JP5485092B2 - Movable lugs and flying bodies equipped with them - Google Patents

Description

  The present invention relates to a movable lug and a flying body including the same.

When a flying body such as a missile is mounted on the lower part of the aircraft, the lug provided on the upper part of the missile is hooked on a hook provided on the lower part of the aircraft body or the main wing. When the hook is released, the flying object is separated from the aircraft and freely falls or flies.
Since the lug is fixed to the flying body and protrudes outside the flying body, it becomes a large air resistance at the time of flying. Flight performance such as the range and speed of the flying object will be reduced. This is a major problem for flying objects that fly at high speeds.

In order to reduce the air resistance of the lug, for example, as shown in Patent Literature 1, the lug is separated from the flying body and removed, or, for example, as shown in Patent Literature 2, the lug is flying What is housed inside is proposed.
In Patent Document 1, a rail is provided on the outer periphery of the flying body to the rear end thereof, and a lug that can be slid by engaging with the rail is restrained by a lug holder with a lug fixing tool (explosion bolt). When it opens at the time, the lug moves backward along the rail by air resistance or the like, and is separated from the rear end of the flying body.
In Patent Document 2, the lug is supported so as to be rotatable around the pivot shaft, and is always urged by the spring so that the upper part falls inside the flying body, and the hook is released. The lug rotates and is stored inside the flying body.

JP-A-6-241694 US Pat. No. 5,961,075

By the way, what is shown by patent document 1 has the subject that the structure of the suspension apparatus including a lug is complicated, becomes large and heavy, or the lug may hit an aircraft immediately after separation.
In the thing shown by patent document 2, since it is urged | biased so that a lug may always fall to the flying body side, it is necessary to hold | maintain in the position which the lug protruded at the time of mounting to an aircraft, and installation takes time. In addition, since the lug rotates following the movement of the hook, there is a problem that the flying object may not be separated due to being caught by the hook.

  In view of such circumstances, the present invention provides a movable lug that can be easily mounted on an aircraft with a simple, small, and lightweight structure and that can reduce air resistance caused by the lug safely and reliably, and a flying lug including the movable lug. The purpose is to provide ginger.

In order to solve the above problems, the present invention employs the following means.
That is, the first aspect of the present invention has an opening that is attached to the outer surface of the flying body so as to be rotatable about an axis extending in a direction perpendicular to the axis of the aircraft, and that accepts a hook provided on the aircraft, A pair of lugs provided at intervals in the aircraft axis direction of the flying object, and an outer surface of the flying object that is provided before or after the aircraft direction in each of the lugs and falls down on the flying object side A lug urging member that urges the lug so as not to protrude from the lug, a lug urging member that constantly urges the lug to rotate toward the accommodating part, and a lug engaging portion provided on the lug; A locking member that holds the locking member in a state protruding from the outer surface, and the locking member is attached to the aircraft, and the locking member is engaged with the lug engaging portion by its tension. Move to release And ear member is a movable lug that is provided.

According to the movable lug of this aspect configured as described above, when the engaging portion of the engaging member is engaged with the lug engaging portion of the lug, the opening on the other end side of the lug is the outer surface of the flying body. Can be held in a protruding state. In this state, when the flying object is attached to the aircraft, the lug is held in a state of protruding from the outer surface, so that the trouble of attaching the lug to the hook can be reduced. And the load which acts on a wire member, ie, tension | tensile_strength, is adjusted so that it may become a magnitude | size which does not move a locking member. For example, the length of the wire member may be set to be larger than the path length of the wire member when the flying object is mounted.
When separating the flying object mounted on the aircraft from the aircraft, first the hook is detached from the lug. At this time, since the engaging portion of the engaging member and the lug engaging portion of the lug are engaged, the lug is held in a state of protruding from the outer surface of the flying body. Therefore, since the lug does not rotate regardless of the movement of the hook, the hook can be reliably removed from the lug.

