Flying object

Abstract

To provide a flying object capable of holding a landing leg with a simple configuration.SOLUTION: A flying object according to an embodiment comprises: a flying object body 2; and a landing leg configured to be able to transition between a retracted state of being retracted in a position along the flying object body 2; and a deployed state of being deployed to a position away from the flying object 2. The flying object body 2 comprises a first protrusion 11 protruding from a part of the flying object body 2. The landing leg comprises a second protrusion 12 protruding from a part of the landing leg. In the retracted state, the first protrusion 11 and the second protrusion 12 face each other in a direction away from the flying object body 2.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present invention relates to an air vehicle. [Background technology]

[0002] For example, Patent Document 1 discloses a structure for holding the landing gear of an aircraft in a retracted state. In this structure, the landing gear is switched between a retracted state and an extended state by the relative movement and rotation of two cylinder structures. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Publication No. 2023-148642 Summary of the Invention [Problem to be solved by the invention]

[0004] However, a movable device and / or additional mechanism is required to maintain the landing legs in a retracted state. Therefore, there is a demand for an air vehicle that can maintain the landing legs with a simple configuration.

[0005] SUMMARY OF THE INVENTION It is therefore an object of the present invention to provide an aircraft capable of holding landing gear with a simple configuration. [Means for solving the problem]

[0006] (1) An aircraft according to one aspect of the present invention (e.g., aircraft 1 in the embodiments) comprises an aircraft body (e.g., aircraft body 2 in the embodiments) and landing legs (e.g., landing legs 3 in the embodiments) that are configured to transition between a stored state in which they are stored in a position along the aircraft body and a deployed state in which they are deployed away from the aircraft body, wherein the aircraft body comprises a first protrusion (e.g., first protrusion 11 in the embodiments) protruding from a portion of the aircraft body, and the landing legs comprise a second protrusion (e.g., second protrusion 12 in the embodiments) protruding from a portion of the landing legs, and the first protrusion and the second protrusion face each other in a direction away from the aircraft body in the stored state.

[0007] (2) In one aspect of the present invention, the first protrusion may be rotatable about a predetermined axis (for example, predetermined axis A in the embodiment).

[0008] (3) In one aspect of the present invention, the first protrusion may rotate around the predetermined axis, thereby releasing the opposing relationship between the first protrusion and the second protrusion.

[0009] (4) In one aspect of the present invention, the first protrusion and the second protrusion may overlap each other when viewed from a direction along the predetermined axis in the stored state.

[0010] (5) In one aspect of the present invention, a frame (e.g., frame 5 in the embodiment) may be provided on the outer side of the aircraft body, and the first protrusion and the second protrusion may face each other outside the frame relative to the aircraft body in the stored state.

[0011] (6) In one aspect of the present invention, a drive unit (for example, drive unit 20 in the embodiment) that drives the first protrusion may be provided directly above the frame.

[0012] (7) In one aspect of the present invention, in the stored state, power may not be supplied to the drive unit.

[0013] (8) In one aspect of the present invention, a lever (for example, lever 30 in the embodiment) may be provided that includes the first protrusion and is configured to be rotatable by the driving force of the driving unit.

[0014] (9) In one aspect of the present invention, a portion of the lever may be formed in a shape that fits along the frame directly above the frame.

[0015] (10) In one aspect of the present invention, a biasing member (for example, biasing member 9 in the embodiment) may be provided that biases the lever so as to maintain the first protrusion and the second protrusion facing each other in the stored state.

[0016] (11) In one aspect of the present invention, a limit switch (for example, limit switch 40 in the embodiment) that detects the movement of the lever may be provided, and a portion of the limit switch may be formed into a shape that conforms to the frame.

[0017] (12) In one aspect of the present invention, the lever may include a first arm (e.g., first arm 31 in the embodiment) on which the first protrusion is provided, and a second arm (e.g., second arm 32 in the embodiment) that is provided so as to be able to contact the limit switch.

[0018] (13) In one aspect of the present invention, the device may include a detection unit (e.g., detection unit 50 in the embodiment) that detects the current value of the drive unit, and a determination unit (e.g., determination unit 51 in the embodiment) that determines the drive state of the drive unit based on the detection result of the detection unit.

