invention, the variable head aircraft may further include an internal connecting passage that extends across the variable space within the variable operating device and is configured to movably connect the variable head portion and the fuselage portion.

[0014] In one embodiment of the present invention, the variable operating device may be configured to shift the center of gravity of the variable head part forward compared to normal during vertical rotation of the variable head part.

[0015] In one embodiment of the present invention, the control unit may control the variable actuation device so that the center of gravity of the variable head unit is shifted by taking into account the forward limit and the rear limit of the center of gravity of the variable head aircraft.

[0016] In one embodiment of the present invention, the variable operating device comprises: an upper linear extension actuator that directly or indirectly links the variable head part and the body part in the upper space of the variable space between the variable head part and the body part; and a lower linear extension actuator or lower hinge mechanism that directly or indirectly links the variable head part and the body part in the lower space of the variable space, and as the upper linear extension actuator is extended, the center of gravity of the variable head part may be shifted forward.

[0017] In one embodiment of the present invention, the variable operating device is provided to enable left and right rotation with respect to the body part with respect to the vertical direction of the variable head part as an axis, wherein the variable operating device may include: an intermediate connecting member disposed to extend in the front-rear direction in the central space of the variable space between the variable head part and the body part; an vertical variable operating part installed on the variable head part, the intermediate connecting member, and the body part for vertical rotation of the variable head part; and a left and right variable operating part installed on the variable head part, the intermediate connecting member, and the body part for left and right rotation of the variable head part.

[0018] In one embodiment of the present invention, the upper and lower variable actuator comprises: an upper linear extension actuator linking the upper rear end of the variable head portion and the upper side of the intermediate connecting member in the upper space of the variable space; a lower hinge mechanism hinge connecting the lower rear end of the variable head portion and the lower side of the intermediate connecting member in the lower space of the variable space; a lower linear extension actuator linking the lower side of the intermediate connecting member and the lower front end of the body portion in the lower space; and an upper hinge mechanism hinge connecting the upper side of the intermediate connecting member and the upper front end of the body portion in the upper space, and the left and right variable actuator comprises: a left linear extension actuator linking the left rear end of the variable head portion and the left side of the intermediate connecting member in the left space of the variable space; a right hinge mechanism hinge connecting the right rear end of the variable head portion and the right side of the intermediate connecting member in the right space of the variable space; and a right linear extension actuator linking the right side of the intermediate connecting member and the right front end of the body portion in the right space. and may include a left hinge mechanism that hinges the left side of the intermediate connecting member and the left front end of the body part in the left space.

[0019] In one embodiment of the present invention, the intermediate connecting member may be provided with a movement freedom providing connection part that provides a degree of freedom in which a component part connected to the intermediate connecting member from the left and right variable operating part can move along a curved path in conjunction with the operation of the up and down variable operating part when the up and down variable operating part is operated, and a degree of freedom in which a component part connected to the intermediate connecting member from the up and down variable operating part can move along a curved path in conjunction with the operation of the left and right variable operating part when the left and right variable operating part is operated.

[0020] A method for controlling a variable head portion of a variable head aircraft according to one embodiment of the present invention is a method for controlling the variable head portion of a variable head aircraft according to one embodiment of the present invention, wherein the control unit controls the variable operating device to rotate the variable head portion in an up-and-down direction within the up-and-down rotation range of the variable head portion.

[0021] In one embodiment of the present invention, the vertical rotation range of the variable head part may be set to ensure a field of view that reduces the lower blind spot occurring during head-up flight of the variable head aircraft compared to the normal state when the variable head part is not rotated vertically.

[0022] In one embodiment of the present invention, the control unit may control the variable actuation device so that the center of gravity of the variable head unit is shifted by taking into account the forward limit and the rear limit of the center of gravity of the variable head aircraft.

[0023] In addition, the present invention may provide a computer-readable recording medium having a program for executing a variable head part control method of a variable head aircraft according to the above-mentioned embodiment on a computer.

[0024] The means for solving the problem described above are merely exemplary and should not be interpreted as intended to limit the present invention. In addition to the exemplary embodiments described above, additional embodiments may exist in the drawings and the detailed description of the invention. Effects of the invention

[0025] According to at least one of the means for solving the problem of the present invention described above, by having a structure in which the head portion of an aircraft rotates relative to the fuselage portion, the head can be rotated in a desired direction during takeoff, landing, and flight of the aircraft, and a field of view of the cockpit, camera, radar, etc. can be secured, thereby increasing maneuverability and preventing safety accidents.

[0026] As a more specific example, according to at least one of the means for solving the problem of the present invention described above, an aircraft having a variable head can adjust the direction of the head, thereby ensuring a clear view of the cockpit even if there is a difference in the attitude and direction of travel of the aircraft, thus reducing blind spots at the landing site during landing and preventing safety accidents through the secured view. In addition, since the head moves independently even if the attitude of the aircraft's fuselage changes during flight, the position and direction of the head can be maintained at a constant level, thereby enhancing the pilot's controllability and reducing operational fatigue for the pilot and passengers.

[0027] In addition, according to at least one of the means for solving the problem of the present invention described above, by rotating and moving the variable head part, it is possible to perform an operation that increases stability by shifting the center of gravity of the aircraft forward or increases ascent performance and efficiency by shifting it backward, depending on the situation during operation.

[0028] In addition, according to at least one of the means for solving the problem of the present invention described above, the head section is connected to the fuselage section through an internal connecting passageway even during takeoff, landing, and flight of the aircraft, thereby enabling the movement of crew, passengers, cargo, etc.

