JP3187212U - Aircraft disaster prevention launcher and aircraft - Google Patents

Abstract

An aircraft disaster prevention launcher and an aircraft that can move in the vertical direction without requiring a power source.
The other end 4 is attached to a lower part 12 of an aircraft, and the other end 4 is attached to a launcher 2 to which a flying object can be attached. The elastic body 16 is attached so as to be urged in the contracting direction, and the locking portion 19 is configured to be locked in a state where the telescopic arm portions 6 and 6 are contracted.
[Selection] Figure 1

Description

  The present invention relates to an aircraft disaster prevention launcher and an aircraft. Specifically, the present invention relates to an aircraft disaster prevention launcher mounted on a single propeller aircraft and an aircraft equipped with a disaster prevention launcher.

For example, in fire extinguishing by water discharge by a fire engine, there is a limit to the height of water discharge in a high-rise building or the like, so that fire may be extinguished using a fire extinguishing bomb.
In such a case, a fire extinguisher is filled with a fire extinguisher instead of an explosive and dropped from a helicopter.

  As described above, in the helicopter, if a fire extinguishing bullet is dropped while hovering over the fire occurrence site, the accuracy of hitting the fire occurrence site is improved. However, there is a risk that smoke will be trapped above the fire site and the visibility will be very poor, or that the helicopter will be very difficult to control due to the updraft.

  In addition, when a fire has occurred from the middle floor rather than the rooftop or top floor of a high-rise building, it is not possible to perform effective fire fighting activities simply by dropping a fire bomb from the sky.

  Therefore, it is conceivable that a launcher is attached to a single propeller aircraft such as a Cessna aircraft, and a rocket-type fire bomb is fired from the vicinity of the fire occurrence site to hit the middle floor, not the rooftop or the top floor of a high-rise building. ing.

  However, when a launcher is attached under the trunk of a single propeller aircraft, the propeller is positioned in front of the launcher, and there is a possibility that a fire extinguisher fired from the launcher will hit the propeller.

  Here, as this type of aircraft launcher, for example, there is one described in Patent Document 1. Specifically, as shown in FIG. 8, a launcher body 102 having a mechanism that can rotate 360 degrees in the horizontal direction and that can move up and down in the vertical direction is attached to the underside of the aircraft 101. 102 is equipped with flying bodies 103 one by one.

JP-A-6-281394

  However, in the launcher described in Patent Document 1, since the operation of the launcher is performed by the hydraulic pressure supply device, the weight of the launcher itself increases. For example, a jet aircraft with a large propulsive force does not impose a burden on the flight even if the weight of the launcher itself increases, but a propeller aircraft has a limit in the propulsive force, and it is quite suitable for a flight with a heavy launcher attached. It may be burdensome.

  The present invention was devised in view of the above points, and provides an aircraft disaster prevention launcher that can move in the vertical direction without requiring a power source and an aircraft equipped with the disaster prevention launcher. It is the purpose.

  In order to achieve the above object, an aircraft disaster prevention launcher according to the present invention has an extendable arm portion attached to a launcher having one end attached to the underside of the aircraft and the other end capable of attaching a flying object, An elastic body attached so as to urge the telescopic arm part in the contracting direction, and a locking part that can be locked in a state where the telescopic arm part is contracted.

  Here, it is possible to move the launcher downward from the aircraft's underbody by the telescopic arm part attached to the launcher where one end is attached to the underside of the aircraft and the other end can be attached to the flying object. Become.

Further, the launcher can be always positioned under the fuselage of the aircraft by the elastic body attached so as to urge the telescopic arm portion in the contracting direction.
For example, if a flying object is attached to the launcher, the telescopic arm will extend by the weight of the flying object and move the launcher downward, and after the flying object is fired, Thus, the telescopic arm can be contracted to move the launcher under the fuselage of the aircraft.

Further, the state where the telescopic arm part is expanded and contracted can be held by the locking part which can be locked when the telescopic arm part is contracted.
For example, by locking the telescopic arm part with the locking part expanded and contracted, by attaching the flying object to the launcher and firing the flying object, releasing the extended and contracting arm part with the locking part The telescopic arm can be extended by the weight of the flying object, and the launcher can be moved downward.