When the hook is pulled out from the lug, the flying object moves downward from the aircraft due to its weight, so that the interval between the attachment portions at both ends of the wire member gradually increases, and one end becomes a wire member attached to the aircraft. Such tension increases.
When the tension of the wire member reaches a predetermined magnitude, the wire member moves the locking member and releases the engagement of the locking portion with the lug engaging portion. When the engagement between the locking portion and the lug engaging portion is released, there is no force to hold the lug in a state protruding from the outer surface of the flying body, so the lug is accommodated by the biasing force of the lug biasing member. It is rotated to the side and accommodated so as not to protrude from the outer surface of the flying body.
When the flying object further falls, the tension of the wire member further increases, so that the wire member is cut halfway or at the attachment portions at both ends, and the flying object is completely separated from the aircraft.

As described above, when the flying object is separated from the aircraft, the lug is automatically and reliably accommodated in the accommodating portion, so that the air resistance due to the lug can be safely and reliably reduced.
Further, since the lug is stored and the flying object is separated by the tension acting on the wire member, for example, the timing of separating the flying object can be adjusted by adjusting the length or strength of the wire member. .
The movable lug is rotatably installed so that the lug is positioned in the housing portion by the lug urging member at a predetermined position, and a locking member that positions the lug in a protruding position and a wire member that releases the locking member. Since it is only provided, a simple, small and lightweight structure can be obtained. For this reason, attachment to an aircraft can be performed easily.

  In this aspect, the locking member is disposed at a lower part of the lug on the housing portion side so that at least a part in the direction perpendicular to the axis of the lug is in contact with the lug, and rotates around the locking axis extending in the direction perpendicular to the axis of the axis. The latching portion may be constantly urged so as to be held while being able to rotate toward the lug side.

  In this case, the locking member and the lug are pressed against each other with the locking portion and the lug engaging portion engaged, so that the lug can be reliably projected from the outer surface of the flying body. Can be held in.

  In this aspect, it is provided with a drive member that is movably attached to the flying body and has a drive portion that can be engaged with the locking member, and the drive member moves by the tension of the connected wire member. With this movement, the driving unit may move the locking member such that the locking unit releases the engagement with the lug engaging unit.

  According to this aspect, when the tension applied to the wire member increases, the drive member moves, and the engaging portion of the engaging member releases the engagement with the lug engaging portion.

  In this aspect, the wire member includes a first wire attached to the locking member or the driving member, a second wire attached to the aircraft, and free ends of the first wire and the second wire. And a connecting member that separates when a tension greater than a predetermined load is applied.

In this way, the wire member connects the first wire attached to the locking member or the drive member, the second wire attached to the aircraft, and the free ends of the first wire and the second wire and has a predetermined load. Since the connecting member that separates when the above tension acts is provided, the flying body further drops after the lug is accommodated in the accommodating portion, and when the tension acting on the wire member becomes a predetermined load or more, The connecting member is separated, and the flying object can be completely separated from the aircraft.
Therefore, since the flying object can be separated at the timing when the tension of the connecting member is separated, the timing at which the flying object is separated can be set more accurately.

  In this aspect, the drive member is rotatably supported around a drive shaft extending in a direction perpendicular to the machine axis, the wire member is connected to one side across the drive shaft, and the locking member is connected to the other side. The drive unit that prevents rotation to the lug side is provided, and the distance from the drive shaft to the attachment portion of the wire member is the distance from the drive shaft to the portion where the drive unit engages with the locking member It may be made larger.

In this way, the load applied to the portion where the drive unit engages with the locking member can be made larger than the load applied to the attachment portion of the wire member, that is, the tension acting on the wire member. The acting engagement force can be increased. Thereby, a locking member can be fixed more reliably.
At this time, the drive member may be constantly urged so that the attachment portion of the wire member rotates to the side opposite to the side where the wire member exists. In this case, when the wire member is cut and the tension is not applied, the drive member rotates to the side opposite to the side where the wire member exists, so the drive member rotates the cut wire member to the flying object side. And the influence on the flight performance of the wire member can be suppressed.

  In this aspect, the pair of lugs may be installed so that the housing portions face each other.

  If it does in this way, the installation range of the movable lug in the axis direction of a flying body can be made small.

