JP2017132420A - Machine mounted with horizontal/vertical flyable aircraft, and machine-outside developing and machine-inside pulling-in device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a machine mounted with a horizontal/vertical flyable aircraft and a machine-outside developing and machine-onside pulling-in device, capable of easy mounting and removal in/from a body inner space without great rectification.SOLUTION: This device is provided with; a detachable container 20 that is detachable fixed to the inner surface of the cargo chamber CR of an aircraft and mounted in the cargo chamber of the aircraft; a movement structure unit 42 that includes one end 40 detachably attached to an external used machine 30 and that is attache to the container and capable of moving, together with the machine, one end between the position of pulling-in and the position of exposure to the outside of a body in a horizontal direction via the opening CO of the cargo chamber of the aircraft; and a driving unit 44a that is attached to the container and that selectively drives the movement structure unit to selectively move one end of the movement structure unit between the pulling-in position and the exposure unit.SELECTED DRAWING: Figure 8

Description

  The present invention relates to a horizontally / vertically flightable aircraft-mounted equipment, deployment outside the aircraft, and equipment that can be deployed outside the fuselage and can be pulled out of the fuselage as needed. Related to the retractor.

  Horizontal and vertical flightable aircraft includes, for example, aircraft that can move a helicopter, propeller shaft between a horizontal direction and a vertical direction.

  Conventionally, various equipment used outside the helicopter fuselage during the flight of a helicopter as an example of an aircraft capable of horizontal and vertical flight is exposed to the outside of the helicopter fuselage via a dedicated or general-purpose attachment. Yes. The various equipment can include, for example, at least one of a hoist, a sample collector, a measuring instrument, an observation device, a camera, an acoustic device, a lighting fixture, an antenna, a firearm, a missile, and the like. Also good. The attachment is made by modifying a part of the fuselage of the helicopter.

  In order to use such a conventional mounting tool, it is necessary to modify a part of the helicopter fuselage, but the modification work is complicated and the modification cost is high. Moreover, the attachment can only be used with a helicopter that has been partially modified to use the attachment.

  Various types of equipment that are exposed and attached to the outside of the helicopter fuselage, as well as the fittings that are exposed and attached to the outside of the helicopter fuselage, Increases air resistance and reduces helicopter range as well as helicopter flight speed. Furthermore, since various equipments are exposed to the outside of the helicopter fuselage when not in use, the possibility of failure increases.

  In order to eliminate the above-mentioned various disadvantages of the conventional externally exposed fixture, the equipment mounted on the fuselage of a horizontal and vertical flightable aircraft represented by a helicopter is deployed outside the fuselage as necessary. Japanese Patent Application Laid-Open No. 5-42897 (Patent Document 1), Japanese Patent No. 5543143 (Patent Document) 2), Japanese Patent No. 2593127 (Patent Document 3), and Japanese Patent Application Laid-Open No. 7-47999 (Patent Document 4).

  In the helicopter described in Japanese Patent Application Laid-Open No. 5-42897 (Patent Document 1), a rail is provided on a hoist column fixed to the fuselage so as to protrude from the inside of the fuselage to the outside. It can move between the inside and outside of the body. Alternatively, the hoist strut is installed on the fuselage so that it can move between the position retracted inside the fuselage and the position protruding outward, and the hoist supported by the hoist strut is retracted inside the fuselage together with the hoist strut And a position protruding outward.

  In an aircraft that can move the helicopter or propeller shaft described in Japanese Patent No. 5543143 (Patent Document 2) between the horizontal and vertical directions, the fuselage door of the fuselage is split up and down and released. The hoist is provided inside the upper door portion. The hoist is stored in the fuselage while the upper door portion is closed, and the hoist is exposed outside the fuselage while the upper door portion is opened upward.

  In the helicopter described in Japanese Patent No. 2593127 (Patent Document 3), a link mechanism is attached to the rear cargo compartment of the fuselage, and the camera device is moved between the inside and outside of the rear cargo compartment by the link mechanism. It can be made.

  In the helicopter described in Japanese Patent Application Laid-Open No. 7-47999 (Patent Document 4), it extends backward from the upper part of the rear end of the main part of the fuselage to which the main rotor is attached to support the tail rotor and the horizontal tail. A rail is provided on the lower surface of the tail (pylon), along which the gondola can move between the inside and outside of the main part of the fuselage.

Japanese Patent Laid-Open No. 5-42897 Japanese Patent No. 5543143 Japanese Patent No. 2593127 Japanese Unexamined Patent Publication No. 7-47999

  In the helicopter described in Patent Document 1, it is necessary to significantly modify the fuselage in order to fix the hoist strut to the fuselage or movably install it, and much cost and time are required for the modification. In addition, the work of removing the hoist column once fixed or installed on the fuselage from the fuselage is complicated and requires a lot of cost and time. And the fittings can still only be used with helicopters that have been partially modified to use the fittings.

  In the helicopter or aircraft described in Patent Document 2, the upper door portion must be made to have high strength. In addition, the cargo door must be structured such that the door of the cargo compartment is divided into upper and lower parts and released.

  In the helicopter described in Patent Literature 3, since the camera device moved to the outside of the rear cargo compartment by the link mechanism is located below the fuselage, it is difficult to land the helicopter in a state where the camera device is moved to the outside. However, the maintenance of the camera device and the detaching operation of the camera device with respect to the link mechanism are complicated.

  In the helicopter described in Patent Document 4, in order to provide the rail supporting the gondola on the lower surface of the tail (pylon), the tail needs to be significantly modified, and much cost and time are required for the modification. In addition, the work of removing the hoist column once fixed or installed on the fuselage from the fuselage is complicated and requires a lot of cost and time. Furthermore, the above modification can be made only to a helicopter having a fuselage with a tail (pylon) extending rearward from the upper part of the rear end of the main part of the fuselage.

  The present invention has been made under the circumstances described above, and the object of the present invention is a special or large remodeling that spends a lot of time and money on horizontal and vertical flightable aircraft, regardless of the shape of the doors and fuselage of the horizontal and vertical flightable aircraft. Can be easily mounted in and removed from the space inside the fuselage, and various devices that are used by being exposed outside the fuselage can be exposed to the outside. However, it is to provide a horizontal / vertical flightable aircraft-equipped aircraft, out-of-flight deployment, and in-flight pull-in device that enables landing of an aircraft capable of horizontal and vertical flight.

In order to achieve the above object, the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retractor according to the present invention are:
A detachable fixing structure that is always provided on the inner surface of the luggage compartment in the fuselage to detachably fix the equipment or luggage, and a cargo compartment opening that opens the inside of the cargo compartment to the outside of the fuselage in the horizontal direction. Horizontal and vertical flightable aircraft-equipped equipment, out-of-flight deployment and in-flight retractor used in horizontal and vertical flightable aircraft including:
A detachable container that is detachably fixed to the inner surface of the cargo compartment of the horizontal and vertical flightable aircraft by the detachable fixing structure and is mounted in the cargo compartment;
The aircraft includes an end portion to which externally used equipment is detachably attached, is attached to the detachable container, and the one end portion is drawn into the cargo compartment together with the externally used equipment, and the horizontal and vertical flightable aircraft A movable structure unit capable of moving between an exposed position exposed to the outside of the body in the horizontal direction through the cargo compartment opening;
A drive unit attached to the removable container for selectively driving the moving structure unit and selectively moving the one end of the moving structure unit between the retracted position and the exposed position;
It is characterized by having.

  According to the concept of the present invention, the inner surface of the luggage compartment includes a floor surface, a wall surface, and a ceiling.

  The horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retracting device according to the present invention, which is configured as described above, has a load in the fuselage in order to removably fix equipment or luggage. It is used in a horizontal and vertical flightable aircraft including a detachable fixing structure that is always provided on the inner surface of the chamber and a cargo chamber opening that opens the inside of the cargo compartment to the outside of the fuselage in the horizontal direction. The removable container to which the moving structure unit and the drive unit are attached is detachably fixed by a detachable fixing structure that is always provided on the inner surface of the cargo compartment in the fuselage of the aircraft capable of horizontal and vertical flight. Mounted in the cargo compartment.

  Therefore, a removable container with a mobile structure unit and a drive unit attached to a special vehicle that spends a lot of time and money on a horizontal and vertical flightable aircraft, regardless of the shape of the door or fuselage of the horizontal and vertical flightable aircraft. Alternatively, it can be easily mounted in and removed from the space in the body without requiring major modifications. This allows the detachable container to be easily mounted and removed from the space of an unmodified horizontal and vertical flightable aircraft.

  The moving structure unit attached to the detachable container includes a pull-in position where one end portion to which externally used equipment is detachably attached is drawn together with the externally used equipment into the cargo compartment, and the cargo compartment of the horizontally and vertically flightable aircraft. Since it can be moved between the exposure position exposed to the outside of the body in the horizontal direction through the opening, various devices used by being exposed to the outside of the body are horizontally exposed to the outside. Allows landing of vertically flyable aircraft.