  In the aircraft disaster prevention launcher according to the present invention, the telescopic arm part is attached to the first arm part and the first arm part so as to be slidable in the longitudinal direction of the first arm part. When the second arm portion slides relative to the first arm portion, the second arm portion can be expanded and contracted.

  Further, in the aircraft disaster prevention launcher according to the present invention, when the telescopic arm portion has the first arm portion and the second arm portion that is connected to and supported by the first arm portion, The arm portion and the second arm portion can be expanded and contracted by rotating around the connecting pivot.

  In order to achieve the above object, an aircraft according to the present invention has a single propeller aircraft main body and one end attached to the underbody of the propeller aircraft main body, and the other end can be attached to a flying object. A telescopic arm portion attached to the launcher, an elastic body attached so as to urge the telescopic arm portion in the contracting direction, and a locking portion that can be locked in a state in which the telescopic arm portion is contracted With.

  Here, the launcher is mounted on the propeller aircraft by a single-engine propeller aircraft main body and a telescopic arm portion attached to a launcher that has one end attached to the underbody of the propeller aircraft main body and the other end capable of attaching a flying object. It is possible to move from below the trunk to the bottom of the propeller.

Further, the launcher can be always positioned under the fuselage of the aircraft by the elastic body attached so as to urge the telescopic arm portion in the contracting direction.
For example, if a flying object is attached to the launcher, the telescopic arm will extend due to the weight of the flying object and move the launcher from the underside of the propeller aircraft to the bottom of the propeller, and after the flying object has been launched It is possible to move the launcher below the fuselage of the aircraft by contracting the telescopic arm portion by the urging force of the elastic body.

Further, the state where the telescopic arm part is expanded and contracted can be held by the locking part which can be locked when the telescopic arm part is contracted.
For example, by locking the telescopic arm part with the locking part expanded and contracted, by attaching the flying object to the launcher and firing the flying object, releasing the extended and contracting arm part with the locking part The telescopic arm can be extended by the weight of the flying object, and the launcher can be moved from the underside of the propeller aircraft to the lower side of the propeller.

According to the aircraft disaster prevention launcher of the present invention, it is possible to move in the vertical direction without requiring a power source.
Further, according to the aircraft of the present invention, the launcher can be moved in the vertical direction from the underside of the aircraft without requiring a power source.

It is a front schematic diagram for demonstrating an example of the launcher for aircrafts to which this invention is applied. It is a side surface schematic diagram for demonstrating an example of the launcher for aircrafts to which this invention is applied. It is a cross-sectional schematic diagram for demonstrating an example of the expansion-contraction arm part of the launcher for aircrafts to which this invention is applied. FIG. 2 is a schematic diagram (A) showing a state in which a flying object is attached to an aircraft launcher to which the present invention is applied, and a schematic diagram (B) showing a state at the time of launching the flying object from the aircraft launcher to which the present invention is applied. Front schematic diagram for explaining another example of an aircraft launcher to which the present invention is applied (A), and front schematic diagram for explaining an operation state in another example of an aircraft launcher to which the present invention is applied (B). It is. Side surface schematic diagram for explaining still another example of an aircraft launcher to which the present invention is applied (A) and a side surface schematic diagram for explaining operational states in still another example of an aircraft launcher to which the present invention is applied ( B). They are a schematic side view (A) for explaining an example of an aircraft to which the present invention is applied and a schematic front view (B) for explaining an example of an aircraft to which the present invention is applied. It is a schematic diagram for demonstrating an example of the conventional aircraft launcher.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings.

<First Embodiment>
FIG. 1 is a schematic front view for explaining an example of an aircraft launcher to which the present invention is applied, FIG. 2 is a schematic side view for explaining an example of an aircraft launcher to which the present invention is applied, and FIG. It is a cross-sectional schematic diagram for demonstrating an example of the expansion-contraction arm part of the applied aircraft launcher.

  The aircraft launcher 1 shown here has a launcher 2 to which a flying object (not shown) such as a rocket can be attached, one end 3 attached to the launcher 2, and the other end 4 to an aircraft (not shown). .) Of the telescopic arm portion (6, 6) attached to the lower trunk 12.