[0029] However, the effects obtainable from this invention are not limited to those described above, and other effects may exist. Brief explanation of the drawing

[0030] FIG. 1 is a conceptual diagram and a partial enlarged view of the normal (neutral) state of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention, viewed from the left. FIG. 2 is a conceptual diagram and a partial enlarged view taken from the left, showing the variable head portion of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention rotated downward. FIG. 3 is a conceptual diagram and a partial enlarged view taken from the left, showing the variable head portion of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention rotated upward. FIG. 4 is a conceptual diagram illustrating the field of view secured by the rotation of the variable head portion during horizontal flight of a variable head aircraft (an example of an aircraft form) according to one embodiment of the present invention. FIG. 5 is a conceptual diagram illustrating the field of view secured by the rotation of the variable head portion during head-up flight of a variable head aircraft (an example of an aircraft form) according to one embodiment of the present invention. Figure 6 is a conceptual diagram illustrating the forward and rear limits of the center of gravity of a flying vehicle (aircraft). Figure 7 is a conceptual diagram illustrating the change in stability according to the position of the center of gravity of a flying vehicle (aircraft). FIG. 8 is a conceptual diagram illustrating the movement of the center of gravity of a flying vehicle (aircraft) through the angle change and movement of the variable head portion of a variable head flying vehicle (example of an aircraft shape) according to one embodiment of the present invention. FIG. 9 is a conceptual diagram viewed from above of a variable head portion of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention, in a state where it is rotated to the left, a normal (neutral) state, and a state where it is rotated to the right. FIG. 10 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to one embodiment of the present invention, based on a normal (neutral) state in which the variable head part is not rotated. FIG. 11 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention and the movement of the head center of gravity based on the state in which the variable head part is rotated downward. FIG. 12 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention and the movement of the head center of gravity based on the state in which the variable head part is rotated upward. FIG. 13 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention and the movement of the head center of gravity based on a state in which the variable head part is not rotated but moved forward. FIG. 14 is a conceptual diagram of a part of a variable head aircraft viewed from above to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to one embodiment of the present invention, based on a normal (neutral) state in which the variable head part is not rotated. FIG. 15 is a conceptual diagram of a part of a variable head aircraft viewed from above to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention and the movement of the head center of gravity based on the state in which the variable head part is rotated to the right. FIG. 16 is a conceptual diagram of a part of a variable head aircraft viewed from above to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention and the movement of the head center of gravity based on the state in which the variable head part is rotated to the left. FIG. 17 is a conceptual diagram for explaining an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to one embodiment of the present invention and a head center of gravity shift based on the state in which the variable head part is rotated downward and simultaneously rotated to the left. FIG. 18 is a conceptual diagram illustrating a variable skin structure applied to one embodiment of a variable actuation device of a variable head aircraft (an example in the form of an aircraft) according to one embodiment of the present invention. Specific details for implementing the invention

[0031] Embodiments of the present invention are described below with reference to the attached drawings to enable those skilled in the art to easily implement the invention. However, the present invention may be embodied in various different forms and is not limited to the embodiments described herein. Furthermore, in order to clearly explain the present invention in the drawings, parts unrelated to the explanation have been omitted, and similar parts throughout the specification are denoted by similar reference numerals.

[0032] Throughout the entire specification, when a part is described as being "connected" to another part, this includes not only cases where they are "directly connected," but also cases where they are "indirectly connected" or "electrically connected" with other elements interposed between them.

[0033] Throughout the entire specification, when a component is described as being located "on," "on top," "on top," "under," "on bottom," or "on bottom" of another component, this includes not only cases where the component is in contact with the other component but also cases where another component exists between the two components.

[0034] Throughout this specification, when a part is described as "comprising" a certain component, this means that, unless specifically stated otherwise, it does not exclude other components but may include additional components.

[0035] Throughout the entire specification, the up, down, left, and right directions are set based on the flight direction being viewed forward during horizontal flight of a variable head aircraft according to one embodiment of the present invention. For example, depending on the flight direction of the variable head aircraft, the upward direction refers to the direction upward relative to the aircraft, and is not necessarily limited to referring only to a vertical upward direction.

[0036] Hereinafter, a variable head aircraft (hereinafter referred to as "the variable head aircraft") according to one embodiment of the present invention will be described. For example, the variable head aircraft may be a passenger aircraft, a military aircraft, an Urban Air Mobility (UAM) vehicle, or a space launch vehicle, but is not limited thereto. That is, the variable head aircraft may be understood to refer to a broad concept applicable to all objects moving in the air.

[0037] FIG. 1 is a conceptual diagram and a partial enlarged view of the normal (neutral) state of a variable head aircraft (example of an aircraft shape) according to one embodiment of the present invention, viewed from the left. FIG. 2 is a conceptual diagram and a partial enlarged view of the state in which the variable head portion of the variable head aircraft (example of an aircraft shape) according to one embodiment of the present invention is rotated downward, viewed from the left, and FIG. 3 is a conceptual diagram and a partial enlarged view of the state in which the variable head portion of the variable head aircraft (example of an aircraft shape) according to one embodiment of the present invention is rotated upward, viewed from the left. For reference, FIG. 2(b) shows the state in which the head is rotated downward when the nose of the variable head aircraft according to one embodiment of the present invention is raised.

[0038] Referring to FIGS. 1 to 3, the variable head aircraft (100) includes a variable head section (1), a body section (2), and a variable operating device (3). Additionally, the variable head aircraft (100) may include a control section (not shown in the drawings) that controls the variable operating device (3) for vertical rotation of the variable head section (1).

[0039] The variable head section (1) is a configuration that refers to the part corresponding to the head (foremost end) of an aircraft or similar flying vehicle. For example, when the variable head flying vehicle (100) is applied to an aircraft, a cockpit where a pilot sits may be provided in the variable head section (1). As another example, a camera or radar for securing a forward view may be installed in the variable head section (1).

[0040] The fuselage (2) is configured to be provided separately from the variable head (1) at the rear of the variable head (1). Referring to FIGS. 1 to 3, the fuselage (2) may refer to the remaining part of the aircraft excluding the variable head (1) located at the very front of the variable head aircraft. Since this distinction between the head and the fuselage is obvious to a person skilled in the art, a more detailed explanation will be omitted. Additionally, referring to the enlarged views of each part in FIGS. 1 to 3, the fuselage (2) may be provided separately from the variable head (1) in a form that is spaced rearward from the variable head (1).

[0041] The variable operating device (3) is configured to connect the variable head part (1) and the body part (2), which are separated and spaced apart front and back. Referring to FIGS. 1 to 3, the variable operating device (3) is provided to enable vertical rotation with respect to the body part (2) with the left and right directions of the variable head part (1) as the axis.

[0042] For example, referring to FIGS. 1 to 3, the variable actuation device (3) may include an upper linear extension actuator (311). Additionally, the variable actuation device (3) may include a lower linear extension actuator (313) or a lower hinge mechanism.