[0019] (14) In one aspect of the present invention, the determination unit may determine the drive state of the drive unit based on each of the detection result of the limit switch and the detection result of the detection unit.

[0020] (15) In one aspect of the present invention, the drive unit may be configured with a solenoid. [Effects of the Invention]

[0021] According to the above aspect (1), the aircraft comprises an aircraft body and landing legs configured to be able to transition between a stored state in which they are stored in a position along the aircraft body and a deployed state in which they are deployed to a position away from the aircraft body, the aircraft body comprising a first protrusion protruding from a part of the aircraft body, and the landing legs comprising a second protrusion protruding from a part of the landing legs, the first protrusion and the second protrusion facing each other in a direction away from the aircraft body in the stored state, thereby achieving the following effects. The landing gear can be held in the stowed state by the first protrusion and the second protrusion facing each other. Therefore, no movable device and / or additional mechanism is required to hold the landing gear in the stowed state. Therefore, it is possible to provide an aircraft that can hold the landing gear with a simple configuration.

[0022] According to the above aspect (2), the first projection is rotatable about a predetermined axis, thereby providing the following effects. Compared to when the primary projections are moved linearly (for example, by stroking up and down), it is easier to prevent the projections from becoming large.

[0023] According to the above aspect (3), the first protrusion rotates around a predetermined axis, thereby releasing the opposing relationship between the first protrusion and the second protrusion, thereby achieving the following effects. Rotation of the first protrusion allows the landing legs to be retracted, held, or released.

[0024] According to the above aspect (4), the first protrusion and the second protrusion overlap each other when viewed from the direction along the predetermined axis in the stored state, thereby achieving the following effects. This makes it easier to prevent the landing gear from bouncing up in the deployment direction compared to when the first protrusion and the second protrusion do not overlap each other (are offset) when viewed from the direction along the specified axis in the stored state.

[0025] According to the above aspect (5), a frame is provided on the outer part of the aircraft body, and the first protrusion and the second protrusion face each other outside the frame relative to the aircraft body in the stored state, thereby achieving the following effects. In the retracted state, the first and second protrusions are more easily spaced inside the frame than when they face each other on the inside of the frame relative to the aircraft body.

[0026] According to the above aspect (6), the following effects are achieved by providing a drive unit that drives the first protrusion directly above the frame. By driving the first protrusion, the landing gear can be retracted, held, or released. In addition, it can free up space inside the frame.

[0027] According to the above aspect (7), in the stored state, no power is supplied to the drive unit, which provides the following effects. Since no power is required to retract and maintain the landing gear, this contributes to energy conservation.

[0028] According to the above aspect (8), the lever including the first protrusion and configured to be rotatable by the driving force of the driving unit is provided, thereby achieving the following effects. By rotating the lever, the landing gear can be retracted, held, or released.

[0029] According to the above aspect (9), a part of the lever is formed in a shape that fits the frame directly above the frame, thereby achieving the following effects. This allows for more space inside the frame.

[0030] According to the above aspect (10), the provision of a biasing member that biases the lever so as to maintain the first protrusion and the second protrusion facing each other in the stored state provides the following effects. Since no power is required to retract and maintain the landing gear, this contributes to energy conservation.

[0031] According to the above aspect (11), a limit switch for detecting the operation of the lever is provided, and a part of the limit switch is formed in a shape that follows the frame, thereby achieving the following effects. The limit switch can detect the movement of the lever, and it also allows for more space inside the frame.

[0032] According to the above aspect (12), the lever includes the first arm provided with the first protrusion and the second arm provided so as to be able to come into contact with the limit switch, thereby achieving the following effects. The lever can have two functions (the first arm holds / releases the landing gear in place, and the second arm operates the limit switch). This eliminates the need for a separate part to operate the limit switch, allowing for a simpler configuration.

[0033] According to the above aspect (13), by providing a detection unit that detects the current value of the drive unit and a determination unit that determines the drive state of the drive unit based on the detection result of the detection unit, the following effects are achieved. The driving status of the drive unit can be grasped.