  Here, the telescopic arm portions (6, 6) are formed by a plate-like first arm portion (7, 7) and a second arm portion (2) whose lateral length is substantially the same as the length of the launcher 2 in the longitudinal direction. 8, 8).

  The first arm portion 7 is formed with mooring groove portions (9, 9) whose both ends are bent in a U-shaped cross section, and further, both end portions (10, 10) are formed in the mooring groove portions (9, 9). ) Is inserted, the second arm 8 is attached.

  As a result, the second arm portion 8 can slide back and forth in the extending direction of the first arm portion 7, and as a result, the telescopic arm portion 6 can be expanded and contracted.

  In addition, one end of the first arm portion (7, 7) is connected to the both axial positions of the propeller (not shown) of the underarm 2 of the aircraft by a joint portion 11 so as to be parallel to the axial direction. It is pivotally supported.

  Also, one end of the wires (13, 13) is connected to the base end of the second arm portion (8, 8), and the other end is the lower trunk 12 in the extending direction of the first arm portion (7, 7). Are inserted into the wire insertion holes (14, 14) opened in.

  Further, pulleys (15, 15) are arranged in the body 5 in the vicinity of the wire insertion holes (14, 14), and the pulleys (15A, 15A) are arranged at substantially the center between the pulleys (15, 15). Is arranged.

  Further, an elastic body 16 formed of an elongated coil spring is disposed on the pulleys (15A, 15A).

  Here, the wires (13, 13) are attached to the elastic body pressing plate 17 moored at the upper end of the elastic body 16 in a state of passing through the elastic body 16 via the pulleys (15, 15) and the pulleys (15A, 15A). It is connected.

  Thereby, the second arm portion (8, 8) is configured to be held by the elastic body 16 in a state of being drawn into the first arm portion (7, 7) by the wire (13, 13). Yes.

The elastic body pressing plate 17 is connected to an operation wire 18 via a locking portion 19.
The operation wire 18 is formed by pressing the elastic body pressing plate 17 in a state in which the telescopic arm portions (6, 6) are contracted by operating the locking portion 19 with the operation wire 18 from a cockpit (not shown). It is set as the structure which can be made to latch.

  In addition, a launch plate 20 to which a flying object (not shown) is attached is provided on the lower surface of the launcher 2. The launch plate 20 is configured such that the launch angle of the flying object can be adjusted by rotating up and down as shown by the imaginary line in the drawing with the rear side of the aircraft (not shown) as the base end. Yes.

  Next, FIG. 4 (A) is a schematic diagram showing a state in which a flying object is attached to an aircraft launcher to which the present invention is applied, and FIG. 4 (B) is a diagram at the time of launching the flying object from the aircraft launcher to which the present invention is applied. It is a schematic diagram which shows a state.

  Here, as shown in FIG. 4A, the aircraft launcher 1 includes the second arm portion (8, 8) attached to the wires (13, 13) by the urging force of the elastic body 16 in the extending direction. Is pulled into the first arm (7, 7).

  As a result, the telescopic arm portions (6, 6) contract, and the telescopic arm portions (6, 6) contract by operating the locking portion 19 with the operation wire 18 to lock the elastic body pressing plate 17. It becomes possible to hold in a state.

  With the telescopic arm portions (6, 6) contracted in this manner, for example, the flying object 21 such as a rocket bullet filled with a fire extinguisher is attached.

  Next, as shown in FIG. 4B, when the flying object 21 is fired, the locking of the elastic body pressing plate 17 by the locking part 19 is released by the operation wire 18.

  As a result, the weight of the flying body 21 is applied to the elastic body pressing plate 17 so that the elastic body 16 is pushed down by the elastic body pressing plate 17 and contracts. As a result, the second arm portion (8, 8) attached to the wire (13, 13) is pulled out from the first arm portion (7, 7), and the telescopic arm portion (6, 6) is extended. It becomes a state.

  In this way, by launching the flying object 21 with the telescopic arm portions (6, 6) extended, in the case of a single-shot Cessna aircraft, it is possible to launch to a destination without hitting a propeller (not shown). Become.

  Furthermore, after launching the flying object 21, the second arm part (8, 8) attached to the wires (13, 13) by the urging force of the elastic body 16 in the extending direction becomes the first arm part (7 7) Returned to the original state by being drawn in.