  The second aspect of the present invention is a flying body provided with the movable lug of the first aspect.

Thus, since the movable lug of the first aspect is provided, the air resistance due to the lug can be reduced safely and reliably.
Moreover, since the movable lug having a simple, small and light structure is used, the structure of the flying object can be reduced in size.

In the present invention, when the engaging portion of the engaging member is engaged with the lug engaging portion of the lug, the lug can be held in a state where the opening on the other end side protrudes from the outer surface of the flying body. It is possible to reduce the trouble of attaching the lug to the hook, and when the hook is detached from the lug, the lug does not rotate regardless of the movement of the hook, so that the hook can be surely removed from the lug.
When the flying object is separated from the aircraft, the lug is automatically and reliably accommodated in the accommodating portion, so that air resistance due to the lug can be safely and reliably reduced.
Further, since the lug is stored and the flying object is separated by the tension acting on the wire member, for example, the timing of separating the flying object can be adjusted by adjusting the length or strength of the wire member. .
Further, the movable lug can have a simple and small structure.

It is a perspective view showing a missile equipped with a movable lug according to an embodiment of the present invention. It is a partial side view which shows the state with which the missile of FIG. 1 was mounted | worn with the aircraft. It is a perspective view showing a schematic structure of a movable lug concerning one embodiment of the present invention. It is a top view of the movable lug concerning one embodiment of the present invention. It is the front view seen from the left side of FIG. It is the rear view seen from the right side of FIG. FIG. 4 is a side view of FIG. 3. It is the fragmentary longitudinal cross-sectional view which cut through a part of FIG. It is a fragmentary sectional view which expands and shows the A section of FIG. It is the fragmentary longitudinal cross-sectional view which cut through a part of FIG. 2 in the initial stage of the missile fall. It is a fragmentary sectional view which expands and shows the A section of FIG. 8 in the state of FIG. It is the fragmentary longitudinal cross-sectional view which cut through a part of FIG. 2 in the state which the missile fell further than FIG. It is a fragmentary sectional view which expands and shows the A section of FIG. 8 in the state of FIG. It is the fragmentary longitudinal cross-sectional view which cut through a part of FIG. 2 in the state in which the missile was separated. It is a fragmentary sectional view which expands and shows the A section of FIG. 8 in the state of FIG. It is the fragmentary longitudinal cross-sectional view which cut through a part of FIG. 2 in the state which time passed from FIG.

Below, the movable lug 1 concerning one Embodiment of this invention is demonstrated with reference to FIGS.
FIG. 1 is a perspective view showing a missile (flying body) 3 equipped with a movable lug 1 according to this embodiment. FIG. 2 is a partial side view showing a state in which the missile 3 is mounted on the aircraft 5.
The movable lug 1 is provided with a front suspension member 7 and a rear suspension member 9 that are installed on the outer surface of the missile 3 in the axial direction L and spaced apart from each other across the center of gravity of the missile 3. ing.
Since the front suspension member 7 and the rear suspension member 9 are the same except that the front and rear suspensions are reversed, the rear suspension member 9 will be described here, and the structure of the front suspension member 7 will be described. Is omitted.

  FIG. 3 is a perspective view showing a schematic configuration of the rear suspension member 9. FIG. 4 is a plan view of the rear suspension member 9. FIG. 5 is a front view seen from the left side of FIG. 6 is a rear view seen from the right side of FIG. FIG. 7 is a side view of FIG. FIG. 8 is a partial longitudinal sectional view of a part of FIG. FIG. 9 is a partial cross-sectional view showing an A portion of FIG. 8 in an enlarged manner.