[0034] According to the above aspect (14), the determination unit determines the drive state of the drive unit based on the detection result of the limit switch and the detection result of the detection unit, thereby achieving the following effects. The drive status of the drive unit can be determined based on two conditions (the limit switch detecting the movement of the lever, and the detector detecting the current value of the drive unit), which allows for redundancy.

[0035] According to the above aspect (15), the drive unit is configured with a solenoid, which provides the following effects. Compared to when the drive unit is configured with an electric motor (for example, a servo motor), the power and control load can be reduced. [Brief explanation of the drawings]

[0036] [Figure 1] FIG. 2 is a partially enlarged perspective view of the aircraft according to the embodiment. [Figure 2] FIG. 2 is a perspective view of a part of the aircraft according to the embodiment, seen from a different direction than that of FIG. 1. [Figure 3] FIG. 4 is an explanatory diagram illustrating the arrangement of the first protrusion and the second protrusion in the stored state according to the embodiment. [Figure 4]FIG. 10 is an explanatory diagram of the arrangement of the lever when released according to the embodiment. [Figure 5] FIG. 2 is a perspective view showing the deployed state of the landing gear of the aircraft according to the embodiment. [Figure 6] FIG. 2 is a perspective view showing the retracted state of the landing gear of the aircraft of the embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0037] Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the following description, expressions indicating relative or absolute arrangements, such as "parallel," "orthogonal," "center," and "coaxial," do not strictly mean such arrangements or states, but also include arrangements or states in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. In the drawings used in the following description, the scale of each component may be appropriately changed to show each component in a recognizable size.

[0038] <Flying object> 1 to 6, aircraft 1 comprises aircraft body 2 and landing legs 3. The landing legs 3 are configured to be able to transition between a stored state (see FIG. 6) in which they are stored in a position along the aircraft body 2, and a deployed state (see FIG. 5) in which they are deployed to a position away from the aircraft body 2. The aircraft body 2 is connected to the landing legs 3 via a link mechanism 90.

[0039] The example of Figure 5 shows an aircraft 1 standing vertically relative to the ground. The upper side of the paper in Figure 5 corresponds to the upper side in the vertical direction. The lower side of the paper in Figure 5 corresponds to the lower side in the vertical direction (towards the ground). The aircraft body 2 extends in the up-down direction (vertical direction). Multiple landing legs 3 (for example, four) are provided on the aircraft body 2. In the example of Figure 5, one of the four landing legs 3 is shown, and the other landing legs 3 are not shown.

[0040] The link mechanism 90 includes a lower beam 91, the first end of which is rotatably connected to the aircraft body 2, and the second end of which is rotatably connected to the landing leg 3. A pair of lower beams 91 are provided, with the first ends connected to two locations on the aircraft body 2. In the deployed state, the pair of lower beams 91 extend horizontally outward from their first ends and then approach each other toward their second ends on the landing leg 3 side. An actuator or the like (not shown) that drives the landing leg 3 may be provided between the pair of lower beams 91. In the example of FIGS. 1 to 4, a portion of the aircraft 1 corresponding to one landing leg 3 is shown, and the other portions are not shown.

[0041] 1 to 4, the aircraft body 2 has a first protrusion 11 protruding from a portion of the aircraft body 2. The landing leg 3 has a second protrusion 12 protruding from a portion of the landing leg 3. In the retracted state, the first protrusion 11 and the second protrusion 12 face each other in directions away from the aircraft body 2. The states shown in FIGS. 1 to 3 correspond to the retracted state of the landing leg 3.

[0042] The first protrusion 11 is rotatable around a predetermined axis A. In this embodiment, the first protrusion 11 and the second protrusion 12 are released from opposing each other when the first protrusion 11 rotates around the predetermined axis A. The state shown in FIG. 4 corresponds to a state in which the first protrusion 11 and the second protrusion 12 are released from opposing each other.

[0043] In the stowed state, the first protrusion 11 and the second protrusion 12 overlap each other when viewed in a direction along a predetermined axis A. In the example of FIG. 1, the second protrusion 12 protrudes from a portion of the bracket 4 attached to the landing leg 3. In the stowed state, a portion of the second protrusion 12 is disposed between the outer portion (frame 5) of the aircraft body 2 and the first protrusion 11. This limits movement of the second protrusion 12 away from the aircraft body 2 in the stowed state.