  In the present embodiment, the first arm portion has a second arm portion that is slidably attached in the longitudinal direction of the first arm portion. There is no need for configuration.

  For example, any mechanism may be used as long as the elastic arm portion contracts by the urging force of the elastic body.

  In the aircraft launcher according to the present invention, the arm portion can be contracted using the biasing force of the elastic body without requiring a driving force such as hydraulic pressure.

Further, when the flying object is launched, it is possible to move to a position where the propeller does not become an obstacle due to the weight of the flying object.
Thereby, for example, a flying object such as a fire extinguisher can be mounted on a single-shot aircraft such as a Cessna aircraft.

<Another embodiment of the first embodiment>
FIG. 5A is a schematic front view for explaining another example of an aircraft launcher to which the present invention is applied, and FIG. 5B is a diagram for explaining an operation state in another example of an aircraft launcher to which the present invention is applied. It is a front schematic diagram for doing.

  The aircraft launcher 1 </ b> A shown here has a launcher 2 to which a flying object 21 such as a rocket can be attached, one end 3 attached to the launcher 2, and the other end 4 under the aircraft (not shown). 12 is composed of telescopic arm portions (6A, 6A) attached to 12.

  Here, the telescopic arm portions (6A, 6A) are composed of a first arm portion (7A, 7A) and a second arm portion (8A, 8A) whose one ends are connected to each other.

  Further, a launch plate 20 is provided on the lower surface of the launcher 2, and as shown in FIG. 2, the launch angle of the flying object is obtained by pivoting up and down with the rear side of the aircraft (not shown) as the base end. It can be adjusted.

  Further, the launcher 2 is connected to an elastic body 16A formed of a contracted coil spring between the lower body 12 and one end of the wire 13 while being inserted through the elastic body 16A. The end is inserted into a wire insertion hole 14 drilled in the lower trunk 12.

  A locking portion 19 is disposed at the other end of the wire 13 inserted into the body 15 in this manner, and an operation wire 18 for operating the locking portion 19 is connected thereto.

  Thus, the flying object 21 can be attached in a state where the telescopic arm portions (6A, 6A) are bent by locking the wire 13 with the locking portion 19.

  In the aircraft launcher 1A configured as described above, as shown in FIG. 5B, when the flying object 21 is fired, the locking of the wire 13 by the locking portion 19 is released by the operation of the operating wire 18. To do.

  Thereby, the elastic body 16A expand | extends because the weight of the flying body 21 is loaded to the elastic body 16A. As a result, the first arm portion (7A, 7A) and the second arm portion (8A, 8A) of the telescopic arm portion (6A, 6A) are extended downward.

  In this manner, by launching the flying object 21 with the telescopic arm portions (6A, 6A) extended, in the case of a single-shot Cessna aircraft, it is possible to launch to a destination without hitting a propeller (not shown). Become.

  Furthermore, after launching the flying object 21, the launcher 2 returns to the original state by the urging force of the elastic body 16A in the contraction direction.

  In the present embodiment, the first arm portion is configured to have the second arm portion that is connected and pivotally supported. However, such a configuration is not necessarily required.

  For example, any mechanism may be used as long as the elastic arm portion contracts by the urging force of the elastic body.

  6A is a schematic side view for explaining still another example of an aircraft launcher to which the present invention is applied, and FIG. 6B is an operational state in yet another example of an aircraft launcher to which the present invention is applied. It is a side surface schematic diagram for demonstrating.

  The aircraft launcher 1B shown here has a launcher 2 to which a flying object 21 such as a rocket can be attached, one end 3 attached to the launcher 2, and the other end 4 under the aircraft (not shown). 12 and the telescopic arm portions (6B, 6B) attached to 12.

  Here, the telescopic arm portions (6B, 6B) are composed of a first arm portion (7B, 7B) and a second arm portion (8B, 8B) whose one ends are connected to each other.

  Further, the flying object holding member 37 is provided on the lower surface of the launcher 2, and the flying object 21 is held by the flying object holding member 37.