  The rear suspension member 9 includes a holding member 11 attached to the missile 3 so that the outer surface forms the outer surface of the missile 3, and a lower end portion at a position inside the outer surface portion of the missile 3 in the holding member 11. A lug 13 that is rotatably attached about an axis extending in the direction B perpendicular to the axis of the machine, and a lug 13 that is provided on the front side of the lug 13 in the machine axis direction L and that has fallen to the missile 3 side protrudes from the outer surface of the missile 3 The lug 13, and the lug coil spring (lug urging member) 17 that constantly urges the lug 13 to rotate toward the accommodating portion 15, and the holding member 11 extends in the direction B perpendicular to the axis. A stopper member (locking member) 19 that restricts the movement of the lug 13 and is attached rotatably to the holding member 11 around an axis extending in the direction B perpendicular to the machine axis. An arm member (driving member) 21 which is a stopper member 19 and engageable, a wire member 23 that connects the aircraft 5 and the arm member 21, is provided.

The holding member 11 includes an upper component member 25, a lower component member 27, and a center holding member 29.
The upper component member 25 has a box shape in which the front side of the central part B in the direction perpendicular to the axis is largely cut out in a substantially U shape and the lower part is opened. The lower component member 27 is installed so as to cover the periphery of the cutout portion 31 of the upper component member 25, and has a box shape with the upper portion opened. The lower part of the upper constituent member 25 and the upper part of the lower constituent member 27 are joined. A shaft member 33 is attached to a joint portion between the upper component member 25 and the lower component member 27 at a substantially central position in the machine axis direction L of the upper component member 25 so as to extend in the direction B perpendicular to the axis.

The center holding member 29 is a rectangular plate member disposed so as to constitute the outer surface of the missile 3 at a substantially central portion B in the direction perpendicular to the axis of the upper component member 25. The length of the central holding member 29 in the front-rear direction is substantially the same as that of the upper constituent member 25, and the length in the axis-perpendicular direction B is such that a gap is formed between the upper constituent member 25 and the cutout portion 31.
At the lower center of the front end of the central holding member 29, a holding portion 35 is provided that extends downward and the lower portion is bent rearward.
The central holding member 29 has a rear end portion attached to the upper component member 25 and a lower portion of the holding portion 35 attached to the arm member 21.

The lug 13 is U-shaped, and both open end portions (one end portions) are inserted into cutout portions 31 positioned on both sides of the central holding member 29 and are rotatably attached to the shaft member 33. As shown in FIGS. 2 to 6, the size of the lug 13 and the position of the shaft member 33 are such that the lug 13 is in a position (hereinafter referred to as an upright position) such that the lug 13 is orthogonal to the outer surface of the missile 3. An opening for receiving a hook 4 provided on the aircraft 5 is formed inside the closed end of 13.
The lug coil spring 17 is attached so as to surround the periphery of the shaft member 33, and one end is attached to the upper component member 25 and the other end is attached to the lug 13. The lug coil spring 17 urges the lug 13 to rotate to the front side around the shaft member 33, in other words, to the accommodating portion 15 side.

The lug 13 is provided with a lug protrusion (lug engaging portion) 37 projecting outward at the front lower portion in the upright position.
A pair of stopper members 19 are provided corresponding to the leg portions on both sides of the lug 13. The stopper member 19 includes a stopper shaft 39 that is rotatably supported by the lower component member 27 and that extends in the direction B perpendicular to the machine axis, and a stopper body 41 that is integrally attached to the stopper shaft 39. Yes. The stopper main body 41 has a substantially rectangular parallelepiped shape having substantially the same width as the leg portion of the lug 13 and is rotatable around the stopper shaft 39.

A stopper portion (locking portion) 43 that engages with the lug protrusion 37 is provided at the end of the stopper body 41 on the side of the lug 13.
A coil spring 45 is attached to the stopper shaft 39 at the shaft end. The coil spring 45 urges the stopper shaft 39 so that the stopper portion 43 moves to the lug 13 side.
As shown in FIGS. 8 and 9, when the lug protrusion 37 and the stopper 43 are engaged, the lug 13 is held in the upright position.
A stopper driving member 47, which is a bar extending in the direction perpendicular to the machine axis B, is attached to one end of the stopper body 41 opposite to the stopper portion 39 so as to protrude into the inner space portion of the lug 13. . The cross-sectional shape of the stopper driving member 47 is substantially rectangular, and the corner on the stopper portion 43 side has a curvature.