[0044] In this embodiment, a frame 5 is provided on the outer side of the aircraft main body 2. The first protrusion 11 and the second protrusion 12 face each other on the outer side of the frame 5 relative to the aircraft main body 2 in the retracted state.

[0045] In the following explanation, an X, Y, Z Cartesian coordinate system will be used as necessary. The X direction corresponds to the direction in which the frame 5 extends (longitudinal direction). The Y direction corresponds to the thickness direction of the frame 5. The Z direction corresponds to the height direction (short direction) that is perpendicular to both the longitudinal direction (X direction) and the thickness direction (Y direction) of the frame 5. In the following explanation, of the X, Y, and Z directions, the arrow side in the figure will be referred to as the plus (+) side, and the side opposite the arrow will be referred to as the minus (-) side. The +X side corresponds to one side in the longitudinal direction, and the -X side corresponds to the other side in the longitudinal direction.

[0046] The frame 5 extends in the X direction so as to connect, for example, two adjacent columns out of a plurality of columns (not shown) extending in the Z direction. The frame 5 may be disposed at a position corresponding to a side portion of a quadrangle (a straight portion of a rectangular frame) when viewed from the Z direction. In the example shown in the figure, the first protrusion 11 and the second protrusion 12 face each other on the -Y side of the frame 5 in the stored state.

[0047] In this embodiment, a drive unit 20 that drives the first protrusion 11 is provided directly above the frame 5. A portion of the drive unit 20 overlaps with the frame 5 when viewed from the Z direction. A portion of the drive unit 20 is formed in a cylindrical shape along the Z direction. The drive unit 20 is supported by a stay 6. The stay 6 is connected to the frame 5. The stay 6 is fixed to the frame 5 with a fastening member such as a bolt. The drive unit 20 may be connected to a wiring 22 for supplying power, for example.

[0048] The drive unit 20 is configured with a solenoid. The drive unit 20 includes a plunger 21 (movable iron core) that is movable in the Z direction. For example, when power is supplied to the drive unit 20, the plunger 21 moves toward the -Z side from its initial position. When power is not supplied to the drive unit 20, the plunger 21 moves toward the +Z side (returns to its initial position). In this embodiment, no power is supplied to the drive unit 20 in the stored state.

[0049] In this embodiment, the lever 30 includes a first protrusion 11 and is configured to be rotatable by the driving force of the driving unit 20. The lever 30 is supported by a holder 7. The lever 30 is supported by the holder 7 so as to be rotatable around a pin 8. The holder 7 is connected to a frame 5. The holder 7 is fixed to the frame 5 with a fastening member such as a bolt. The pin 8 is provided on a portion of the holder 7 on the +Z side of the frame 5. Both ends of the pin 8 in the Y direction are supported (double-supported) by portions of the holder 7 spaced apart in the Y direction.

[0050] A part of the lever 30 is formed in a shape that fits along the frame 5 directly above the frame 5. A part of the lever 30 overlaps with the frame 5 when viewed from the Z direction.

[0051] In this embodiment, a biasing member 9 is provided that biases the lever 30 so as to maintain the first protrusion 11 and the second protrusion 12 facing each other in the stored state. The biasing member 9 is, for example, a coil spring. One end of the biasing member 9 is attached to a portion of the lever 30. The other end of the biasing member 9 is attached to a portion of the holder 7.

[0052] In this embodiment, a limit switch 40 is provided that detects the operation of the lever 30. A portion of the limit switch 40 is formed in a shape that follows the frame 5. A portion of the limit switch 40 is formed in a shape that has its length in the X direction. The limit switch 40 is provided on the -Y side of the frame 5. The limit switch 40 is fixed to the frame 5 with a fastening member such as a bolt.

[0053] The lever 30 includes a first arm 31 provided with a first protrusion 11, and a second arm 32 provided so as to be able to come into contact with the limit switch 40. The lever 30 includes an insertion portion 33 between the first arm 31 and the second arm 32, through which the pin 8 is inserted.