FIG. 1 shows a fuselage of a helicopter which is an example of a horizontal / vertical flightable aircraft equipped with a detachable container for a horizontal / vertical flightable aircraft-equipped equipment / outboard deployment and in-flight retractor according to the first embodiment of the present invention. It is a schematic top view which cuts and shows the roof of a luggage compartment in order to show the detachable structure of the main luggage compartment. FIG. 2 is a schematic longitudinal sectional view of a part of the luggage compartment and a part of the detachable container fixed to the luggage compartment by a detachable structure along the line II-II in FIG. 1. FIG. 3 shows a fuselage of a helicopter which is an example of a horizontal / vertical flightable aircraft equipped with a detachable container for horizontal / vertical flightable aircraft-equipped equipment / outboard deployment and in-flight retractor according to the second embodiment of the present invention. It is a schematic top view which cuts and shows the roof of a luggage compartment in order to show the detachable structure of the main luggage compartment. 4A shows a part of the luggage compartment along the line IV (A) -IV (A) in FIG. 3 and a part of the removable container fixed to the luggage compartment by a removable structure. It is a schematic longitudinal cross-sectional view; (B) is a figure which shows schematically in the state which decomposed | disassembled the modification of the detachable structure of FIG. 3 and (A); (C) is a deformation | transformation of (B) It is a figure which shows roughly in the state which assembled the example. FIG. 5 is a view of a helicopter fuselage which is an example of a horizontal / vertical flightable aircraft equipped with a detachable container for horizontal and vertical flightable aircraft-equipped equipment / outboard deployment and in-flight retractor according to the third embodiment of the present invention. It is a schematic top view which cuts and shows the roof of a luggage compartment in order to show the detachable structure of the main luggage compartment. FIG. 6 is a schematic longitudinal sectional view of a part of the luggage compartment and a part of the detachable container fixed to the luggage compartment by a detachable structure along the line VI-VI in FIG. 5. FIG. 7 is a drawing showing the moving structure unit in the retracted position and the exposed position in the first example of the configuration common to the horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to the first to third embodiments of the present invention. It is the schematic plan view which looked at the state which exists in the upper surface. FIG. 8 is a schematic side view of the configuration of FIG. FIG. 9A shows a second example of a configuration common to the horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retractor according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 10 (A) shows the moving structure unit exposed in the second example of the configuration common to the horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retractor according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 11A shows a third example of a configuration common to the horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 12 (A) shows the moving structure unit exposed in a third example of a configuration common to horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retractor according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 13A shows the fourth example of the configuration common to the horizontal / vertical flightable aircraft mounted equipment / external deployment and in-flight retractor according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 14 (A) shows a moving structure unit exposed in a fourth example having a configuration common to horizontally mounted aircraft capable of horizontal and vertical flight, deployment outside the aircraft, and in-flight retractor according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 15A shows a fifth example of a structure common to the horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A). FIG. 16 (A) shows the moving structure unit exposed in the fifth example of the configuration common to the horizontal / vertical flightable aircraft mounted equipment / external deployment and in-flight retractor according to the first to third embodiments of the present invention. It is a figure which shows roughly the right half which looked at the state in a position from the front; (B) is a schematic top view of (A).

[First Embodiment]
Referring to FIG. 1 and FIG. 2, a helicopter which is an example of a horizontal / vertical flightable aircraft to which a horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting device 10 according to the first embodiment of the present invention is attached. The detachable fixing structure 14 for the cargo compartment CR of the main body 12a of the 12 trunks will be described.

  However, in accordance with the inventive concept, the horizontal and vertical flightable aircraft may be an aircraft capable of flying in the horizontal and vertical directions by moving the propeller shaft between the horizontal and vertical directions.

  This helicopter 12 is a so-called general-purpose helicopter that does not have a structure for a special purpose. The fuselage of this helicopter 12 is located at the main part 12a where the cargo compartment CR is provided, the front part 12b which is located in front of the main part 12a and where the cockpit is provided, and behind the main part 12a. And a rear portion 12c in which a horizontal tail HS and a tail rotor TR are provided at the rear end. The roof of the main body 12a of the fuselage is provided with a main engine (not shown) and a main rotor (not shown) rotated by the main engine and operated from the cockpit. In FIG. 1, the roof of the main body 12a of the fuselage is cut away to show the cargo compartment CR.

  A pair of cargo compartment openings CO that open the inside of the cargo compartment CR to the outside of the fuselage are provided on both side surfaces of the main body 12a in the horizontal direction. The fuselage further includes a pair of doors 12d movable between a closed position that closes each of the pair of cargo compartment openings CO and an open position that opens each of the pair of cargo compartment openings CO. .

  In this embodiment, the main body 12a of the fuselage is provided with a pair of cargo compartment openings CO. However, according to the concept of the present invention, the outer wall of the main portion 12a of the fuselage is horizontally outside the cargo compartment CR in the horizontal direction. It is sufficient if there is at least one luggage compartment opening to be opened. In this case, the luggage compartment opening opens at least one of the horizontal side surface, the other side surface, or the rear surface inside the cargo space CR. There may be at least one door 12d corresponding to at least one cargo compartment opening.

  Each of the pair of doors 12d is attached to the main body 12a of the trunk so as to be slidable in the front-rear direction of the trunk between the closed position and the open position along both side surfaces of the main section 12a. However, according to the concept of the present invention, the door 12d may be movable from the closed position to the open position by being divided in the vertical direction.

  The detachable fixing structure 14 is always provided on the inner surface of the cargo compartment CR of the fuselage in order to fix the equipment or the load easily and detachably. In this embodiment, the detachable fixing structure 14 includes a fixing hole 14a formed at a plurality of predetermined positions on the inner surface, a fixing member 14b that is detachably fixed to the fixing hole 14a, and a fixing bolt in this embodiment. The fixing hole 14a and the fixing member 14b of the floor surface FL, which are part of the inner surface, are used. According to the concept of the present invention, the fixing member 14b can be a screw or a metal fitting used for fixing a leg of a seat in a normal horizontal and vertical flightable aircraft in addition to the fixing bolt described above.

  The horizontal and vertical flightable aircraft-mounted equipment / external deployment and in-flight retractor 10 of this embodiment is placed in the cargo compartment CR of the helicopter 12 while moving at least one of the pair of doors 12d of the helicopter 12 to the open position. A detachable container 20 that can be mounted and removed from the cargo compartment CR is provided. The detachable container 20 can be detachably fixed at the predetermined position by the detachable fixing structure 14 of the helicopter 12 when mounted at a predetermined position in the cargo compartment CR. The detachable container 20 of this embodiment includes a frame body having an outer dimension that can be easily mounted in the cargo compartment CR of the helicopter 12, and the floor surface of the cargo compartment CR when mounted at a predetermined position in the cargo compartment CR. A floor member 20b in which fixing holes 20a corresponding to at least some of the plurality of fixing holes 14a of the FL are formed is fixed to the lower frame of the frame body.

  The detachable container 20 is mounted at a predetermined position in the cargo compartment CR of the helicopter 12 so that several fixing holes 20a of the floor member 20b are matched with some corresponding fixing holes 14a of the floor surface FL of the cargo compartment CR. After that, as shown in FIG. 2, the fixing member 14b is inserted into the fixing hole 20a and fixed to the corresponding fixing hole 14a, so that it can be fixed at a predetermined position in the cargo compartment CR. Further, by removing the fixing member 14b from some corresponding fixing holes 14a of the floor surface FL of the cargo compartment CR and several fixing holes 20a of the floor member 20b, the detachable container 20 is placed in the cargo compartment CR of the helicopter 12. It is possible to move from the predetermined position to the outside of the luggage compartment CR.

  According to the concept of the present invention, the detachable container 20 used in the horizontal and vertical flightable aircraft-equipped aircraft / outboard deployment and inboard retractor 10 of the first embodiment can be easily mounted in the cargo compartment CR of the helicopter 12. Floor member 20b having a fixed outer shape and formed with fixing holes 20a corresponding to at least some of the plurality of fixing holes 14a on the floor surface FL of the loading chamber CR when mounted at a predetermined position in the loading chamber CR. Can only consist of.

  According to the concept of the present invention, the plurality of fixing holes 14a are formed in the wall surface of the cargo compartment CR, and the removable container 20 is fixed to one or more of the plurality of fixing holes 14a in the wall surface of the cargo compartment CR. If the hole 20a is formed, the detachable container 20 can be detachably fixed to the wall surface by using the fixing member 14b.

  Furthermore, according to the concept of the present invention, a plurality of fixing holes 14a are formed in the ceiling of the cargo compartment CR, and the removable container 20 corresponds to one of the plurality of fixing holes 14a in the ceiling of the cargo compartment CR. If the fixing hole 20a is formed, the detachable container 20 can be detachably fixed to the ceiling by using the fixing member 14b.

[Second Embodiment]
Referring to FIG. 3 and FIG. 4A, a horizontal / vertical flightable aircraft equipped with a horizontal / vertical flightable aircraft-equipped equipment / external deployment and in-flight retractor 10 ′ according to the second embodiment of the present invention. The detachable fixing structure 14 'for the cargo compartment CR of the main part 12a of the fuselage of the helicopter 12 as an example will be described.

  The structure of this helicopter 12 is the horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting device 10 according to the first embodiment described above with reference to FIGS. 1 and 2 except for the detachable fixing structure 14 '. Is the same as the structure of the helicopter 12 which is an example of a horizontally and vertically flightable aircraft to which is attached. The structure other than the detachable fixing structure 14 'includes the structure of the helicopter 12 described above with reference to FIGS. Corresponding structures are denoted by the same reference numerals and detailed description thereof is omitted.

  The detachable fixing structure 14 'is always provided to fix the equipment or the load easily and detachably on the inner surface of the cargo compartment CR of the fuselage. In this embodiment, the detachable fixing structure 14 'includes a plurality of fixed rails 14'R fixed to a plurality of predetermined positions on the floor surface FL which is a part of the inner surface. Each of the plurality of fixed rails 14′R extends in the longitudinal direction of the fuselage, that is, the direction along the longitudinal axis of the fuselage, and the plurality of fixed rails 14′R is fixed to the floor surface FL of the cargo compartment CR. use. Each of the plurality of fixed rails 14'R has an engagement hole EG extending in the longitudinal direction inside thereof, and each engagement hole EG is open at both ends in the longitudinal direction. . Each engagement hole is provided with a slit SL opened on the upper surface of each fixed rail 14'R. Similarly to the fixed rail 14'R, the slit SL also extends in the longitudinal direction and opens at both ends in the longitudinal direction.