[0043] The upper linear extension actuator (311) is configured to directly or indirectly link the variable head part (1) and the body part (2) in the upper space of the variable space (30) between the variable head part (1) and the body part (2). The lower linear extension actuator (313) is configured to directly or indirectly link the variable head part (1) and the body part (2) in the lower space of the variable space (30). The upper linear extension actuator (311) and the lower linear extension actuator (313) are devices that linearly extend and retract along the longitudinal direction (drive to increase or decrease the length) (e.g., hydraulic, pneumatic, or mechanical actuators), and various linear drive devices known in the field of mechanical devices or to be developed in the future may be applied thereto.

[0044] For example, referring to FIG. 1 and FIG. 2 together, when the upper linear extension actuator (311) is extended in length compared to normal (see FIG. 1) and the lower linear extension actuator (313) is contracted in length compared to normal (see FIG. 2), the variable head part (1) can be rotated downward with the left and right directions as the axis of rotation.

[0045] Also, as another example, referring to FIG. 1 and FIG. 3 together, when the upper linear extension actuator (311) is contracted in length compared to normal (see FIG. 1) and the lower linear extension actuator (313) is extended in length compared to normal (see FIG. 3), the variable head part (1) can be rotated upward with the left and right directions as the axis of rotation.

[0046] Additionally, the lower hinge mechanism is configured to link the variable head part (1) and the body part (2) in the lower space of the variable space (30) without linear extension, using one or more hinges (hinges with the left and right directions as rotation axes), and is configured to be placed in place of the lower linear extension actuator (313). For example, referring to FIGS. 1 to 3, when the lower hinge mechanism is placed in place of the lower linear extension actuator (313), only the upper linear extension actuator (311) is linearly extended; thus, when the upper linear extension actuator (313) is linearly extended compared to the normal state (based on FIG. 1), the variable head part (1) can be driven to rotate downward as shown in FIG. 2. For reference, this lower hinge mechanism can be understood as having the same or similar configuration by referring to the configuration of the lower hinge mechanism referred to by reference numeral 312 in FIGS. 10 to 13, which will be described later.

[0047] As such, in one embodiment of the present invention, the variable actuation device (3) may be provided to include two linear extension actuators (an upper linear extension actuator and a lower linear extension actuator), or to include one linear extension actuator (an upper linear extension actuator) and one hinge mechanism (a lower hinge mechanism).

[0048] FIG. 4 is a conceptual diagram illustrating the field of view secured by the rotation of the variable head portion during horizontal flight of a variable head aircraft (example of an aircraft form) according to one embodiment of the present invention, and FIG. 5 is a conceptual diagram illustrating the field of view secured by the rotation of the variable head portion during head-up flight of a variable head aircraft (example of an aircraft form) according to one embodiment of the present invention.

[0049] For example, referring to FIG. 4(a), a conventional aircraft with a fixed head may have blind spots due to the field of view of the head (cockpit). Consequently, conventional aircraft may not be able to visually check the condition of the runway during landing. In contrast, referring to FIG. 4(b), in the case of an aircraft equipped with the variable head aircraft (100), by adjusting the angle of the head (variable head part) to rotate downward, additional visibility of the runway is secured and blind spots are reduced, allowing the safety of the runway to be more clearly visually confirmed.

[0050] As another example, referring to FIG. 5 (a), conventional aircraft maneuver with the fuselage head raised (nose up) during landing, and as a result, the cockpit's field of view is further away from the ground. In contrast, referring to FIG. 5 (b), in the case of an aircraft equipped with the variable head aircraft (100), the angle of the head can be adjusted downward to face the ground to be landed on, thereby securing a wider field of view of the runway from the cockpit compared to conventional aircraft.

[0051] Accordingly, the vertical rotation range of the variable head unit (1) can be set to ensure a clear view, thereby reducing the lower blind spot that occurs during head-up (nose-up) flight of the variable head aircraft (100) compared to normal conditions when the variable head unit (1) is not rotated vertically. Here, the lower blind spot may include one or more of the lower blind spot of the pilot inside the cockpit equipped with the variable head unit (1) and the lower blind spot of the camera or radar equipped with the variable head unit (1). That is, in this invention, the lower blind spot can be understood as a concept that encompasses both the blind spot that occurs during visual inspection by the pilot and the blind spot that occurs during inspection through a device such as a camera or radar.

[0052] Figure 6 is a conceptual diagram explaining the forward and rear limits of the center of gravity of an aircraft, and Figure 7 is a conceptual diagram explaining the change in stability according to the position of the center of gravity of an aircraft.

[0053] The center of gravity of an aircraft is a factor that affects the aircraft's stability and maneuverability. Referring to Figure 6, the aircraft has forward and rear limits where the center of gravity can be located, and cargo, passengers, etc., must be properly positioned so that the center of gravity exists within the range between the forward and rear limits.

[0054] Furthermore, the aircraft's center of gravity may fluctuate due to factors such as fuel consumption during flight. If these fluctuations cause the center of gravity to exceed the forward and aft limits, aircraft performance—including maneuverability, climb rate, speed, and fuel efficiency—will decrease, and structural damage may occur. Therefore, if the center of gravity exceeds these limits, it is advisable to redeploy passengers, cargo, and fuel, or to reduce weight.

[0055] Referring to Fig. 7, generally, when the center of gravity of an aircraft shifts forward, the stability of the aircraft increases, and when the center of gravity shifts backward, the climb performance and efficiency of the aircraft increase. Conventional aircraft have considered the stability and efficiency of the aircraft by adjusting the angle of attack of the horizontal tail after the position of the center of gravity is determined following the loading of passengers, cargo, fuel, etc. However, if the position of the aircraft's center of gravity shifts due to factors such as fuel consumption during flight, the stability and efficiency may change unintendedly.

[0056] FIG. 8 is a conceptual diagram illustrating the movement of the center of gravity of a flying vehicle (aircraft) through the angle change and movement of the variable head portion of a variable head flying vehicle (example of an aircraft shape) according to one embodiment of the present invention.

[0057] Referring to FIG. 8, when the variable head aircraft (100) is applied to an aircraft, the head portion can be variably rotated and moved, thereby allowing the head's center of gravity to be moved as well, and the change in the head's center of gravity caused by such rotation and movement of the head can cause the aircraft's center of gravity to move forward or backward. For example, as shown in FIG. 8, if the head is rotated downward from its normal position, the head's center of gravity shifts forward, and accordingly, the center of gravity of the entire aircraft can also be moved forward.