One arm member 21 is provided for each stopper member 19. Each arm member 21 has an arm main body 49 formed of a bent plate material, and a drive arm (drive) fixedly attached to a lower end portion of the arm main body 49 so as to protrude rearward from the arm main body 49. Part) 51 and a drive shaft 53 that is rotatably supported by the lower component member 27 and supports the arm main body 49 and the drive arm 51.
A coil spring 55 is attached to the shaft end of the drive shaft 53. The coil spring 55 urges the arm body 49 so that the free end moves away from the lug 13.

The free end of the arm body 49 is connected to the end of the wire member 23 so as to pull the free end of the arm body 49 toward the lug 13.
The drive arm 51 is located at a position where it can be engaged with the stopper drive member 47, and when mounted on the missile 3, the drive member 51 rotates the stopper member 19 toward the lug 13 as shown in FIG. To prevent.

The distance from the drive shaft 53 of the arm body 49 to the attachment position of the wire member 23 is approximately three times the distance from the drive shaft 53 of the drive arm 51 to the tip of the drive arm 51. Therefore, the distance from the drive shaft 53 to the attachment position of the wire member 23 is at least three times the distance from the drive shaft 53 of the drive arm 51 to the portion where the drive arm 51 engages with the stopper drive member 47. Will be.
If it does in this way, the load concerning the part which the drive arm 51 engages with the stopper drive member 47 can be made into 3 times or more of the load concerning the attachment part of the wire member 23, ie, the tension | tensile_strength which acts on a wire member.
In addition, if this magnification is 2 times or more, for example, a sufficient effect can be exhibited.

The wire member 23 is attached to the free end of the arm main body 49 and extends to the rear side through the lower part of the central holding member 29; the second wire 59 having one end attached to the aircraft 5; A coupler (connecting member) 61 that connects the free ends of the first wire and the second wire and separates when a tension greater than a predetermined load is applied is provided.
In the present embodiment, the first wire 57 is attached to the arm main body 49, that is, the arm member 21, but it is not limited to this. For example, the stopper portion 43 may be attached to the stopper member 19 so as to move in a direction in which the stopper portion 43 separates from the lug projection portion 37.

Although the structure of the rear suspension member 9 has been described above, the front suspension member 7 has the same structure as that of the rear suspension member 9 and the front-rear relationship is reversed.
Accordingly, a pair of lugs 13 are provided on the missile 3 at intervals along the axis direction L thereof. The pair of lugs 13 are installed so that the accommodating portions 15 face each other. Since the lug 13 is accommodated toward the inside of the space between the pair of lugs 13, the installation range of the movable lug 1 in the axial direction L of the missile 3 can be reduced.

  As shown in FIG. 2, the hook 4 is inserted into the lug 13 from the accommodating portion 15 side due to the positional relationship with the wire member 23 and the like. If it does in this way, compared with what is inserted from the outer side of the space between the lugs 13, the hook 4 can make the installation range of a movable lug small.

The operation of the movable lug 1 configured as described above will be described.
8 and 9 are partial longitudinal sectional views of the rear suspension member 9 showing a state where the missile 3 is mounted on the aircraft 5. FIG. 16 is a partial longitudinal sectional view of the rear suspension member 9 showing a state after the missile 3 is completely detached from the aircraft 5, and thus a state before being mounted on the aircraft 5.

First, the mounting of the missile 3 on the aircraft 5 will be described.
When the lugs 13 of the front suspension member 7 and the rear suspension member 9 are raised to the upright position (the state protruding from the outer surface of the missile 3) from the state of FIG. The load that presses the surface on the lug 13 side is eliminated. As a result, the stopper body 41 is rotated by the coil spring 45 so that the stopper portion 43 moves toward the lug 13, so that the stopper portion 43 engages with the lug protrusion 37. In this state, the stopper portion 43 supports the load to be rotated by the lug 13, that is, the direction of the force applied in the direction in which the lug protrusion 37 moves is substantially perpendicular to the perpendicular line passing through the stopper shaft 39 and perpendicular to the stopper portion 43. Therefore, the lug protrusion 37 and the stopper 43 are pressed against each other, and the lug 13 is held in the upright position.