  The detachable fixing structure 14 'includes a plurality of inverted T-shaped fixing members 14'S inserted into at least some of the engagement holes EG and the slits SL of the plurality of fixing rails 14'R. The fixing member 14'S can move in the width direction along the engagement hole EG, but can move upward and downward from the engagement hole EG by engaging the ceiling and bottom of the engagement hole EG. I can't. In the fixing member 14 ′S, the upper protruding portion 14′U inserted into the engagement hole EG and the slit SL has a thread groove formed on the outer peripheral surface and is a male screw. The fixing member 14'S can be a headed bolt.

  In this embodiment, the horizontal and vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting device 10 ′ moves the cargo compartment CR of the helicopter 12 while moving at least one of the pair of doors 12d of the helicopter 12 to the open position. On the other hand, a detachable container 20 ′ that can be mounted and removed from the cargo compartment CR is provided. The detachable container 20 ′ can be detachably fixed at the predetermined position by the detachable fixing structure 14 ′ of the helicopter 12 when mounted in the predetermined position of the cargo compartment CR. The detachable container 20 ′ of this embodiment includes a frame having an outer dimension that can be easily mounted in the cargo compartment CR of the helicopter 12, and the floor of the cargo compartment CR when mounted at a predetermined position in the cargo compartment CR. A floor member 20'b in which fixing holes 20'a corresponding to at least some of the plurality of fixing rails 14'R on the surface FL are formed is fixed to the lower frame of the frame body.

  In this embodiment, the detachable container 20 ′ of the horizontal / vertical flightable aircraft-equipped equipment / external deployment and in-flight retractor 10 ′ has only the configuration of the floor member 20′b, and the horizontal configuration of the first embodiment of FIGS. The vertical flightable aircraft-mounted equipment / external deployment and in-flight pull-in device 10 has a different configuration from the floor member 20b of the removable container 20, and the other configuration is the same as the removable container 20.

  The detachable container 20 ′ is mounted at a predetermined position in the cargo compartment CR of the helicopter 12, and several corresponding fixings of the floor surface FL of the cargo compartment CR are installed in several fixing holes 20′a of the floor member 20′b. After inserting the upper protruding portions 14′U of the plurality of fixing members 14 ′S of the rail 14′R, another fixing member that can be attached to and detached from the upper protruding portion 14′U, in this embodiment, a nut is fixed. Thus, as shown in FIG. 4, it can be fixed at a predetermined position in the cargo compartment CR. Further, another fixing member that can be detached from the upper protruding portions 14'U of the plurality of fixing members 14'S of the corresponding fixing rails 14'R of the floor surface FL of the cargo compartment CR, in this embodiment, a nut , And removing some of the fixing holes 20'a of the floor member 20'b from the upper protruding portions 14'U of the plurality of fixing members 14'S of the corresponding fixing rail 14'R. Can be moved from a predetermined position in the cargo compartment CR of the helicopter 12 to the outside of the cargo compartment CR.

  According to the concept of the present invention, the detachable container 20 ′ used in the horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device 10 ′ of the second embodiment is also easily installed in the cargo compartment CR of the helicopter 12. The upper projecting portions 14 of the plurality of fixing members 14'S of the corresponding fixing rail 14'R of the floor surface FL of the cargo compartment CR when mounted at a predetermined position in the cargo compartment CR. The floor member 20'b can be configured only with the fixing holes 20'a corresponding to at least some of 'U.

  According to the concept of the present invention, the fixed rail 14'R may extend in the width direction of the fuselage, that is, the direction along the vertical axis and the vertical axis of the fuselage.

  4B schematically shows a modified example of the fixed rail 14′R and the fixed member 14 ′S shown in FIGS. 3 and 4A in an exploded state. . The slits SLM of the fixed rail 14′RM of this modification are formed with wide portions having the same shape at predetermined intervals along the extending direction. Inside the fixed rail 14'RM, there is formed an engagement hole EGM that communicates with the slit SLM and is wider than the slit SLM and extends in the longitudinal direction. The fixing member 14′P has the same length as that between two continuous widened portions of the slit SLM and has the same width as the slit SLM, and the widened width provided at both ends of the central portion in the longitudinal direction. And an enlarged portion corresponding to the portion, and a stud bolt 14'W supported so as to be directed upward in the vertical direction at the center portion.

FIG. 4C schematically shows the slit SLM of the fixed rail 14′RM of the modification of FIG. 4B assembled.
When the detachable container 20 ′ is mounted at a predetermined position in the cargo compartment CR, stud bolts are positioned at positions corresponding to several fixing holes 20′a of the floor member 20′b of the detachable container 20 ′ at the predetermined position. After the two enlarged portions at both ends of the fixing member 14'P are pushed into two continuous widened portions in the slit SLM of the fixing rail 14'RM so that the 14'W is disposed, the fixing member 14'P is engaged. In the hole EGM, it is moved along the longitudinal direction by a half length between two continuous widened portions of the slit SLM. As a result, as shown in FIG. 4C, the two enlarged portions at both ends of the fixing member 14′P are vertically engaged with the engagement hole EGM between two continuous widened portions in the slit SLM. The stud bolts 14'W are engaged and disposed between two consecutive widened portions in the slit SLM. Thereafter, the retainer 14'F is attached to the base of the upward projecting portion that projects upward from the slit SLM in the stud bolt 14'W, so that the retainer 14'F is accommodated in the widened portion corresponding to the stud bolt 14'W. To be flush with the upper surface of the fixed rail 14'RM. The retainer 14'F accommodated in the widened portion engages with the widened portion in the longitudinal direction of the fixed rail 14'RM and fixes the position of the fixing member 14'P in the longitudinal direction.

  Further, some fixed holes 20'a of the floor member 20'b of the removable container 20 'mounted at a predetermined position in the cargo compartment CR of the helicopter 12 correspond to some of the floor surface FL of the cargo compartment CR. After inserting the upper protruding portions of the stud bolts 14′W of the plurality of fixing members 14′P of the fixed rail 14′RM, the upper protruding portions can be attached and detached as shown in FIG. By fixing another fixing member, in this embodiment, a nut, the detachable container 20 ′ is fixed at a predetermined position in the cargo compartment CR in the same manner as shown in FIG. It can be made. Further, another fixing member detachable from the upper projecting portion of the stud bolt 14'W of the plurality of fixing members 14'P of the corresponding fixing rails 14'R of the floor surface FL of the cargo compartment CR, this implementation In the form, the nut is removed, and several fixing holes 20'a of the floor member 20'b are extracted from the upper protruding portions of the stud bolts 14'W of the plurality of fixing members 14'P of the corresponding fixing rail 14'RM. Thus, the removable container 20 ′ can be moved from a predetermined position in the cargo compartment CR of the helicopter 12 to the outside of the cargo compartment CR.

  According to the concept of the present invention, a plurality of fixed rails 14'R or 14'RM are fixed to the wall surface of the cargo compartment CR, and a plurality of fixed rails 14'R on the wall surface of the cargo compartment CR are attached to the removable container 20 '. Alternatively, if a fixing hole 20′a corresponding to at least one of the upper protruding portion 14′U of the fixing member 14 ′S of the 14′RM or the upper protruding portion of the stud bolt 14′W is formed, the fixing member 14 By using 'S or stud bolt 14'W, removable container 20' can be detachably fixed to the wall surface.

  Furthermore, according to the concept of the present invention, a plurality of fixed rails 14'R or 14'RM are fixed to the ceiling of the cargo compartment CR, and a plurality of fixed rails 14 'on the ceiling of the cargo compartment CR are attached to the removable container 20'. If the fixing hole 20'a corresponding to at least one of the upper protruding portion 14'U of the fixing member 14'S of R or 14'RM or the upper protruding portion of the stud bolt 14'W is formed, the fixing member By using the 14 ′S or the stud bolt 14′W, the detachable container 20 ′ can be detachably fixed to the ceiling.

[Third Embodiment]
With reference to FIG. 5 and FIG. 6, an example of a horizontal / vertical flightable aircraft to which a horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retractor 10 ″ according to the third embodiment of the present invention is attached. The detachable fixing structure 14 ″ of the cargo compartment CR of the main part 12a of the fuselage of a certain helicopter 12 will be described.

  The structure of this helicopter 12 is the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retracting device according to the first embodiment described above with reference to FIGS. 1 and 2 except for the detachable fixing structure 14 ″. 10 is the same as the structure of the helicopter 12 which is an example of a horizontally and vertically flightable aircraft to which the aircraft 10 is attached. The structure of the helicopter 12 described above with reference to FIG. 1 and FIG. The same reference numerals are assigned to the structures corresponding to the structures, and detailed description is omitted.

  The detachable fixing structure 14 ″ is always provided to fix the equipment or the load easily and detachably on the inner surface of the cargo compartment CR of the fuselage. In this embodiment, the detachable fixing structure 14 ″ includes a plurality of ring-shaped fixing members 14 ″ L fixed to a plurality of predetermined positions on the inner surface.

  The horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retractor 10 ″ according to this embodiment has a cargo compartment of the helicopter 12 while moving at least one of the pair of doors 12d of the helicopter 12 to the open position. A detachable container 20 ″ that can be mounted on the CR and removed from the cargo compartment CR is provided. The detachable container 20 ″ can be detachably fixed at the predetermined position by the detachable fixing structure 14 ″ of the helicopter 12 when mounted in the predetermined position of the cargo compartment CR. The detachable container 20 ″ of this embodiment includes a frame body having an outer dimension that can be easily mounted in the cargo compartment CR of the helicopter 12.