[0054] First arm 31 extends from insertion portion 33 to the -X side, and then extends obliquely toward the -Y and -Z sides. First protrusion 11 is provided at the -Z end of first arm 31. One end of biasing member 9 is attached to a +Z side portion of first arm 31 (a portion closer to insertion portion 33).

[0055] Second arm 32 extends from insertion portion 33 to the +X side and then extends toward the +Y side. The +Y end of second arm 32 is provided so as to be able to come into contact with limit switch 40. Plunger 21 is able to come into contact with the +Z side portion of second arm 32 (the portion closer to insertion portion 33).

[0056] In this embodiment, when the landing legs 3 are in the retracted state, no power is supplied to the drive unit 20. In the retracted state, the plunger 21 of the drive unit 20 is in its initial position. In the retracted state, the biasing member 9 biases the lever 30 so as to maintain the first protrusion 11 and the second protrusion 12 facing each other. Due to this biasing, in the retracted state, the first protrusion 11 and the second protrusion 12 face each other in the Y direction (see FIGS. 1 and 3).

[0057] On the other hand, when the landing legs 3 are to be released from the retracted state, power is supplied to the drive unit 20. When power is supplied to the drive unit 20, the plunger 21 of the drive unit 20 moves toward the -Z side from its initial position. The plunger 21 rotates the lever 30 about a predetermined axis A (rotating clockwise when viewed from the -Y direction) against the biasing force of the biasing member 9. This rotation releases the first protrusion 11 and the second protrusion 12 from opposing each other in the Y direction (see FIG. 4). At this time, the second arm 32 comes into contact with the limit switch 40, activating the limit switch 40.

[0058] In this embodiment, a detection unit 50 that detects the current value of the drive unit 20 and a determination unit 51 that determines the drive state of the drive unit 20 based on the detection result of the detection unit 50 are provided.

[0059] The determination unit 51 constitutes a control device (not shown). The determination unit 51 determines the driving state of the driving unit 20 based on the detection result of the limit switch 40 and the detection result of the detection unit 50.

[0060] The determination unit 51 determines the drive state of the drive unit 20 based on two conditions (that the limit switch 40 has detected the operation of the lever 30, and that the detection unit 50 has detected the current value of the drive unit 20). The detection of the operation of the lever 30 by the limit switch 40 corresponds to the second arm 32 coming into contact with the limit switch 40. The detection of the current value of the drive unit 20 by the detection unit 50 corresponds to the current value of the drive unit 20 detected by the detection unit 50 exceeding a predetermined threshold value.

[0061] <Action and effect> As described above, the aircraft 1 in the above embodiment comprises the aircraft main body 2 and landing legs 3 that are configured to transition between a stored state in which they are stored in a position along the aircraft main body 2, and a deployed state in which they are deployed to a position away from the aircraft main body 2. The aircraft main body 2 comprises a first protrusion 11 that protrudes from a portion of the aircraft main body 2. The landing legs 3 comprise a second protrusion 12 that protrudes from a portion of the landing legs 3. The first protrusion 11 and second protrusion 12 face each other in a direction away from the aircraft main body 2 in the stored state. With this configuration, the retracted state can be maintained by the opposing first protrusions 11 and second protrusions 12. Therefore, no movable device and / or additional mechanism is required to maintain the retracted state of the landing legs 3. Therefore, it is possible to provide an aircraft that can maintain the landing legs 3 with a simple configuration.

[0062] In the above embodiment, the first protrusion 11 is rotatable about a predetermined axis A. According to this configuration, it is easier to prevent the size from increasing compared to when the primary projection 11 is moved linearly (for example, by stroking up and down).

[0063] In the above embodiment, the first protrusion 11 rotates around the predetermined axis A, thereby releasing the opposing relationship between the first protrusion 11 and the second protrusion 12. According to this configuration, the landing legs 3 can be retracted, held, or released by rotating the first protrusions 11.