[0058] That is, the variable actuation device (3) may be configured to shift the center of gravity of the variable head part (1) forward compared to normal when the variable head part (1) rotates up and down. As a more specific example, referring to FIG. 2 (one embodiment) and FIG. 11 (another embodiment) to be described later, the center of gravity of the variable head part (1) may be shifted forward as the upper linear extension actuator (311) extends. Conversely, referring to FIG. 3 and FIG. 12 to be described later, the center of gravity of the variable head part (1) may be shifted forward as the lower linear extension actuator (313) extends. In addition, referring to FIG. 13 to be described later, the center of gravity of the variable head part (1) may be shifted forward even when both the upper linear extension actuator (311) and the lower linear extension actuator (313) extend. That is, when both the upper linear extension actuator (311) and the lower linear extension actuator (313) are extended, the variable head part (1) can be made to move its center of gravity forward while maintaining a neutral range.

[0059] Accordingly, the control unit of the variable head aircraft (100) can control the variable operating device (3) so that the center of gravity of the variable head unit (1) is shifted by taking into account the forward limit and rear limit of the center of gravity of the variable head aircraft (100).

[0060] In summary, as at least one of the upper linear extension actuator (311) and the lower linear extension actuator (313) is extended, the center of gravity of the variable head part (1) can be shifted forward. Regarding the shift of the center of gravity of such a flying vehicle (aircraft), further details will be described later based on an embodiment of FIGS. 10 to 17.

[0061] In this way, through the rotation and movement of the variable head part (1) of the variable head aircraft (100), it is possible to move the center of gravity of the aircraft forward to increase stability or move it backward to increase ascent performance and efficiency depending on the situation during operation.

[0062] In addition, since conventional aircraft could not arbitrarily change the position of the center of gravity during operation, the fuel tank was positioned near the center of gravity to reduce the impact of fuel consumption. However, when the variable head aircraft (100) is applied to the aircraft, the center of gravity can be moved according to the rotation and movement of the variable head part (1), so the fuel tank can be placed in a different area of ​​the aircraft (e.g., the rear of the fuselage).

[0063] Meanwhile, referring to FIGS. 1 to 3, the variable head aircraft (100) may include an internal connecting passage (5) that extends across a variable space (30) inside a variable operating device (3) to movably connect the variable head part (1) and the fuselage part (2). Referring to FIGS. 1 to 3, the internal connecting passage (5) may be provided in a form in which the rear end is fixed to the fuselage part (2), or may be provided in a tube form in which the passage space is extended in the front-rear direction to form a passage. In addition, the internal connecting passage (5) may be provided inside the intermediate connecting member (33) in an embodiment based on FIGS. 10 to 17 to be described later, or the intermediate connecting member (33) itself may be provided integrally so that it also performs the role of the internal connecting passage (5).

[0064] As such, an internal connecting passage (5) connecting the head and the fuselage is provided, allowing movement of crew, passengers, cargo, etc. between the variable head section (1) and the fuselage section (2).

[0065] FIG. 9 is a conceptual diagram viewed from above of a variable head portion of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention, in a state where it is rotated to the left, a normal (neutral) state, and a state where it is rotated to the right.

[0066] Referring to FIG. 9, the variable operating device (3) can be provided to enable left and right rotation with respect to the body part (2) with the vertical direction of the variable head part (1) as an axis.

[0067] Referring to FIG. 9 for example, the variable actuation device (3) may include a left linear extension actuator (321). Additionally, the variable actuation device (3) may include a right linear extension actuator (323) or a right hinge mechanism. As another example, the variable actuation device (3) may include a right linear extension actuator (323) and a left hinge mechanism.

[0068] The left linear extension actuator (321) is configured to directly or indirectly link the variable head part (1) and the body part (2) in the left space of the variable space (30) between the variable head part (1) and the body part (2). The right linear extension actuator (323) is configured to directly or indirectly link the variable head part (1) and the body part (2) in the right space of the variable space (30). Since this configuration is identical or similar to the upper and lower linear extension actuators (313, 323) described above, a more detailed explanation will be omitted.

[0069] For example, when the left linear extension actuator (321) is extended in length compared to normal (see Fig. 9 (b)) and the right linear extension actuator (323) is contracted in length compared to normal (see Fig. 9 (c)), the variable head part (1) can be rotated to the right with the vertical direction as the axis of rotation.

[0070] Also, as another example, when the left linear extension actuator (321) is contracted in length compared to normal (see Fig. 9 (b)) and the right linear extension actuator (323) is extended in length compared to normal (see Fig. 9 (a)), the variable head part (1) can be rotated to the left with the vertical direction as the axis of rotation.

[0071] Additionally, the right hinge mechanism is configured to link the variable head part (1) and the body part (2) in the right space of the variable space (30) without linear extension, using one or more hinges (hinges with the vertical direction as a rotation axis), and can be placed in place of the right linear extension actuator (323). For example, when the right hinge mechanism is placed in place of the right linear extension actuator (323), only the left linear extension actuator (321) is linearly extended; thus, when the left linear extension actuator (321) is linearly extended compared to the normal state (see (c) of FIG. 9), the variable head part (1) can be driven to rotate to the right. For reference, this right hinge mechanism can be understood as having the same or similar configuration by referring to the configuration of the right hinge mechanism designated by reference numeral 322 in FIG. 14 to 16, which will be described later.

[0072] Additionally, the left hinge mechanism is configured to link the variable head part (1) and the body part (2) in the left space of the variable space (30) without linear extension, using one or more hinges (hinges with the vertical direction as a rotation axis), and can be placed in place of the left linear extension actuator (323). For example, if the right hinge mechanism is placed in place of the left linear extension actuator (321), only the right linear extension actuator (323) is linearly extended; thus, when the right linear extension actuator (323) is linearly extended compared to the normal state (see FIG. 9 (a)), the variable head part (1) can be driven to rotate to the left. For reference, this left hinge mechanism can be understood as having the same or similar configuration by referring to the configuration of the left hinge mechanism designated by reference numeral 324 in FIG. 14 to 16, which will be described later.

[0073] In one embodiment of the present invention, the variable actuation device (3) may be provided to include two linear extension actuators (a left linear extension actuator and a right linear extension actuator) in response to rotation in the left and right directions, or to include one linear extension actuator (either one of the left linear extension actuator and the right linear extension actuator) and one hinge mechanism (the other of the left hinge mechanism and the right hinge mechanism).