  In this embodiment, the detachable container 20 ″ of the horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting device 10 ″ has only the configuration of the floor member 20 ″ b, and the first implementation of FIG. 1 and FIG. Horizontal and vertical flightable aircraft-equipped aircraft / configuration of the floor member 20b of the removable container 20 of the in-flight deployment / in-flight retractor 10 and the horizontal / vertical flightable aircraft / equipment / machine of the second embodiment shown in FIGS. Unlike the configuration of the floor member 20'b of the removable container 20 'of the outward deployment and in-machine retracting device 10', the other configurations are the same as those of the two removable containers 20 and 20 'described above.

  The detachable fixing structure 14 ″ is hung on the detachable container 20 ″ mounted at a predetermined position in the cargo compartment CR after the detachable container 20 ″ is mounted at a predetermined position in the cargo compartment CR of the helicopter 12. And fixed to a plurality of fixing members 14 ″ L on the inner surface, and in this embodiment, several corresponding fixing members 14 ″ L on the floor surface FL, which are part of the inner surface of the cargo compartment CR. And a latch member 14 ″ F. The latch member 14 ″ F includes a flexible belt-like or rope-like extending member that includes hooks that are latched to the fixing member 14 ″ L at both ends and a length adjusting mechanism that is not illustrated. . In this case, the detachable container 20 is stretched over the upper surface of the detachable container 20 ″ mounted at a predetermined position in the luggage compartment CR, and the length is adjusted to be shortened by the length adjusting mechanism. ″ Can be held in a predetermined position in the cargo space CR, that is, can be detachably fixed.

  The latch member 14 ″ F is latched to the latchable structure portion of the detachable container 20 ″ mounted at a predetermined position in the cargo compartment CR at one end with a hook latched on the fixing member 14 ″ L. It is also possible to provide a rod-like extending member that is provided with a hook that is provided at the other end and that is provided with a length adjusting mechanism that is not shown. In this case, the hook between one end is hooked on the fixing member 14 ″ L and the hook on the other end is hooked on the hookable structure of the removable container 20 ″, and then the distance between the hooks on both ends is adjusted by the length adjusting mechanism. By adjusting so as to shorten the length, the detachable container 20 ″ can be held at a predetermined position in the cargo compartment CR, that is, detachably fixed.

  Further, the removable container 20 with respect to a predetermined position in the cargo compartment CR can be obtained by increasing the length of the extending member by the length adjusting mechanism or by increasing the length between the hooks at both ends of the rod-shaped extending member. It is possible to release the restraint of ″, that is, release and fix the removable attachment, and the removable container 20 can be moved from a predetermined position in the cargo compartment CR of the helicopter 12 to the outside of the cargo compartment CR.

  According to the concept of the present invention, if a plurality of fixing members 14 ″ L are fixed to the wall surface of the cargo compartment CR, the detachable container 20 ′ is attached to the wall surface by using the latching member 14 ″ F. It can be fixed detachably. Here, the hooking member 14 ″ F is provided with a hook that is hooked on the fixing member 14 ″ L at both ends, and is provided with a length adjusting mechanism (not shown), and is extended in a flexible band or rope shape. If the member is provided, the extending member is stretched over the side surface of the detachable container 20 ″ mounted at a predetermined position in the cargo compartment CR.

  According to the concept of the present invention, if a plurality of fixing members 14 ″ L are fixed to the ceiling of the cargo compartment CR, the detachable container 20 ′ can be placed on the ceiling by using the latching member 14 ″ F. It can be fixed detachably. Here, the hooking member 14 ″ F is provided with a hook that is hooked on the fixing member 14 ″ L at both ends, and is provided with a length adjusting mechanism (not shown), and is extended in a flexible band or rope shape. If the member is provided, the extending member is stretched over the lower surface of the detachable container 20 ″ mounted at a predetermined position in the cargo compartment CR.

[First to Sixth Examples of Configuration Common to Horizontal-Vertical Flightable Equipment / External Deployment and In-flight Retracting Devices 10, 10 ′, and 10 ″ According to First to Third Embodiments]
The horizontal and vertical flightable aircraft-equipped aircraft / in-flight deployment and in-flight retracting devices 10, 10 ′ and 10 ″ according to the first to third embodiments are the three types of detachable fixing structures 14, 14 ′ of the helicopter 12. , 14 ″ of the detachable containers 20, 20 ′, 20 ″ for detachably fixing the detachable containers 20, 20 ′, 20 ″ to a predetermined position in the cargo compartment CR of the helicopter 12 Only the configurations of the floor members 20b, 20′b, 20 ″ b are different, and the other configurations are common. Therefore, in order to avoid the complexity of the description, in the following first to sixth examples, the horizontal and vertical flightable aircraft-mounted equipment / outboard deployment and the removable container 20 of the in-flight retractor 10 according to the first embodiment are used. The case will be described, and the detachable fixing structure 14 is not shown.

First example
Referring to FIGS. 7 and 8, the horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight retracting devices 10, 10 ′, and 10 ″ according to the first to third embodiments are configured in common. An example of the case of the detachable container 20 of the aircraft-mounted equipment / external deployment and in-flight retractor 10 according to the first embodiment will be described.

  FIG. 7 shows a main part 12a of the fuselage of the helicopter 12 of FIG. 1 with the roof omitted and is schematically enlarged, and a floor surface FL which is a part of the inner surface of the cargo compartment CR of the main part 12a. Also shown is a detachable container 20 which is detachably fixed at a predetermined position by a detachable fixing structure 14 (see FIGS. 1 and 2) not shown here. Further, in FIG. 7, the door 12d in the closed position in which the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is closed is indicated by a two-dot chain line, and the door 12d in the open position in which the cargo compartment opening CO is opened is indicated by a solid line. ing.

  At a predetermined position of the detachable container 20, a moving structure unit 42 including one end 40 to which the externally used equipment 30 is detachably attached, and a drive unit 44 for selectively driving the moving structure unit 42 are attached. Yes. In this example, the horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight retractor 10 are arranged on the floor member 20b of the detachable container 20 on the front side of the main body 12a of the fuselage indicated by the arrow F in FIG. A pair of moving structure units 42 are attached to the rear side in the opposite direction. The pair of moving structure units 42 have the same structure as each other, and are preferably arranged symmetrically in the left and right in the cargo compartment CR of the fuselage in the horizontal direction when the fuselage is viewed from the front. Nevertheless, according to the concept of the present invention, at least one moving structure unit 42 is sufficient.

  The externally used equipment 30 is equipment that is exposed outside the fuselage and used, for example, at least a hoist, a sample collector, a measuring instrument, an observation device, a camera, an acoustic device, a lighting fixture, an antenna, a firearm, a missile, etc. One can be included, but of course other equipment may be used.

  The movable structural unit 42 is pulled in by pulling the one end 40 into the cargo compartment CR together with the external equipment 30 as shown by the solid line in FIGS. 7 and 8 while the door 12d is disposed in the open position. As shown by a two-dot chain line in FIGS. 7 and 8, the position can be moved between the exposed position exposed to the outside of the body in the horizontal direction through the cargo compartment opening CO. The moving structure unit 42 of this example includes a horizontal moving type link mechanism as shown in FIG.

  In this example, the moving structure unit 42 on the front side can expose the externally used equipment 30 to the right outside of the body when the body is viewed from the front, and the moving structure unit 42 on the rear side can view the body from the front. The external equipment 30 can be exposed to the left outer side of the body. However, when the moving structure unit 42 on the front side sees the fuselage from the front, the external use equipment 30 is exposed to the left outer side of the fuselage, and when the moving structure unit 42 on the rear side sees the fuselage from the front, The equipment 30 can be exposed to the right outside of the body.

  In this example, the drive unit 44 includes a drive source 44a connected to each of the front-side moving structure unit 42 and the rear-side moving structure unit 42. The drive source 44a is, for example, an electric motor, a combination of an electric motor and a gear train, It can be a combination of an electric motor and a lever, or a piston-cylinder assembly utilizing fluid pressure.

  The drive unit 44 includes a control unit 44b that controls the operation of the drive source 44a between the moving structure unit 42 on the front side and the moving structure unit 42 on the rear side. In the drive unit 44, a power source for the electric motor or a fluid pressure source (for example, a compressor) for the fluid pressure is disposed between the moving structure unit 42 on the front side and the moving structure unit 42 on the rear side. I can do it. The electric motor or the electric motor of the fluid source may be configured to be electrically connectable to a power supply terminal disposed in the cargo compartment of the main part 12a of the fuselage of the helicopter 12.

  In FIG. 7, the externally used equipment 30 at the retracted position is indicated by a solid line, and the externally used equipment 30 at the exposed position is indicated by a two-dot chain line.

  Opening and closing of the door 12d for the cargo compartment opening CO of the cargo compartment CR of the fuselage of the helicopter 12 may be performed manually by a passenger of the helicopter 12, but is performed by a door opening / closing drive unit 46 provided in the removable container 20. It is preferable. The door opening / closing drive unit 46 can be a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly utilizing fluid pressure, or the like. In the case where the door opening / closing drive unit 46 is a combination of an electric motor and a gear train, it is necessary to attach a rack rail that meshes with the gear train to the door 12d. It is not a modification. When the door opening / closing drive unit 46 is a combination of an electric motor and a lever or a piston-cylinder assembly utilizing fluid pressure, it is necessary to connect the tip of the lever or the tip of the piston to the door 12d. Is easy, and is not an essential modification of the main body of the door 12d.