[0064] In the above embodiment, the first protrusion 11 and the second protrusion 12 overlap each other when viewed from the direction along the predetermined axis A in the stored state. With this configuration, it is easier to prevent the landing leg 3 from bouncing up in the deployment direction compared to when the first protrusion 11 and the second protrusion 12 do not overlap each other (are offset) when viewed from the direction along the specified axis A in the stored state.

[0065] In the above embodiment, the frame 5 is provided on the outer side of the aircraft main body 2. The first protrusion 11 and the second protrusion 12 face each other on the outer side of the frame 5 relative to the aircraft main body 2 in the retracted state. With this configuration, it is easier to ensure space inside the frame 5 compared to when the first protrusion 11 and the second protrusion 12 are facing each other on the inside of the frame 5 relative to the aircraft main body 2 in the retracted state.

[0066] In the above embodiment, the drive unit 20 for driving the first protrusion 11 is provided immediately above the frame 5 . According to this configuration, the landing legs 3 can be held in a retracted state or released by driving the first protrusions 11. In addition, space inside the frame 5 can be secured.

[0067] In the above embodiment, no power is supplied to the drive unit 20 in the stored state. According to this configuration, no power is required to store and maintain the landing legs 3, which contributes to energy conservation.

[0068] In the above embodiment, the lever 30 includes the first protrusion 11 and is configured to be rotatable by the driving force of the driving unit 20. According to this configuration, the landing gear 3 can be held / released by rotating the lever 30.

[0069] In the above embodiment, a portion of the lever 30 is formed in a shape that fits along the frame 5 directly above the frame 5 . According to this configuration, the space inside the frame 5 can be secured.

[0070] In the above embodiment, the biasing member 9 is provided to bias the lever 30 so as to maintain the first protrusion 11 and the second protrusion 12 facing each other in the stored state. According to this configuration, no power is required to store and maintain the landing legs 3, which contributes to energy conservation.

[0071] In the above embodiment, the limit switch 40 is provided to detect the movement of the lever 30. A part of the limit switch 40 is formed in a shape that fits along the frame 5. According to this configuration, the movement of the lever 30 can be detected by the limit switch 40. In addition, the space inside the frame 5 can be secured.

[0072] In the above embodiment, the lever 30 includes the first arm 31 provided with the first protrusion 11 and the second arm 32 provided so as to be able to come into contact with the limit switch 40. With this configuration, the lever 30 can have two functions (the first arm 31 has the function of holding / releasing the landing gear 3 in storage, and the second arm 32 has the function of activating the limit switch 40). Therefore, no separate part is required to activate the limit switch 40. This makes it possible to achieve a simpler configuration.

[0073] In the above embodiment, the detecting unit 50 that detects the current value of the driving unit 20 and the determining unit 51 that determines the driving state of the driving unit 20 based on the detection result of the detecting unit 50 are provided. According to this configuration, the driving state of the driving unit 20 can be grasped.

[0074] In the above embodiment, the determination unit 51 determines the driving state of the driving unit 20 based on the detection result of the limit switch 40 and the detection result of the detection unit 50. According to this configuration, the drive state of the drive unit 20 can be determined based on two conditions (that the limit switch 40 detects the operation of the lever 30, and that the detector 50 detects the current value of the drive unit 20). Therefore, redundancy can be provided.

[0075] In the above embodiment, the driving unit 20 is configured as a solenoid. According to this configuration, the power and control load can be reduced compared to when the drive unit 20 is configured with an electric motor (for example, a servo motor or the like).

[0076] <Modification> In the above embodiment, the first protrusion is described as being rotatable about a predetermined axis, but this is not limiting. For example, the first protrusion may be capable of linear movement (e.g., vertical stroke). The manner in which the first protrusion moves can be changed according to design specifications.

[0077] In the above embodiment, an example has been described in which the first protrusion rotates around a predetermined axis to release the opposing relationship between the first protrusion and the second protrusion, but this is not limiting. For example, the first protrusion may move linearly (e.g., stroke up and down) to release the opposing relationship between the first protrusion and the second protrusion. The manner in which the opposing relationship between the first protrusion and the second protrusion is released can be changed according to design specifications.