In this state, the missile 3 is carried into the aircraft 5, the hook 4 is inserted into the opening of the lug 13, and the missile is attached to the aircraft 5. Thus, since the lug 13 is held in a state of protruding from the outer surface of the missile 3, labor for mounting the lug 13 on the hook 4 can be reduced.
Thereafter, the coupler 61 connects the first wire 57 and the second wire 59, and the wire member 23 connects the front suspension member 7 and the rear suspension member 9 to the aircraft 5.
In the present embodiment, the length of the wire member 23 is large enough to bring the arm main body 49 into a substantially upright position against the force that the free end of the arm main body 49 tends to move toward the accommodating portion 15 by the coil spring 55. It is said. At this time, as shown in FIG. 9, the drive arm 51 has its root portion engaged with the stopper drive member 47, and holds the stopper main body 41 so as not to rotate.

Next, the separation operation of the missile 3 from the aircraft 5 will be described.
FIGS. 10 and 11 are partial longitudinal sectional views of the rear suspension member 9 showing the state of the missile 3 in the initial fall immediately after the hook 4 of the aircraft 5 is detached from the lug 13.
When injecting the missile 3 from the aircraft 5, first, the hook 4 is detached from the lug 13.
At this time, the lug protrusion 37 and the stopper 43 are engaged, and the lug 13 is held in the upright position, so that the lug 13 does not rotate regardless of the movement of the hook 4. Thereby, the hook 4 can be reliably extracted from the lug 13.

When the hook 4 is extracted from the lug 13, the missile 3 moves (drops) downward from the aircraft 5 due to its weight, so that the tension on the wire member 23 attached to the aircraft 5 at one end increases, and the first The free end portion of the arm body 49 to which the wire 57 is attached is pulled to the rear side.
When the free end of the arm main body 49 is pulled rearward, the arm main body 49 rotates toward the rear about the drive shaft 53, so that the drive arm 51 attached integrally to the arm main body 49 has a distal end portion. Rotates to move downward.

  As the drive arm 51 rotates, the drive arm 51 pushes the stopper drive member 47 downward. Therefore, as shown in FIG. 11, the stopper body 41 has the stopper portion 43 around the stopper shaft 39 and the lug 13, that is, the lug protrusion. It is rotated in a direction away from the portion 37.

12 and 13 are partial longitudinal sectional views of the rear suspension member 9 showing a state in which the missile 3 has further dropped.
When the missile 3 further falls, the free end portion of the arm body 49 is pulled further rearward by the tension of the wire member 23, so that the driving arm 51 pushes the stopper driving member 47 further downward. As a result, the stopper main body 41 is further rotated in a direction in which the stopper portion 43 is separated from the lug projection portion 37, so that the stopper portion 43 is detached from the lug projection portion 37 as shown in FIG. 13.
At this position, the direction of tension of the wire member 23 substantially coincides with the extending direction of the arm main body 49, so that the rotation of the arm main body 49 stops.

When the stopper portion 43 is detached from the lug protrusion 37, there is no force to hold the lug 13 in the upright position, so the lug 13 is moved forward with the urging force of the lug coil spring 17 around the shaft member 33. Then, it rotates toward the storage unit 15 and is stored in the storage unit 15 so as not to protrude from the outer surface of the missile 3 as shown in FIG.
At this time, since the lug 13 presses the surface adjacent to the stopper portion 43 of the stopper body 41, the stopper body 41 rotates around the stopper shaft 39 to the position shown in FIG.

  If the missile 3 further falls after the lug 13 is accommodated in the accommodating portion 15, the tension acting on the wire member 23 increases. When this tension exceeds a predetermined load, the coupler 61 is separated, and the first wire 57 and the second wire 59 are separated, so that the missile 3 is completely separated from the aircraft 5. As described above, the missile 3 can be separated at the timing of the tension at which the coupler 61 separates. Therefore, the timing at which the missile 3 is separated can be set accurately. By adjusting the length of the wire member 23 or the magnitude of the predetermined load, the timing at which the tension applied to the wire member 23 becomes the predetermined load can be adjusted, so the timing at which the missile 3 is separated can be easily adjusted. can do.