  The control unit 44b is configured to be operated directly or remotely by a passenger of the helicopter 12. When the door 12d is opened / closed by the door opening / closing drive unit 46, the control unit 44b interlocks with the operation of the door opening / closing drive unit 46 to drive the front moving structure unit 42 and the drive source 44a of the rear moving structure unit 42. Can be configured to control the operation of

  In this example, the operation of the door opening / closing drive unit 46 is controlled using the control unit 44b, and the operation of the driving source 44a of the moving structure unit 42 on the front side and the moving structure unit 42 on the rear side is controlled to use externally-used equipment. 30 is moved from the retracted position in which the main body 12a of the helicopter 12 is pulled into the cargo compartment CR of the helicopter 12 to the exposed position that is exposed to the outside of the fuselage in the horizontal direction via the cargo compartment opening CO of the main body 12a of the fuselage. When the door 12d is first moved from the closed position to the open position by the door opening / closing drive unit 46, the front side moving structure unit 42 and the rear moving structure unit 42 are driven by the drive source 44a. The moving structure unit 42 and the rear moving structure unit 42 are driven to move the externally used equipment 30 from the retracted position to the exposed position. .

  When the external equipment 30 is moved from the exposed position to the retracted position, the front moving structure unit 42 and the rear moving structure unit 42 are first driven by the driving source 44a of the front moving structure unit 42 and the rear moving structure unit 42. After driving the moving structural unit 42 and moving the externally used equipment 30 from the exposed position to the retracted position, the door opening / closing drive unit 46 moves the door 12d from the open position to the closed position.

<< Second example >>
Referring to FIG. 9 and FIG. 10, a configuration common to the horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight retracting devices 10, 10 ′ and 10 ″ according to the first to third embodiments. The case of the detachable container 20 of the aircraft mounted equipment / external deployment and in-flight retractor 10 according to the first embodiment will be described with respect to two examples.

  9A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 9B schematically shows the helicopter of FIG. The front half 12 of the fuselage 12 and the upper half of the main portion 12a when viewed from above 12 are shown schematically.

  A detachable container not shown here by a detachable fixing structure 14 (see FIGS. 1 and 2) not shown here at a predetermined position of the floor surface FL which is a part of the inner surface of the cargo compartment CR of the main portion 12a. 20 (see FIGS. 1 and 2) is detachably fixed. In FIGS. 9A and 9B, the door 12d in the closed position in which the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is closed is shown by a solid line.

  FIG. 10A also schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 10B also schematically shows the helicopter of FIG. Although the front half 12b of the fuselage 12 and the upper half of the main portion 12a are schematically cut away when viewed from above, the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is shown here. The opened door 12d in the open position is indicated by a solid line.

  At a predetermined position of the detachable container 20, a moving structure unit 52 including an end portion 50 to which the externally used equipment 30 is detachably attached and a drive unit 54 for selectively driving the moving structure unit 52 are attached. Yes. In this example, the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retracting device 10 is seen from the front as shown in FIG. 9A on the floor member 20b of the detachable container 20. A pair of moving structure units 52 are attached to the left and right sides of the main body 12a of the body. However, in FIGS. 9A and 9B, only the right moving structure unit 52 is shown. The pair of moving structure units 52 have the same structure as each other, and are preferably arranged symmetrically in the left and right in the cargo compartment CR of the fuselage in the horizontal direction when the fuselage is viewed from the front. Nevertheless, according to the concept of the present invention, at least one moving structure unit 52 is sufficient.

  As in the case of the first example described above with reference to FIGS. 7 and 8, the externally used equipment 30 is equipment that is used by being exposed to the outside of the body, such as a hoist, a sample collector, and a measuring instrument. , An observation device, a camera, an audio device, a lighting device, an antenna, a firearm, a missile, and the like.

  The moving structural unit 52 is shown in FIGS. 9A and 9B while the door 12d is positioned in the open position as shown in FIGS. 10A and 10B. As shown in FIG. 10A and FIG. 10B, the fuselage is opened in the horizontal direction by pulling the one end 50 into the cargo compartment CR together with the external equipment 30 and the cargo compartment opening CO. It is possible to move between the exposure positions exposed outside. The moving structure unit 52 of this example includes a pantograph mechanism, which is a kind of link mechanism, as shown in FIGS. 9A and 10A.

  In this example, the right moving structure unit 52 can expose the externally used equipment 30 to the right outside of the body when the body is viewed from the front, and the left moving structure unit 52 is when the body is viewed from the front. The external equipment 30 can be exposed to the left outer side of the body.

  In this example, the drive unit 54 includes a drive source 54a, and the drive source 54a is, for example, an electric motor, a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly using fluid pressure, or the like. I can do it.

  The drive unit 54 includes a control unit 54b that controls the operation of the drive source 54a between the right moving structure unit 52 and the left moving structure unit 52. In the drive unit 54, a power source for the electric motor or a fluid pressure source (for example, a compressor) for the fluid pressure may be disposed between the right moving structure unit 52 and the left moving structure unit 52. The electric motor or the electric motor of the fluid source may be configured to be electrically connectable to a power supply terminal disposed in the cargo compartment of the main part 12a of the fuselage of the helicopter 12.

  9A and 9B show the externally used equipment 30 in the retracted position, and FIGS. 10A and 10B show the externally used equipment 30 in the exposed position.

  The opening and closing of the door 12d for the cargo compartment opening CO of the fuselage compartment CR of the fuselage of the helicopter 12 may be manually performed by the passenger of the helicopter 12, but the first example described above with reference to FIGS. As in the case, it is preferable that the door opening / closing drive unit 46 (see FIGS. 7 and 8) provided in the removable container 20 (not shown) is used. The door opening / closing drive unit 46 can be a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly utilizing fluid pressure, or the like. In the case where the door opening / closing drive unit 46 is a combination of an electric motor and a gear train, it is necessary to attach a rack rail that meshes with the gear train to the door 12d. It is not a modification. When the door opening / closing drive unit 46 is a combination of an electric motor and a lever or a piston-cylinder assembly utilizing fluid pressure, it is necessary to connect the tip of the lever or the tip of the piston to the door 12d. Is easy, and is not an essential modification of the main body of the door 12d.

  The control unit 54b is configured to be operated directly or remotely by a passenger of the helicopter 12. When the door 12d is opened / closed by the door opening / closing drive unit 46 (see FIGS. 7 and 8), the control unit 54b moves the right side moving structure unit 52 and the left side in conjunction with the operation of the door opening / closing drive unit 46. It can be configured to control the operation of the drive source 54a of the structural unit 52.

  In this example, the control unit 54b is used to control the operation of the door opening / closing drive unit 46 (see FIGS. 7 and 8) and the operation of the right moving structure unit 52 and the drive source 54a of the left moving structure unit 52. Is controlled from the retracted position where the externally used equipment 30 is retracted into the cargo compartment CR of the main part 12a of the fuselage 12 to the outside of the fuselage in the horizontal direction via the cargo compartment opening CO of the main part 12a of the fuselage. When moving to the exposure position to be exposed, the door opening / closing drive unit 46 first opens the door 12d from the closed position shown in FIG. 9B to the open position shown in FIG. The right moving structure unit 52 and the left moving structure unit 52 are driven by the drive source 54a of the right moving structure unit 52 and the left moving structure unit 52. Driven to move to the exposed position shown external fleet 30 shown in retracted and positioned (A) and (B) in FIG. 9 (A) and (B) in FIG. 10.

  When the external equipment 30 is moved from the exposed position shown in FIGS. 10A and 10B to the retracted position shown in FIGS. 9A and 9B, first, The right moving structure unit 52 and the left moving structure unit 52 are driven by the driving source 54a of the right moving structure unit 52 and the left moving structure unit 52 to move the externally used equipment 30 from the exposed position to the retracted position. After that, the door opening / closing drive unit 46 moves the door 12d from the open position to the closed position.

<Third example>
Referring to FIGS. 11 and 12, the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retracting devices 10, 10 ′, and 10 ″ according to the first to third embodiments are configured in common. The case of the detachable container 20 of the aircraft mounted equipment / external deployment and in-flight retractor 10 according to the first embodiment will be described with respect to three examples.

  11A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 11B schematically shows the helicopter of FIG. The front half 12 of the fuselage 12 and the upper half of the main portion 12a when viewed from above 12 are shown schematically.

  In this example, the detachable fixing structure 14 (see FIG. 1 and FIG. 2) not shown here at a predetermined position of the ceiling CL which is a part of the inner surface of the cargo compartment CR of the main portion 12a is not shown here. A possible container 20 (see FIGS. 1 and 2) is detachably fixed. Further, in FIGS. 11A and 11B, the door 12d in the closed position in which the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is closed is shown by a solid line.

  12A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 12B also schematically shows the helicopter of FIG. Although the front half 12b of the fuselage 12 and the upper half of the main portion 12a are schematically cut away when viewed from above, the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is shown here. The opened door 12d in the open position is indicated by a solid line.

  At a predetermined position of the detachable container 20, a moving structure unit 62 including one end 60 to which the externally used equipment 30 is detachably attached, and a drive unit 64 that selectively drives the moving structure unit 62 are attached. Yes. In this example, the horizontal / vertical flightable aircraft-mounted equipment / external deployment and in-flight retractor 10 is shown in FIG. 11A on the floor member 20b of the detachable container 20 (in this example, the ceiling member). As shown, a pair of moving structure units 62 are attached to the left and right sides of the main body 12a of the body when the body is viewed from the front. However, in FIGS. 11A and 11B, only the right moving structure unit 62 is shown. The pair of moving structure units 62 have the same structure as each other, and are preferably arranged symmetrically in the left and right in the cargo compartment CR of the fuselage in the horizontal direction when the fuselage is viewed from the front. Nevertheless, according to the concept of the present invention, at least one moving structure unit 62 is sufficient.