[0074] As such, according to one embodiment of the present invention, the head (variable head portion) of the aircraft (aircraft) can be rotated in all directions by means of a variable operating device. That is, in the case of an aircraft to which the variable head aircraft (100) is applied, the head can be rotated in all directions—up, down, left, and right—by operating a variable operating device (actuator) to ensure visibility in the cockpit.

[0075] For example, when the head is rotated downward, the field of view of the cockpit equipped in the head also rotates downward, thereby reducing the blind spot below caused by head-up flight and securing a clear view. In particular, as described above and referring to FIG. 5, when a conventional aircraft approaches a runway in a head-up state during landing flight, it is impossible to visually check the conditions of the runway; however, an aircraft equipped with the variable head aircraft (100) can secure a clear view toward the runway, thereby preventing safety accidents that may occur during landing. Furthermore, according to one embodiment of the present invention, since the head moves independently of the fuselage, the attitude of the head can be maintained constant even if the attitude of the aircraft changes during flight, so the pilot's field of view is also maintained constant, thereby improving maneuverability, and passengers on board the head experience less change in attitude, thus reducing flight fatigue.

[0076] Meanwhile, another embodiment of the variable operating device (3) of the variable head aircraft (100) described below will be explained with reference to FIGS. 10 to 17. However, redundant descriptions of configurations identical or similar to those described in the embodiment corresponding to FIGS. 1 to 3 and FIG. 9 may be omitted.

[0077] FIG. 10 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention, based on a normal (neutral) state where the variable head part is not rotated. FIG. 11 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention and the movement of the head center of gravity based on a state where the variable head part is rotated downward; FIG. 12 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention and the movement of the head center of gravity based on a state where the variable head part is rotated upward; and FIG. 13 is a conceptual diagram of a part of a variable head aircraft viewed from the left to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention and the movement of the head center of gravity based on a state where the variable head part is not rotated (maintained neutral) but moved forward.

[0078] For reference, the drawing shown in (b) in each of FIGS. 10 to 12 can be understood as a perspective view of the configuration (drawing reference numerals 322, 323, 3422, 3423) located on the right side that is obscured and not visible when a part of the variable head aircraft (100) is viewed from the left.

[0079] Additionally, FIG. 14 is a conceptual diagram of a part of a variable head aircraft viewed from above to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention based on a normal (neutral) state in which the variable head part is not rotated; FIG. 15 is a conceptual diagram of a part of a variable head aircraft viewed from above to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention and the movement of the head center of gravity based on a state in which the variable head part is rotated to the right; and FIG. 16 is a conceptual diagram of a part of a variable head aircraft viewed from above to explain an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft form) according to an embodiment of the present invention and the movement of the head center of gravity based on a state in which the variable head part is rotated to the left.

[0080] For reference, the drawing shown in (b) in each of FIGS. 14 to 16 can be understood as a perspective view of a configuration (drawing reference numerals 312, 313, 3412, 3413) located on the lower side that is obscured and not visible when viewed from above of a part of the variable head aircraft (100).

[0081] In addition, FIG. 17 is a conceptual diagram for explaining an embodiment of a variable operating device of a variable head aircraft (an example of an aircraft shape) according to one embodiment of the present invention and a head center of gravity shift based on the state in which the variable head part is rotated downward and simultaneously rotated to the left.

[0082] Referring to FIGS. 10 to 17, the variable operating device (3) may include an intermediate connecting member (33) arranged to extend in the front-rear direction in the central space of the variable space (30) between the variable head part (1) and the body part (2), an up-and-down variable operating part (311, 312, 313, 314) installed on the variable head part (1), the intermediate connecting member (33), and the body part (2) for up-and-down rotation of the variable head part (1), and a left-and-right variable operating part (321, 322, 323, 324) installed on the variable head part (1), the intermediate connecting member (33), and the body part (2) for left-and-right rotation of the variable head part (1). For reference, the intermediate connecting member (33) is configured to form an internal connecting passage itself and may have the same configuration as the internal connecting passage part (5), but is not limited thereto. As another example, the intermediate connecting member (33) may be provided to surround at least a portion of the outer area of ​​the separately provided internal connecting passage (5).

[0083] More specifically, the upper and lower variable operating parts (311, 312, 313, 314) may include an upper linear extension actuator (311) that links the upper rear end of the variable head part (1) and the upper side of the intermediate connecting member (33) in the upper space of the variable space (30), a lower hinge mechanism (312) that hinges the lower rear end of the variable head part (1) and the lower side of the intermediate connecting member (33) in the lower space of the variable space (30), a lower linear extension actuator (313) that links the lower side of the intermediate connecting member (33) and the lower front end of the body part (2) in the lower space, and an upper hinge mechanism (312) that hinges the upper side of the intermediate connecting member (33) and the upper front end of the body part (2) in the upper space.

[0084] Additionally, the left and right variable operating parts (321, 322, 323, 324) may include a left linear extension actuator (321) that links the left rear end of the variable head part (1) and the left side of the intermediate connecting member (33) in the left space of the variable space (30), a right hinge mechanism (322) that hinges the right rear end of the variable head part (1) and the right side of the intermediate connecting member (33) in the right space of the variable space (30), a right linear extension actuator (323) that links the right side of the intermediate connecting member (33) and the right front end of the body part (2) in the right space, and a left hinge mechanism (324) that hinges the left side of the intermediate connecting member (33) and the left front end of the body part (2) in the left space.

[0085] Additionally, the intermediate connecting member (33) may be provided with a connecting part (34) that provides a degree of freedom of movement.

[0086] The connecting part (34) providing the degree of freedom of movement is configured such that when the vertical variable operating part (31) is operated, the part connected to the intermediate connecting member (33) in the horizontal variable operating part (32) is connected to the vertical variable operating part (31) and the part connected to the intermediate connecting member (33) in the horizontal variable operating part (31) is connected to the vertical variable operating part (32) and the part connected to the intermediate connecting member (33) is connected to the vertical variable operating part (31) and the part connected to the horizontal variable operating part (32) is connected to the horizontal variable operating part (32) and the part connected to the intermediate connecting member (33) is connected to the horizontal variable operating part (32) and the part provided with the degree of freedom to move along the curved path.