[0078] In the above embodiment, the first protrusion and the second protrusion overlap each other when viewed along the predetermined axis in the stored state, but this is not limited to this. For example, the first protrusion and the second protrusion do not have to overlap each other when viewed along the predetermined axis in the stored state (they may be offset). The arrangement of the first protrusion and the second protrusion in the stored state can be changed according to design specifications.

[0079] In the above embodiment, an example was described in which a frame is provided on the outer side of the aircraft body, and the first and second protrusions face each other on the outer side of the frame relative to the aircraft body in the retracted state, but this is not limited to this. For example, the first and second protrusions may face each other on the inner side of the frame relative to the aircraft body in the retracted state. The arrangement of the first and second protrusions relative to the frame can be changed depending on the design specifications.

[0080] In the above embodiment, an example was described in which the drive unit for driving the first protrusion is provided directly above the frame, but this is not limited to this. For example, the drive unit for driving the first protrusion may be provided on the side of the frame. The manner in which the drive unit is installed relative to the frame can be changed depending on the design specifications.

[0081] In the above embodiment, an example has been described in which power is not supplied to the drive unit in the stored state, but this is not limiting. For example, power may be supplied to the drive unit in the stored state. The manner in which power is supplied to the drive unit can be changed according to design specifications.

[0082] In the above embodiment, an example was described in which a lever including a first protrusion and configured to be rotatable by the driving force of a driving unit was provided, but this is not limited thereto. For example, the first protrusion may be provided on a member separate from the lever. The configuration of the lever can be changed according to design specifications.

[0083] In the above embodiment, an example has been described in which a portion of the lever is formed directly above the frame and conforms to the frame, but this is not limiting. For example, the entire lever may be disposed to the side of the frame. The arrangement and / or shape of the lever relative to the frame can be changed according to design specifications.

[0084] In the above embodiment, an example was described in which a biasing member was provided that biases the lever to maintain the opposing relationship between the first and second protrusions in the stored state, but this is not limited thereto. For example, the biasing member may bias the lever to release the opposing relationship between the first and second protrusions in the stored state. In this case, a pressing member (separate from the biasing member) may be provided that presses the lever to maintain the opposing relationship between the first and second protrusions in the stored state, or the opposing relationship between the first and second protrusions may be maintained by the driving force of the driving unit. The installation manner of the biasing member and / or the manner in which the opposing relationship between the first and second protrusions in the stored state is maintained can be changed according to design specifications.

[0085] In the above embodiment, an example has been described in which a limit switch is provided to detect the movement of a lever, and a portion of the limit switch is formed in a shape that conforms to the frame, but this is not limited to this. For example, a sensor that detects the movement of the lever may be provided. The installation mode and / or shape of the limit switch relative to the frame can be changed according to design specifications.

[0086] In the above embodiment, the lever is described as including a first arm provided with a first protrusion and a second arm provided so as to be able to contact the limit switch, but this is not limiting. For example, two types of levers (a first lever having a function of holding / releasing the landing gear retraction and a second lever having a function of activating the limit switch) may be provided. For example, a separate part for activating the limit switch may be provided. The configuration of the lever can be changed according to design specifications.

[0087] In the above embodiment, an example has been described in which a detector detects the current value of the drive unit and a determiner determines the drive state of the drive unit based on the detection result of the detector, but this is not limiting. For example, a sensor may be provided that detects the operation of a plunger of the drive unit (solenoid). The installation manner of the detector and / or determiner can be changed according to design specifications.

[0088] In the above embodiment, the determination unit determines the drive state of the drive unit based on the detection results of the limit switch and the detection unit, but this is not limiting. For example, the drive state of the drive unit may be determined based on one condition (either that the limit switch detects the movement of the lever or that the detection unit detects the current value of the drive unit). The manner in which the drive state of the drive unit is determined may be changed depending on the design specifications.

[0089] In the above embodiment, the driving unit is configured as a solenoid, but this is not limiting. For example, the driving unit may be configured as an electric motor (e.g., a servo motor). The configuration of the driving unit can be changed according to the design specifications.