  As in the case of the first example described above with reference to FIGS. 7 and 8, the externally used equipment 30 is equipment that is used by being exposed to the outside of the body, such as a hoist, a sample collector, and a measuring instrument. , An observation device, a camera, an audio device, a lighting device, an antenna, a firearm, a missile, and the like.

  The moving structural unit 62 is shown in FIGS. 11A and 11B while the door 12d is positioned in the open position as shown in FIGS. 12A and 12B. As shown in FIG. 12A and FIG. 12B, the fuselage in the horizontal direction through the retracted position in which the one end 60 is pulled into the cargo compartment CR together with the external equipment 30 as shown in FIG. It is possible to move between the exposure positions exposed outside. The moving structure unit 62 of this example includes a so-called swing-type link mechanism as shown in FIGS. 11A and 12A.

  In this example, the right moving structure unit 62 can expose the externally used equipment 30 to the right outside of the body when the body is viewed from the front, and the left moving structure unit 62 is when the body is viewed from the front. The external equipment 30 can be exposed to the left outer side of the body.

  In this example, the drive unit 64 includes a drive source 64a, and the drive source 64a is, for example, an electric motor, a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly using fluid pressure, or the like. I can do it.

  The drive unit 64 includes a control unit 64b that controls the operation of the drive source 64a between the right moving structure unit 62 and the left moving structure unit 62. In the drive unit 64, a power source for the electric motor or a fluid pressure source (for example, a compressor) for the fluid pressure may be disposed between the right moving structure unit 62 and the left moving structure unit 62. The electric motor or the electric motor of the fluid source may be configured to be electrically connectable to a power supply terminal disposed in the cargo compartment of the main part 12a of the fuselage of the helicopter 12.

  11A and 11B show the externally used equipment 30 in the retracted position, and FIGS. 12A and 12B show the externally used equipment 30 in the exposed position.

  The opening and closing of the door 12d for the cargo compartment opening CO of the fuselage compartment CR of the fuselage of the helicopter 12 may be manually performed by the passenger of the helicopter 12, but the first example described above with reference to FIGS. As in the case, it is preferable that the door opening / closing drive unit 46 (see FIGS. 7 and 8) provided in the removable container 20 (not shown) is used. The door opening / closing drive unit 46 can be a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly utilizing fluid pressure, or the like. In the case where the door opening / closing drive unit 46 is a combination of an electric motor and a gear train, it is necessary to attach a rack rail that meshes with the gear train to the door 12d. It is not a modification. When the door opening / closing drive unit 46 is a combination of an electric motor and a lever or a piston-cylinder assembly utilizing fluid pressure, it is necessary to connect the tip of the lever or the tip of the piston to the door 12d. Is easy, and is not an essential modification of the main body of the door 12d.

  The control unit 64b is configured to be directly operated or remotely operated by a passenger of the helicopter 12. When the door 12d is opened / closed by the door opening / closing drive unit 46 (see FIGS. 7 and 8), the control unit 64b moves the right side moving structure unit 62 and the left side in conjunction with the operation of the door opening / closing drive unit 46. It can be configured to control the operation of the drive source 64a of the structural unit 62.

  In this example, the control unit 64b is used to control the operation of the door opening / closing drive unit 46 (see FIGS. 7 and 8), and the operation of the right moving structure unit 62 and the driving source 64a of the left moving structure unit 62. Is controlled from the retracted position where the externally used equipment 30 is retracted into the cargo compartment CR of the main part 12a of the fuselage 12 to the outside of the fuselage in the horizontal direction via the cargo compartment opening CO of the main part 12a of the fuselage. When moving to the exposure position to be exposed, first, the door opening / closing drive unit 46 moves the door 12d from the closed position shown in FIG. 11B to the open position shown in FIG. The right moving structure unit 62 and the left moving structure unit 62 are driven by the drive source 64a of the right moving structure unit 62 and the left moving structure unit 62. The driven to move to the exposed position shown external fleet 30 shown in retracted and positioned (A) and (B) in FIG. 11 (A) and (B) in FIG. 12.

  When the external equipment 30 is moved from the exposed position shown in FIGS. 12A and 12B to the retracted position shown in FIGS. 11A and 11B, first, The right moving structure unit 62 and the left moving structure unit 62 are driven by the drive source 64a of the right moving structure unit 62 and the left moving structure unit 62 to move the external equipment 30 from the exposed position to the retracted position. After that, the door opening / closing drive unit 46 moves the door 12d from the open position to the closed position.

<< 4th example >>
Referring to FIG. 13 and FIG. 14, a configuration common to the horizontal and vertical flightable aircraft-mounted equipment / external deployment and in-flight retracting devices 10, 10 ′, and 10 ″ according to the first to third embodiments. Regarding the four examples, the case of the detachable container 20 of the aircraft-mounted equipment / external deployment and the in-flight retractor 10 according to the first embodiment will be described.

  13A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 13B schematically shows the helicopter of FIG. The front half 12 of the fuselage 12 and the upper half of the main portion 12a when viewed from above 12 are shown schematically.

  A detachable container not shown here by a detachable fixing structure 14 (see FIGS. 1 and 2) not shown here at a predetermined position of the floor surface FL which is a part of the inner surface of the cargo compartment CR of the main portion 12a. 20 (see FIGS. 1 and 2) is detachably fixed. In FIGS. 13A and 13B, the door 12d in the closed position in which the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is closed is shown by a solid line.

  14A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 14B also schematically shows the helicopter of FIG. Although the front half 12b of the fuselage 12 and the upper half of the main portion 12a are schematically cut away when viewed from above, the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is shown here. The opened door 12d in the open position is indicated by a solid line.

  At a predetermined position of the detachable container 20, a moving structure unit 72 including an end portion 70 to which the externally used equipment 30 is detachably attached, and a drive unit 74 that selectively drives the moving structure unit 72 are attached. Yes. In this example, the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retractor 10 can be seen from the front as shown in FIG. 13 (A) on the floor member 20b of the detachable container 20. A pair of moving structure units 72 are attached to the left and right sides of the main part 12a of the body. However, in FIGS. 13A and 13B, only the right moving structure unit 72 is shown. The pair of moving structure units 72 have the same structure as each other, and are preferably arranged symmetrically in the left and right in the cargo compartment CR of the fuselage in the horizontal direction when the fuselage is viewed from the front. Nevertheless, according to the concept of the present invention, at least one moving structure unit 72 is sufficient.

  As in the case of the first example described above with reference to FIGS. 7 and 8, the externally used equipment 30 is equipment that is used by being exposed to the outside of the body, such as a hoist, a sample collector, and a measuring instrument. , An observation device, a camera, an audio device, a lighting device, an antenna, a firearm, a missile, and the like.

  The moving structure unit 72 is shown in FIGS. 13A and 13B while the door 12d is positioned in the open position as shown in FIGS. 14A and 14B. As shown in FIG. 14A and FIG. 14B, the fuselage is opened in the horizontal direction by pulling the one end 70 together with the externally used equipment 30 into the cargo compartment CR and the cargo compartment opening CO as shown in FIGS. It is possible to move between the exposure positions exposed outside. The moving structure unit 72 of this example includes a telescopic column structure as shown in FIGS. 13A and 13B and FIGS. 14A and 14B.

  In this example, the right moving structure unit 72 can expose the externally used equipment 30 to the right outside of the body when the body is viewed from the front, and the left moving structure unit 72 is when the body is viewed from the front. The external equipment 30 can be exposed to the left outer side of the body.

  In this example, the drive unit 74 includes a drive source 74a, and the drive source 74a is, for example, an electric motor, a combination of an electric motor and a rod screw member, a combination of an electric motor and a lever, a piston-cylinder assembly using fluid pressure, or the like. I can do it.

  The drive unit 74 includes a control unit 74b that controls the operation of the drive source 74a between the right moving structure unit 72 and the left moving structure unit 72. In the drive unit 74, a power source for the electric motor or a fluid pressure source (for example, a compressor) for the fluid pressure may be disposed between the right moving structure unit 72 and the left moving structure unit 72. The electric motor or the electric motor of the fluid source may be configured to be electrically connectable to a power supply terminal disposed in the cargo compartment of the main part 12a of the fuselage of the helicopter 12.

  13A and 13B show the externally used equipment 30 in the retracted position, and FIGS. 14A and 14B show the externally used equipment 30 in the exposed position.

  The opening and closing of the door 12d for the cargo compartment opening CO of the fuselage compartment CR of the fuselage of the helicopter 12 may be manually performed by the passenger of the helicopter 12, but the first example described above with reference to FIGS. As in the case, it is preferable that the door opening / closing drive unit 46 (see FIGS. 7 and 8) provided in the removable container 20 (not shown) is used. The door opening / closing drive unit 46 can be a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly utilizing fluid pressure, or the like. In the case where the door opening / closing drive unit 46 is a combination of an electric motor and a gear train, it is necessary to attach a rack rail that meshes with the gear train to the door 12d. It is not a modification. When the door opening / closing drive unit 46 is a combination of an electric motor and a lever or a piston-cylinder assembly utilizing fluid pressure, it is necessary to connect the tip of the lever or the tip of the piston to the door 12d. Is easy, and is not an essential modification of the main body of the door 12d.