[0087] In other words, the movement freedom providing connection part (34) is provided together with an intermediate connecting member (33) (e.g., an internal connecting passage part), so that when the variable head part (1) is rotated up and down by driving at least one of the upper linear extension actuator (311) and lower linear extension actuator (313) of the upper and lower variable operating part (see FIG. 11 and FIG. 12), each component (321, 322, 323, 324) of the left and right variable operating part can move along a curved path (rotational movement) in accordance with this up and down rotational movement, or when the variable head part (1) is rotated left and right by driving at least one of the left linear extension actuator (321) and right linear extension actuator (323) of the left and right variable operating part (see FIG. 15 and FIG. 16), each component (321, 322, 323, 324) of the left and right variable operating part can move along a curved path (rotational movement) in accordance with this left and right rotational movement. It is a configuration that makes it possible.

[0088] Referring to FIGS. 10 and 11 for example, when the length of the upper linear extension actuator (311) increases, the variable head part (1) rotates downward around the lower hinge mechanism (312). At this time, each component (321, 322, 323, 324) of the left and right variable actuators located on the side is not directly fixed to the intermediate connecting member (33), but is indirectly connected to the intermediate connecting member (33) through each rotational member (rotational movement allowance member) (3421, 3422, 3423, 3424), so that they can rotate along a curved path in accordance with the downward rotation of the variable head part (1). More specifically, referring to FIG. 11, when the variable head part (1) is rotated downward, the left linear extension actuator (321) can be rotated by being connected to the left actuator rotation member (3421) (see FIG. 11 (a)), and the right hinge mechanism (322) can be rotated by being connected to the right hinge rotation member (3422) (see FIG. 11 (b)).

[0089] Additionally, referring to FIGS. 10 and 12, when the length of the lower linear extension actuator (313) increases, the variable head part (1) rotates upward around the upper hinge mechanism (314). At this time, each component (321, 322, 323, 324) of the left and right variable actuators located on the side is not directly fixed to the intermediate connecting member (33), but is indirectly connected to the intermediate connecting member (33) through each rotating member (rotational movement allowing member) (3421, 3422, 3423, 3424), so that it can rotate along a curved path in accordance with the upward rotation of the variable head part (1). More specifically, referring to FIG. 12, when the variable head part (1) is rotated upward, the right linear extension actuator (323) can be rotated by being connected to the right actuator rotation member (3423) (see FIG. 12 (b)), and the left hinge mechanism (324) can be rotated by being connected to the left hinge rotation member (3424) (see FIG. 12 (a)).

[0090] If each component (321, 322, 323, 324) of the left and right variable operating unit is directly fixed to the intermediate connecting member (33), then due to this left and right fixed state, downward rotation or upward rotation of the variable head unit (1) cannot proceed, so it is necessary to provide such a rotating member (a member that allows rotational movement) to implement both upward and downward rotation and left and right rotation. For example, such rotating members (3421, 3422, 3423, 3424) may be provided so that the component part connected to the intermediate connecting member (33) in the left and right variable operating unit (321, 322, 323, 324) can slide or rail move along the arc-shaped curve path shown in FIGS. 11 and 12, but this is not limited thereto, and various rotating members (members that allow degrees of freedom to move along a curve path) known to a person skilled in the art of mechanical devices or developed in the future may be applied and provided.

[0091] Additionally, referring to FIGS. 14 and 15 for example, when the length of the left linear extension actuator (321) increases, the variable head part (1) rotates to the right around the right hinge mechanism (322). At this time, each component (311, 312, 313, 314) of the upper and lower variable actuators located on the upper and lower surfaces is not directly fixed to the intermediate connecting member (33), but is indirectly connected to the intermediate connecting member (33) through each rotational member (rotational movement allowance member) (3411, 3412, 3413, 3414), so that they can rotate along a curved path in accordance with the rightward rotation of the variable head part (1). More specifically, referring to FIG. 15, when the variable head part (1) is rotated to the right, the upper linear extension actuator (311) can be rotated by being connected to the upper actuator rotation member (3411) (see FIG. 15 (a)), and the lower hinge mechanism (312) can be rotated by being connected to the lower hinge rotation member (3412) (see FIG. 15 (b)).

[0092] Additionally, referring to FIGS. 14 and 16, when the length of the right linear extension actuator (323) increases, the variable head part (1) rotates to the left around the left hinge mechanism (324). At this time, each component (311, 312, 313, 314) of the upper and lower variable actuators located on the upper and lower surfaces is not directly fixed to the intermediate connecting member (33), but is indirectly connected to the intermediate connecting member (33) through each rotational member (rotational movement allowance member) (3411, 3412, 3413, 3414), so that they can rotate along a curved path in accordance with the leftward rotation of the variable head part (1). More specifically, referring to FIG. 16, when the variable head part (1) is rotated to the left, the lower linear extension actuator (313) can be rotated by being connected to the lower actuator rotation member (3413) (see FIG. 16 (b)), and the upper hinge mechanism (314) can be rotated by being connected to the upper hinge rotation member (3414) (see FIG. 16 (a)).

[0093] If each component (311, 312, 313, 314) of the vertical variable operating part is directly fixed to the intermediate connecting member (33), then due to this vertical fixed state, the rightward rotation or leftward rotation of the variable head part (1) cannot proceed, so it is necessary to provide such a rotating member (rotational movement allowing member) to implement both vertical rotation and leftward rotation. For example, such rotating members (3411, 3412, 3413, 3414) may be provided such that a component connected to an intermediate connecting member (33) in an up-and-down variable operating part (311, 312, 313, 314) along an arc-shaped curved path shown in FIGS. 15 and 16 can slide or rail move, but is not limited thereto, and various rotating members (members that allow a degree of freedom to move along a curved path) known to a person skilled in the art of machinery and equipment or developed in the future may be applied and provided.

[0094] In addition, regarding the movement of the head center of gravity, the head center of gravity is moved forward in the downward rotation state of Fig. 11 or the upward rotation state of Fig. 12, in contrast to the normal neutral state of Fig. 10. Also, the head center of gravity is moved forward in the right rotation state of Fig. 15 or the left rotation state of Fig. 16, in contrast to the normal neutral state of Fig. 14. Since the rotation of the variable head part (1) in the up, down, left, and right directions is implemented through the length extension of the linear extension actuators (311, 313, 321, 323) at each position, it can be understood that such forward movement of the head center of gravity is accompanied by this.