[0090] In the above embodiment, the determination unit is described as constituting a control device, but this is not limiting. For example, a program for implementing some or all of the functions of the control device may be recorded on a computer-readable recording medium, and the program may be loaded into a computer system and executed to perform all or part of the processing performed by the control device. Note that the term "computer system" as used herein includes hardware such as an OS and peripheral devices. The term "computer system" also includes a WWW system equipped with a web page provision environment (or display environment). The term "computer-readable recording medium" refers to portable media such as floppy disks, optical magnetic disks, ROMs, and CD-ROMs, as well as storage devices such as hard disks built into a computer system. Furthermore, the term "computer-readable recording medium" also includes devices that retain a program for a certain period of time, such as volatile memory (RAM) within a computer system that acts as a server or client when the program is transmitted via a network such as the Internet or a communication line such as a telephone line.

[0091] The program may also be transmitted from a computer system storing the program in a storage device or the like to another computer system via a transmission medium or by transmission waves in the transmission medium. Here, the "transmission medium" that transmits the program refers to a medium that has the function of transmitting information, such as a network (communication network) such as the Internet or a communication line (communication line) such as a telephone line. The program may also be a program that realizes part of the above-mentioned functions. Furthermore, the program may be a so-called differential file (differential program) that can realize the above-mentioned functions in combination with a program already recorded in the computer system.

[0092] The above describes preferred embodiments of the present invention, but the present invention is not limited to these, and additions, omissions, substitutions, and other modifications to the configuration are possible within the scope of the spirit of the present invention, and the above-mentioned modifications can also be combined as appropriate. [Explanation of symbols]

[0093] 1. Aircraft 2. Aircraft body 3 landing gear 5 frames 9. Pressurizing member 11 1st protrusion 12 Second protrusion 20 Drive unit 30 Lever 31 First Arm 32 Second Arm 33 Insertion part 40 Limit Switch 50 Detection unit 51 Judgment section A given axis

Claims

1. The aircraft body; a landing gear configured to be capable of transitioning between a stored state in which the landing gear is stored at a position along the aircraft body and a deployed state in which the landing gear is deployed at a position away from the aircraft body; the aircraft body includes a first protrusion protruding from a portion of the aircraft body; the landing leg includes a second protrusion protruding from a portion of the landing leg; the first protrusion and the second protrusion face each other in a direction away from the aircraft body in the stored state; Flying vehicle.

2. The first protrusion is rotatable about a predetermined axis. The flying vehicle according to claim 1 .

3. The first protrusion rotates around the predetermined axis, thereby releasing the opposing relationship between the first protrusion and the second protrusion. The flying vehicle according to claim 2.

4. the first protrusion and the second protrusion overlap each other when viewed from a direction along the predetermined axis in the stored state; 4. The flying vehicle according to claim 2 or 3.

5. a frame provided on the outer side of the aircraft body; the first protrusion and the second protrusion face each other on the outer side of the frame with respect to the aircraft body in the stored state; 4. The flying vehicle according to claim 1 .

6. a drive unit that drives the first protrusion is provided directly above the frame; The flying vehicle according to claim 5.

7. In the stored state, no power is supplied to the drive unit. The flying vehicle according to claim 6.

8. a lever including the first protrusion and configured to be rotatable by the driving force of the driving unit; The flying vehicle according to claim 6.

9. a portion of the lever is formed in a shape that follows the frame directly above the frame; The flying vehicle according to claim 8.

10. a biasing member that biases the lever so as to maintain the first protrusion and the second protrusion facing each other in the stored state; The flying vehicle according to claim 8.

11. a limit switch that detects the movement of the lever; A part of the limit switch is formed into a shape that fits along the frame. The flying vehicle according to claim 8.

12. The lever includes a first arm on which the first protrusion is provided and a second arm provided so as to be able to come into contact with the limit switch. The flying vehicle according to claim 11.

13. a detection unit that detects a current value of the drive unit; a determination unit that determines the drive state of the drive unit based on the detection result of the detection unit, The flying vehicle according to claim 11.

14. The determination unit determines the drive state of the drive unit based on each of the detection result of the limit switch and the detection result of the detection unit. The flying vehicle according to claim 13.

15. The drive unit is composed of a solenoid. The flying vehicle according to claim 6.

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