  The control unit 74b is configured to be operated directly or remotely by a passenger of the helicopter 12. When the door 12d is opened / closed by the door opening / closing drive unit 46 (see FIGS. 7 and 8), the control unit 74b moves the right side moving structure unit 72 and the left side in conjunction with the operation of the door opening / closing drive unit 46. It can be configured to control the operation of the drive source 74a of the structural unit 72.

  In this example, the control unit 74b is used to control the operation of the door opening / closing drive unit 46 (see FIGS. 7 and 8) and the operation of the right moving structure unit 72 and the drive source 74a of the left moving structure unit 72. Is controlled from the retracted position where the externally used equipment 30 is retracted into the cargo compartment CR of the main part 12a of the fuselage 12 to the outside of the fuselage in the horizontal direction via the cargo compartment opening CO of the main part 12a of the fuselage. When moving to the exposure position to be exposed, the door opening / closing drive unit 46 first opens the door 12d from the closed position shown in FIG. 13B to the open position shown in FIG. The right moving structure unit 72 and the left moving structure unit 72 are driven by the drive source 74a of the right moving structure unit 72 and the left moving structure unit 72. The driven to move to the exposed position shown external fleet 30 shown in retracted and positioned in FIG. 13 (A) and (B) in (A) and (B) in FIG. 14.

  When the external equipment 30 is moved from the exposed position shown in FIGS. 14A and 14B to the retracted position shown in FIGS. 13A and 13B, first, The right moving structure unit 72 and the left moving structure unit 72 are driven by the drive source 74a of the right moving structure unit 72 and the left moving structure unit 72 to move the external equipment 30 from the exposed position to the retracted position. After that, the door opening / closing drive unit 46 moves the door 12d from the open position to the closed position.

<< 5th example >>
Referring to FIG. 15 and FIG. 16, the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retracting devices 10, 10 ′, and 10 ″ according to the first to third embodiments are configured in common. The case of the detachable container 20 of the aircraft mounted equipment / external deployment and in-flight retractor 10 according to the first embodiment will be described with respect to five examples.

  FIG. 15A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 15B schematically shows the helicopter of FIG. The front half 12 of the fuselage 12 and the upper half of the main portion 12a when viewed from above 12 are shown schematically.

  A detachable container not shown here by a detachable fixing structure 14 (see FIGS. 1 and 2) not shown here at a predetermined position of the floor surface FL which is a part of the inner surface of the cargo compartment CR of the main portion 12a. 20 (see FIGS. 1 and 2) is detachably fixed. In FIGS. 15A and 15B, the door 12d in the closed position in which the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is closed is indicated by a solid line.

  16A schematically shows the right half of the front portion 12b of the fuselage when the helicopter 12 of FIG. 1 is viewed from the front, and FIG. 16B also schematically shows the helicopter of FIG. Although the front half 12b of the fuselage 12 and the upper half of the main portion 12a are schematically cut away when viewed from above, the cargo compartment opening CO facing the horizontal direction of the cargo compartment CR is shown here. The opened door 12d in the open position is indicated by a solid line.

  At a predetermined position of the detachable container 20, a moving structure unit 82 including one end 80 to which the externally used equipment 30 is detachably attached and a drive unit 84 that selectively drives the moving structure unit 82 are attached. Yes. In this example, the horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight retracting device 10 is seen from the front as shown in FIG. 15A on the floor member 20b of the detachable container 20. A pair of moving structure units 82 are attached to the left and right sides of the main body 12a of the body. However, in FIGS. 15A and 15B, only the right moving structure unit 82 is shown. The pair of moving structure units 82 have the same structure as each other, and are preferably arranged symmetrically in the left and right in the cargo compartment CR of the fuselage in the horizontal direction when the fuselage is viewed from the front. Nevertheless, according to the concept of the present invention, at least one moving structure unit 82 is sufficient.

  As in the case of the first example described above with reference to FIGS. 7 and 8, the externally used equipment 30 is equipment that is used by being exposed to the outside of the body, such as a hoist, a sample collector, and a measuring instrument. , An observation device, a camera, an audio device, a lighting device, an antenna, a firearm, a missile, and the like.

  The moving structural unit 82 is shown in FIGS. 15A and 15B while the door 12d is positioned in the open position as shown in FIGS. 16A and 16B. As shown in FIG. 16A and FIG. 16B, the fuselage in the horizontal direction through the retracted position where the one end 80 is drawn into the cargo compartment CR together with the external equipment 30 as shown. It is possible to move between the exposure positions exposed outside. The moving structure unit 72 of this example is pivoted so that the one end 80 can be pivoted horizontally as shown in FIGS. 15A and 15B and FIGS. 16A and 16B. Contains a structure. The rotating structure includes a central axis CS that extends upward toward the floor member 20b of the removable container 20. The lower end of the center axis CS is supported with respect to the floor member 20b so that the center axis CS is fixed or rotatable around a vertical center line. A horizontal rotation lever HL with one end 80 is combined with the central axis CS. When the lower end of the central axis CS is fixed to the floor member 20b, the horizontal rotation lever HL is attached to the central axis CS so as to be able to rotate in the horizontal direction around the central axis CS. When the center axis CS is supported so that the lower end of the center axis CS can rotate around the center line in the vertical direction, the horizontal rotation lever HL can rotate in the horizontal direction around the center axis CS. It is fixed to the central axis CS.

  In this example, the right moving structure unit 82 can expose the externally used equipment 30 to the right outside of the body when the body is viewed from the front, and the left moving structure unit 82 is when the body is viewed from the front. The external equipment 30 can be exposed to the left outer side of the body.

  In this example, the drive unit 84 includes a drive source 84a, and the drive source 84a is, for example, an electric motor, a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly using fluid pressure, or the like. I can do it.

  The drive unit 84 includes a control unit 84b that controls the operation of the drive source 84a between the right moving structure unit 82 and the left moving structure unit 82. In the drive unit 84, a power source for the electric motor or a fluid pressure source (for example, a compressor) for the fluid pressure may be disposed between the right moving structure unit 82 and the left moving structure unit 82. The electric motor or the electric motor of the fluid source may be configured to be electrically connectable to a power supply terminal disposed in the cargo compartment of the main part 12a of the fuselage of the helicopter 12.

  15A and 15B show the externally used equipment 30 in the retracted position, and FIGS. 16A and 16B show the externally used equipment 30 in the exposed position.

  The opening and closing of the door 12d for the cargo compartment opening CO of the fuselage compartment CR of the fuselage of the helicopter 12 may be manually performed by the passenger of the helicopter 12, but the first example described above with reference to FIGS. As in the case, it is preferable that the door opening / closing drive unit 46 (see FIGS. 7 and 8) provided in the removable container 20 (not shown) is used. The door opening / closing drive unit 46 can be a combination of an electric motor and a gear train, a combination of an electric motor and a lever, a piston-cylinder assembly utilizing fluid pressure, or the like. In the case where the door opening / closing drive unit 46 is a combination of an electric motor and a gear train, it is necessary to attach a rack rail that meshes with the gear train to the door 12d. It is not a modification. When the door opening / closing drive unit 46 is a combination of an electric motor and a lever or a piston-cylinder assembly utilizing fluid pressure, it is necessary to connect the tip of the lever or the tip of the piston to the door 12d. Is easy, and is not an essential modification of the main body of the door 12d.

  The control unit 84b is configured to be operated directly or remotely by a passenger of the helicopter 12. When the door 12d is opened / closed by the door opening / closing drive unit 46 (see FIGS. 7 and 8), the control unit 84b moves to the left and the right moving structure unit 82 in conjunction with the operation of the door opening / closing drive unit 46. It can be configured to control the operation of the drive source 84a of the structural unit 82.

  In this example, the control unit 84b is used to control the operation of the door opening / closing drive unit 46 (see FIGS. 7 and 8) and the operation of the right moving structure unit 82 and the drive source 84a of the left moving structure unit 82. Is controlled from the retracted position where the externally used equipment 30 is retracted into the cargo compartment CR of the main part 12a of the fuselage 12 to the outside of the fuselage in the horizontal direction via the cargo compartment opening CO of the main part 12a of the fuselage. When moving to the exposure position to be exposed, the door opening / closing drive unit 46 first opens the door 12d from the closed position shown in FIG. 15B to the open position shown in FIG. The right moving structure unit 82 and the left moving structure unit 82 are driven by the drive source 84a of the right moving structure unit 82 and the left moving structure unit 82. The driven to move to the exposed position shown external fleet 30 shown in retracted and positioned in FIG. 15 (A) and (B) in (A) and (B) in FIG. 16.

  When the external equipment 30 is moved from the exposed position shown in FIGS. 16A and 16B to the retracted position shown in FIGS. 15A and 15B, first, The right moving structure unit 82 and the left moving structure unit 82 are driven by the drive source 84a to move the right moving structure unit 82 and the left moving structure unit 82 to move the external equipment 30 from the exposed position to the retracted position. After that, the door opening / closing drive unit 46 moves the door 12d from the open position to the closed position.

<< Modifications of First to Fifth Examples >>
It should be noted that the external use equipment 30 is detachably attached to the one end portions 40, 50, 60, 70, and 80 of the moving structure units 42, 52, 62, 72, and 82 of the first to fifth examples described above. The external equipment 30 can be detachably attached via an attachment member that can rotate in a predetermined or arbitrary direction. Further, the mounting member can be configured to be controlled to face a desired direction by the control units 44b, 54b, 64b, 72b, and 82b of the first to fifth examples. In this case, the externally used equipment 30 arranged at the exposure position can be directed in a desired direction.