  In the present embodiment, the coupler 61 that divides the wire member 23 is used, but the coupler 61 may not be used. In this case, when the tension of the wire member 23 increases, the wire member 23 is cut in the middle or at the attachment portions at both ends, so that the missile 3 can be separated from the aircraft 5.

  When the coupler 61 is separated, the tension of the first wire 57 disappears, so that the arm body 49 rotates forward around the drive shaft 53 by the biasing force of the coil spring 55. When the arm main body 49 rotates forward, the first wire 57 is pulled and accommodated in the missile 3 as shown in FIG. 16, so that adverse effects on the flight of the missile 3 can be suppressed.

Thus, since the missile 3 is separated from the aircraft 5 and dropped, the lug 13 is automatically and reliably accommodated in the accommodating portion 15, so that the air resistance by the lug 13 can be reduced safely and reliably. it can.
In addition, the movable lug 1 is rotatably installed so that the lug 13 is positioned in the accommodating portion 15 by the lug coil spring 17 at a predetermined position, and the stopper member 19 that positions the lug 13 at the protruding position and the stopper member 19. Since only the arm member 21 and the wire member 23 to be released are provided, a simple, small and lightweight structure can be obtained. For this reason, attachment to an aircraft can be performed easily.

  The present invention is not limited to the embodiment described above, and various modifications may be made without departing from the spirit of the present invention.

DESCRIPTION OF SYMBOLS 1 Movable lug 3 Missile 4 Hook 5 Aircraft 13 Lug 15 Accommodation part 17 Coil spring 19 for lugs Stopper member 21 Arm member 23 Wire member 37 Lug projection part 39 Stopper shaft 43 Stopper part 51 Drive arm 57 First wire 59 Second wire 61 Coupler B Axle perpendicular direction L Axle direction

Claims (7)

Attached to the outer surface of the flying body so as to be rotatable about an axis extending in a direction perpendicular to the axis of the aircraft, and has an opening for receiving a hook provided on the aircraft. A pair of lugs provided with
An accommodation portion that is provided before or after the axis direction in each of the lugs, and accommodates the lugs that have fallen to the flying body side so as not to protrude from the outer surface of the flying body;
A lug biasing member that constantly biases the lug so as to rotate toward the housing part;
A locking member that engages with a lug engaging portion provided on the lug and has a locking portion that holds the lug in a state protruding from the outer surface;
A wire member attached to the aircraft and moving the locking member by its tension so that the locking portion disengages the lug engaging portion;
A movable lug characterized by comprising:   The locking member is disposed at a lower portion of the lug on the housing portion side so that at least a part in a direction perpendicular to the axis of the lug is in contact with the lug, and is rotatably held around a locking axis extending in the direction perpendicular to the axis of the axis. The movable lug according to claim 1, wherein the latching portion is constantly biased so as to rotate toward the lug.   A drive member is provided that is movably attached to the flying body and has a drive portion that can be engaged with the locking member. Accordingly, the drive unit moves the locking member so that the locking unit releases the engagement with the lug engaging unit. The movable lug according to claim 1 or 2, .   The wire member connects a first wire attached to the locking member or the drive member, a second wire attached to the aircraft, and free ends of the first wire and the second wire. The movable lug according to any one of claims 1 to 3, further comprising a connection member that is separated when a tension greater than a predetermined load is applied. The drive member is rotatably supported around a drive shaft extending in a direction perpendicular to the machine axis, and the wire member is connected to one side across the drive shaft,
The distance from the said drive shaft to the attachment part of the said wire member is made larger than the distance from the said drive shaft to the part to which a drive part engages with the said locking member. Item 5. The movable lug according to Item 4.   The movable lug according to any one of claims 1 to 5, wherein the pair of lugs are installed so that the housing portions face each other. A flying body comprising the movable lug according to any one of claims 1 to 6.

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