[0095] Additionally, referring to FIG. 13, when the length of all linear extension actuators (311, 313, 321, 323) is contracted or increased, the variable head portion (1) may remain in a neutral position without rotating, or the head center of gravity may be moved forward and backward while the variable head portion (1) rotates only slightly. In this case, each hinge mechanism (312, 314, 322, 324) may be moved along each rotating member (3412, 3414, 3422, 3424).

[0096] Additionally, the variable head unit (1) may simultaneously implement either vertical rotation and either horizontal rotation. That is, the variable head aircraft (1) may be provided to rotate the variable head unit (1) in various directions, including upward, downward, left, and right, according to the operation combination of linear extension actuators.

[0097] Referring to FIG. 17 for example, when the length of the upper linear extension actuator (311) increases and the length of the right linear extension actuator (323) also increases, the variable head part (1) rotates around the lower hinge mechanism (312) and also rotates around the left hinge mechanism (324), so that the variable head part (1) rotates in a direction that combines downward rotation and left rotation. At this time, among the components not involved in the rotational drive, the left linear extension actuator (321) is connected to the left actuator rotation member (3421) and rotates along an arc-shaped curve path, the right hinge mechanism (322) is connected to the right hinge rotation member (3422) and rotates along an arc-shaped curve path, the lower linear extension actuator (313) is connected to the lower actuator rotation member (3413) and rotates along an arc-shaped curve path, and the upper hinge mechanism (314) is connected to the upper hinge rotation member (3414) and rotates along an arc-shaped curve path.

[0098] FIG. 18 is a conceptual diagram illustrating a variable skin structure applied to one embodiment of a variable actuation device of a variable head aircraft (an example in the form of an aircraft) according to one embodiment of the present invention.

[0099] Referring together to FIGS. 1 to 3, FIG. 9, and FIG. 18, the variable head aircraft (100) may include a variable skin structure (4). The variable skin structure (4) is configured to surround the variable space (30) so as to prevent external exposure of the variable operating device (3) installed in the variable space (30) between the variable head part (1) and the fuselage part (2) when the variable head part (1) rotates relative to the fuselage part (2). The variable skin structure (4) is configured to be able to extend and contract within an up-and-down rotational range, and may be provided with a stretchable material that does not cause wrinkles.

[0100] That is, the variable skin structure (4) can be described as a structure that smoothly connects the variable head part (1) and the body part (2), which are provided separated from each other. When the variable head part (1) rotates up, down, left, and right, there is a possibility that wrinkles will occur in the area of ​​the variable skin structure (4) that is relatively shortened in length to accommodate the rotation of the head part (1).

[0101] For example, referring to the enlarged view of part (a) in FIG. 2 and (c) in FIG. 18, when the variable head part (1) rotates downward, the upper part of the variable skin structure (4) is stretched and the lower part is contracted. Also, referring to the enlarged view of part (a) in FIG. 3 and (a) in FIG. 18, when the variable head part (1) rotates upward, the lower part of the skin structure is stretched and the upper part is contracted.

[0102] However, since wrinkles may occur in the skin of an aircraft or other flying vehicle due to contraction of the lower part or upper part of the variable skin structure (4), the aerodynamic performance of the flying vehicle may be degraded, it is desirable that the variable skin structure (4) be provided in the variable head flying vehicle (100) to smoothly connect the variable head part (1) and the fuselage part (2) in order to improve aerodynamic performance. For example, the variable skin structure (4) can be implemented in a wrinkle-free variable skin form by utilizing a material with good elasticity or a material such as a shape memory alloy / polymer. For reference, the term "wrinkle-free variable skin form" does not refer only to a case where there are absolutely no wrinkles, but can be understood to broadly refer to a case where the occurrence of wrinkles is significantly reduced compared to when a material with good elasticity or a shape memory alloy / polymer is not used.

[0103] Meanwhile, the present invention may provide a method for controlling the variable head part (1) of the variable head aircraft (100) described above (hereinafter referred to as the ‘present method’), and the present method is described below. However, since the present method shares the same or corresponding technical features as the variable head aircraft (100) described above, the same reference numerals are used for configurations that are identical or similar to the configuration described in relation to the variable head aircraft (100), and redundant descriptions are to be simplified or omitted.

[0104] In this method, the control unit controls the variable operating device (3) to rotate the variable head unit (1) in the up and down direction within the up and down rotation range of the variable head unit (1). At this time, the up and down rotation range of the variable head unit (1) can be set considering securing a field of view that reduces the lower blind spot that occurs during head-up flight of the variable head aircraft (100) compared to the normal state when the variable head unit (1) is not rotated up and down.

[0105] In addition, in this method, the control unit can control the variable operating device (3) to rotate the variable head unit (1) in the left and right directions within the left and right rotation range of the variable head unit (1).

[0106] In addition, in this method, the control unit can control the variable operating device (3) so that the center of gravity of the variable head unit (1) is shifted by considering the forward limit and the rear limit of the center of gravity of the variable head aircraft (100).

[0107] Meanwhile, the method for controlling the variable head portion of a variable head aircraft according to one embodiment of the present invention may be implemented in the form of program instructions that can be executed through various computer means and recorded on a computer-readable medium. The computer-readable medium may include program instructions, data files, data structures, etc., either individually or in combination. The program instructions recorded on the medium may be those specifically designed and configured for the present invention, or they may be those known and available to those skilled in the art of computer software. Examples of computer-readable recording media include magnetic media such as hard disks, floppy disks, and magnetic tapes; optical recording media such as CD-ROMs and DVDs; magneto-optical media such as floptical disks; and hardware devices specifically configured to store and execute program instructions, such as ROM, RAM, and flash memory. Examples of program instructions include machine code, such as that generated by a compiler, as well as high-level language code that can be executed by a computer using an interpreter, etc. The above-described hardware device may be configured to operate as one or more software modules to perform the operation of the present invention, and vice versa.

[0108] In addition, the variable head control method of the aforementioned variable head aircraft can also be implemented in the form of a computer program or application stored on a computer-readable recording medium and executed by a computer.