DESCRIPTION OF SYMBOLS 10 ... Airplane equipment which can be horizontally / vertically flightable / Expansion and retracting device, 12 ... Helicopter, 12a ... Main part, 12b ... Front part, 12c ... Rear part, 12d ... Door, CR ... Cargo, FL ... Floor surface, DESCRIPTION OF SYMBOLS 14 ... Removable fixing structure, 14a ... Fixed hole, 14b ... Fixed member, HS ... Horizontal tail, TR ... Tail rotor, CO ... Cargo opening, 20 ... Removable container, 20a ... Fixed hole, 20b ... Floor member;
10 '... Horizontal and vertical flightable aircraft-equipped equipment / expansion and retracting device, 14' ... Removable fixing structure, 14'R ... Fixed rail, EG ... Engagement hole, SL ... Slit, 14'S ... Fixing member , 14'U ... upward projecting portion, 14'RM ... fixed rail, SLM ... slit, EGM ... engagement hole, 14'P ... fixing member, 14'W ... stud bolt, 14'F ... retainer, 20 '... detachable Possible container, 20'a ... fixing hole, 20'b ... floor member;
10 ″: Horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight retracting device, 14 ″ —detachable fixing structure, 14 ″ L—fixing member, 14 ″ F—latch member, 20 ″ ... Removable container, 20 ″ b ... floor member;
30 ... External equipment, 40 ... One end, 42 ... Moving structure unit, 44 ... Drive unit, F ... Arrow, 44a ... Drive source, 44b ... Control unit, 46 ... Door opening / closing drive unit;
50 ... one end, 52 ... moving structure unit, 54 ... drive unit, 54a ... drive source, 54b ... control unit;
60 ... one end, 62 ... moving structure unit, 64 ... drive unit, 64a ... drive source, 64b ... control unit;
70 ... one end, 72 ... moving structure unit, 74 ... drive unit, 74a ... drive source, 74b ... control unit;
80 ... one end part, 82 ... moving structure unit, 84 ... drive unit, 84a ... drive source, 84b ... control unit, CS ... central axis, HL ... horizontal rotation lever

In order to achieve the above object, the horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retractor according to the present invention are:
A detachable fixing structure that is always provided on the inner surface of the luggage compartment in the fuselage to detachably fix the equipment or luggage, and a cargo compartment opening that opens the inside of the cargo compartment to the outside of the fuselage in the horizontal direction. the and Nde containing, in the body is provided with a movable door between an open position for opening said luggage compartment opening and a closed position for closing the luggage compartment opening, horizontal along the door to the side of the body A horizontally and vertically flightable aircraft-mounted equipment, outboard deployment and inboard retractor used in a horizontally and vertically flightable aircraft that is a sliding door that slides between the closed and open positions in a direction :
A detachable container that is detachably fixed to the inner surface of the cargo compartment of the horizontal and vertical flightable aircraft by the detachable fixing structure and is mounted in the cargo compartment;
The aircraft includes an end portion to which externally used equipment is detachably attached, is attached to the detachable container, and the one end portion is drawn into the cargo compartment together with the externally used equipment, and the horizontal and vertical flightable aircraft A movable structure unit capable of moving between an exposed position exposed to the outside of the body in the horizontal direction through the cargo compartment opening;
A drive unit attached to the removable container for selectively driving the moving structure unit and selectively moving the one end of the moving structure unit between the retracted position and the exposed position;
The door is moved from the closed position to the open position as the one end of the moving structure unit is fixed to the detachable container and moved from the retracted position to the exposed position by the drive unit. A door opening / closing drive unit that moves the door from the open position to the closed position as the part moves from the exposed position to the retracted position;
It is characterized by having.
In order to achieve the above object, another horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retractor according to the present invention are:
A detachable fixing structure that is always provided on the inner surface of the cargo compartment in the fuselage to detachably fix the equipment or luggage, and the inner side of the cargo compartment on the outer side of the fuselage in the horizontal direction on both sides of the fuselage. A pair of cargo compartment openings to be opened, wherein the body closes each of the pair of cargo compartment openings on both sides of the fuselage and opens each of the pair of cargo compartment openings. A pair of doors movable between the closed position and the open position, wherein the pair of doors slides between the closed position and the open position in a horizontal direction along both side surfaces of the body. Horizontal and vertical flightable aircraft-equipped equipment, outboard deployment and inboard retractor used in a pair of sliding doors, horizontal and vertical flightable aircraft:
A detachable container that is detachably fixed to the inner surface of the cargo compartment of the horizontal and vertical flightable aircraft by the detachable fixing structure and is mounted in the cargo compartment;
Each includes an end portion to which externally used equipment is detachably attached, and is attached to the detachable container corresponding to the pair of cargo compartment openings on the both side surfaces of the fuselage. The used part is moved between the retracted position where the one end portion is retracted into the cargo compartment and the exposed position exposed to the outside of the fuselage in the horizontal direction through the cargo compartment opening of the horizontally and vertically flightable aircraft. A pair of mobile structural units capable of
A drive unit attached to the removable container for selectively driving the moving structure unit and selectively moving the one end of the moving structure unit between the retracted position and the exposed position;
The pair of doors are fixed to the removable container, and the pair of doors are moved from the closed position to the open position by the drive unit moving the one end of the pair of moving structure units from the retracted position to the exposed position. A door opening / closing drive unit that moves the pair of doors from the open position to the closed position as the one end moves from the exposed position to the retracted position;
It is characterized by having.

Claims (12)

A detachable fixing structure that is always provided on the inner surface of the luggage compartment in the fuselage to detachably fix the equipment or luggage, and a cargo compartment opening that opens the inside of the cargo compartment to the outside of the fuselage in the horizontal direction. Horizontal and vertical flightable aircraft-equipped equipment, out-of-flight deployment and in-flight retractor used in horizontal and vertical flightable aircraft including:
A detachable container that is detachably fixed to the inner surface of the cargo compartment of the horizontal and vertical flightable aircraft by the detachable fixing structure and is mounted in the cargo compartment;
The aircraft includes an end portion to which externally used equipment is detachably attached, is attached to the detachable container, and the one end portion is drawn into the cargo compartment together with the externally used equipment, and the horizontal and vertical flightable aircraft A movable structure unit capable of moving between an exposed position exposed to the outside of the body in the horizontal direction through the cargo compartment opening;
A drive unit attached to the removable container for selectively driving the moving structure unit and selectively moving the one end of the moving structure unit between the retracted position and the exposed position;
An aircraft-mounted equipment / out-of-flight deployment and in-flight pull-in device capable of horizontal and vertical flight. The fuselage of the horizontal and vertical flightable aircraft includes a door that is movable between a closed position that closes the cargo compartment opening and an open position that opens the cargo compartment opening;
The door is moved from the closed position to the open position as the one end of the moving structure unit is fixed to the removable container and moved from the retracted position to the exposed position. A door opening / closing drive unit that moves the door from the open position to the closed position as the part moves from the exposed position to the retracted position;
The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to claim 1. The door of the fuselage of the horizontal and vertical flightable aircraft is a sliding door that slides between the closed position and the open position in a horizontal direction along a side surface of the fuselage;
The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to claim 2. The fuselage of the horizontal and vertical flightable aircraft is provided with a pair of luggage compartment openings on both sides;
The moving structure unit includes a pair of moving structure units corresponding to the luggage compartment openings on the both side surfaces of the body.
The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to claim 1. The fuselage of the horizontal and vertical flightable aircraft between a closed position that closes each of the pair of luggage compartment openings on each side of the fuselage and an open position that opens each of the pair of cargo compartment openings; With a pair of movable doors,
A pair of the doors are moved from the closed position to the open position as the drive unit moves from the retracted position to the exposed position of the one end of the pair of moving structure units fixed to the removable container. And a door opening / closing drive unit that moves the pair of doors from the open position to the closed position as the end portion moves from the exposed position to the retracted position.
The horizontal and vertical flightable aircraft-equipped aircraft / external deployment and in-flight retractor according to claim 4. A pair of the doors of the fuselage of the horizontal and vertical flightable aircraft are a pair of sliding doors that slide between the closed position and the open position in a horizontal direction along both sides of the fuselage;
6. The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to claim 5. The detachable fixing structure of the horizontal and vertical flightable aircraft includes a fixing hole formed at a plurality of predetermined positions on an inner surface of a cargo compartment in the fuselage, and a plurality of fixing bolts detachably fixed to the fixing holes. Including,
The horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight pull-in device according to any one of claims 1 to 6. The detachable fixing structure of the horizontal and vertical flightable aircraft includes a fixed rail that is detachably fixed to a plurality of predetermined positions on the inner surface of the cargo compartment in the fuselage, and is detachably fixed to an arbitrary position of the fixed rail. Including a fixing bolt,
The horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight pull-in device according to any one of claims 1 to 6. The detachable fixing structure of the horizontal and vertical flightable aircraft includes a hook metal fitting that is detachably fixed to a plurality of predetermined positions on the inner surface of the cargo compartment in the fuselage, and a detachable container mounted in the cargo compartment. A latch member that is latched and latched on a plurality of hook metal fittings,
The horizontal and vertical flightable aircraft-equipped equipment / external deployment and in-flight pull-in device according to any one of claims 1 to 6. The moving structure unit includes a link mechanism capable of horizontally moving the one end between the retracted position and the exposed position.
10. The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to any one of claims 1 to 9. The moving structure unit includes a telescopic column structure capable of horizontally moving the one end between the retracted position and the exposed position.
10. The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to any one of claims 1 to 9. The moving structure unit has a rotating structure that has a second end rotatably connected to the removable container and that allows the one end to be horizontally rotated between the retracted position and the exposed position. Including,
10. The horizontally and vertically flightable aircraft-mounted equipment / external deployment and in-flight retracting device according to any one of claims 1 to 9.