[0109] The foregoing description of the present invention is for illustrative purposes only, and those skilled in the art will understand that other specific forms can be easily modified without altering the technical concept or essential features of the present invention. Therefore, the embodiments described above should be understood as illustrative in all respects and not restrictive. For example, each component described as a single unit may be implemented in a distributed manner, and components described as distributed may likewise be implemented in a combined form.

[0110] The scope of the present invention is defined by the claims set forth below rather than by the detailed description above, and all modifications or variations derived from the meaning and scope of the claims and the concept of equivalents thereof should be interpreted as being included within the scope of the present invention. Explanation of the symbols

[0111] 100: Variable Head Aircraft 1: Variable head unit 2: Fuselage 3: Variable actuation device 30: Variable space 4: Variable Skin Structure 5: Internal connecting passageway 311, 312, 313, 314: Vertical variable operating parts 311: Upper linear extension actuator 312: Lower hinge mechanism 313: Lower linear extension actuator 314: Upper hinge mechanism 321, 322, 324, 324: Left and right variable operating parts 321: Left linear extension actuator 322: Right hinge mechanism 323: Right linear extension actuator 324: Left hinge mechanism 33: Intermediate connecting member 34: Connection providing degrees of freedom of movement 3411: Upper actuator rotating member (rotational movement allowing member) 3412: Lower hinge rotational member (rotational movement allowing member) 3413: Lower actuator rotating member (rotational movement allowing member) 3414: Upper hinge rotational member (rotational movement allowing member) 3421: Left actuator rotary member (rotational movement allowing member) 3422: Right hinge rotational member (rotational movement allowing member) 3423: Right actuator rotating member (rotational movement allowing member) 3424: Left hinge rotational member (rotational movement allowing member)

Claims

Claim 1 A variable head aircraft comprising: a variable head section; a fuselage section provided at the rear of the variable head section and separated from the variable head section; a variable actuation device connecting the variable head section and the fuselage section, provided such that vertical rotation with respect to the fuselage section is possible with respect to the variable head section with respect to the left and right directions of the variable head section as an axis; and a control unit for controlling the variable actuation device for vertical rotation of the variable head section, wherein the vertical rotation range of the variable head section is set considering securing a field of view that reduces the lower blind spot occurring during head-up flight of the variable head aircraft compared to normal conditions when the variable head section is not rotated vertically, and wherein the variable actuation device is provided such that horizontal rotation with respect to the fuselage section is possible with respect to the variable head section with respect to the vertical directions of the variable head section as an axis, and wherein the variable actuation device comprises: an intermediate connecting member disposed to extend in the front-rear direction in the central space of the variable space between the variable head section and the fuselage section; and a vertical variable actuation unit installed on the variable head section, the intermediate connecting member, and the fuselage section for vertical rotation of the variable head section. A variable head aircraft comprising a variable head portion, an intermediate connecting member, and a left and right variable operating portion installed in the fuselage portion for left and right rotation of the variable head portion. Claim 2 In paragraph 1, the variable head aircraft is a passenger aircraft, a military aircraft, a UAM (Urban Air Mobility), or a space launch vehicle. Claim 3 delete Claim 4 A variable head aircraft according to claim 1, wherein the lower blind spot comprises one or more of the lower blind spot of a pilot in the cockpit provided in the variable head and the lower blind spot of a camera or radar provided in the variable head. Claim 5 The variable head aircraft according to claim 1 further comprises a variable skin structure provided to surround the variable space so as to prevent external exposure of the variable operating device installed in the variable space between the variable head part and the fuselage part when the variable head part rotates relative to the fuselage part, wherein the variable skin structure is provided to be expandable and contractable within the vertical rotation range and is provided with a stretchable material that does not produce wrinkles. Claim 6 In paragraph 5, the variable head aircraft further comprises an internal connecting passage that extends across the variable space within the variable operating device and is configured to movably connect the variable head portion and the fuselage portion. Claim 7 A variable head aircraft according to claim 1, wherein the variable operating device is configured to shift the center of gravity of the variable head part forward compared to normal during vertical rotation of the variable head part. Claim 8 In claim 7, the control unit controls the variable operating device so that the center of gravity of the variable head unit is shifted by taking into account the forward limit and rear limit of the center of gravity of the variable head aircraft. Claim 9 delete Claim 10 delete Claim 11 In claim 1, the upper and lower variable operating unit comprises: an upper linear extension actuator linking the upper rear end of the variable head unit and the upper side of the intermediate connecting member in the upper space of the variable space; a lower hinge mechanism hinge connecting the lower rear end of the variable head unit and the lower side of the intermediate connecting member in the lower space of the variable space; a lower linear extension actuator linking the lower side of the intermediate connecting member and the lower front end of the fuselage unit in the lower space; and an upper hinge mechanism hinge connecting the upper side of the intermediate connecting member and the upper front end of the fuselage unit in the upper space, and the left and right variable operating unit comprises: a left linear extension actuator linking the left rear end of the variable head unit and the left side of the intermediate connecting member in the left space of the variable space; a right hinge mechanism hinge connecting the right rear end of the variable head unit and the right side of the intermediate connecting member in the right space of the variable space; and a right linear extension actuator linking the right side of the intermediate connecting member and the right front end of the fuselage unit in the right space. A variable head aircraft comprising a left hinge mechanism that hinge-connects the left side of the intermediate connecting member and the left front end of the fuselage in the left space. Claim 12 A variable head aircraft according to claim 11, wherein the intermediate connecting member is provided with a degree of freedom of movement providing a connecting member that allows a component part connected to the intermediate connecting member from the left and right variable operating part to move along a curved path in conjunction with the operation of the up and down variable operating part when the up and down variable operating part is operated, and a component part connected to the intermediate connecting member from the up and down variable operating part to move along a curved path in conjunction with the operation of the left and right variable operating part when the left and right variable operating part is operated. Claim 13 A method for controlling the variable head portion of a variable head aircraft according to claim 1, wherein the control unit controls the variable operating device to rotate the variable head portion in the up-and-down direction within the up-and-down rotation range of the variable head portion, or rotate the variable head portion in the left-and-right direction within the left-and-right rotation range of the variable head portion. Claim 14 delete Claim 15 A method for controlling a variable head unit of a variable head aircraft, wherein, in paragraph 13, the control unit controls the variable operating device so that the center of gravity of the variable head unit is shifted by considering the forward limit and the rear limit of the center of gravity of the variable head aircraft.

Images