  Further, the launcher 2 is connected to an elastic body 16B formed of a contracted coil spring between the lower body 12 and one end of the wire 13 while being inserted through the elastic body 16B. The end is inserted into a wire insertion hole 14 drilled in the lower trunk 12.

  A locking portion 19 is arranged at the other end of the wire 13 inserted into the body 5 in this way, and an operation wire 18 for operating the locking portion 19 is connected.

  Thus, the flying object 21 can be attached in a state in which the telescopic arm portions (6B, 6B) are bent by locking the wire 13 with the locking portion 19.

  In the aircraft launcher 1B having the above configuration, as shown in FIG. 6B, when the flying object 21 is fired, the locking of the wire 13 by the locking portion 19 is released by operating the operating wire 18. To do.

  Thereby, the elastic body 16B expand | extends because the weight of the flying body 21 is loaded to the elastic body 16B. As a result, the first arm portion (7B, 7B) and the second arm portion (8B, 8B) of the telescopic arm portion (6B, 6B) are extended downward.

  In this manner, by launching the flying object 21 with the telescopic arm portions (6B, 6B) extended, in the case of a single-shot Cessna aircraft, it is possible to launch to a destination without hitting a propeller (not shown). Become.

  Furthermore, after launching the flying object 21, the launcher 2 returns to the original state by the biasing force in the contraction direction of the elastic body 16B.

  In the aircraft launcher according to the present invention, the arm portion can be contracted using the biasing force of the elastic body without requiring a driving force such as hydraulic pressure.

Further, when the flying object is launched, it is possible to move to a position where the propeller does not become an obstacle due to the weight of the flying object.
Thereby, for example, a flying object such as a fire extinguisher can be mounted on a single-shot aircraft such as a Cessna aircraft.

<Second Embodiment>
FIG. 7A is a schematic side view for explaining an example of an aircraft to which the present invention is applied, and FIG. 7B is a schematic front view for explaining an example of an aircraft to which the present invention is applied.

  The aircraft 30 shown here is a single-engine light aircraft such as a Cessna aircraft. As shown in FIG. 7A, the fuselage 31, a main wing 32, a tail wing 33 provided on the fuselage 31, and a fuselage 31. And a propeller 34 provided at the tip of the head.

  Further, wheels 35 are disposed at both side positions of the main wing 32 and the rear end position of the fuselage 31, and a steering pit 36 is provided on the fuselage 31 on the main wing 32.

Here, the aircraft launcher 1 is attached to the lower trunk 12 under the control pit 36.
As shown in FIGS. 1 to 3, the aircraft launcher 1 has a launcher 2, one end 3 attached to the launcher 2, and the other end 4 attached to a lower trunk 12 of an aircraft (not shown). The telescopic arm portions (6, 6) are configured.

  The telescopic arm portions (6, 6) have plate-like first arm portions (7, 7) and second arm portions (8) whose lateral length is substantially the same as the length of the launcher 2 in the longitudinal direction. 8).

  The first arm portion 7 is formed with mooring groove portions (9, 9) whose both ends are bent in a U-shaped cross section, and further, both end portions (10, 10) are formed in the mooring groove portions (9, 9). ) Is inserted, the second arm 8 is attached.

  As a result, the second arm portion 8 can slide back and forth in the extending direction of the first arm portion 7, and as a result, the telescopic arm portion 6 can be expanded and contracted.

  In addition, one end of the first arm portion (7, 7) is connected to the both axial positions of the propeller (not shown) of the underarm 2 of the aircraft by a joint portion 11 so as to be parallel to the axial direction. It is pivotally supported.

  Also, one end of the wires (13, 13) is connected to the base end of the second arm portion (8, 8), and the other end is the lower trunk 12 in the extending direction of the first arm portion (7, 7). Are inserted into the wire insertion holes (14, 14) opened in.

  Further, pulleys (15, 15) are arranged in the body 15 near the wire insertion holes (14, 14), and the pulleys (15A, 15A) are arranged at substantially the center between the pulleys (15, 15). Is arranged.

  In addition, an elastic body 16 formed of a contracted coil spring is disposed on the pulleys (15A, 15A).

  Here, the wires (13, 13) are attached to the elastic body pressing plate 17 moored at the upper end of the elastic body 16 in a state of passing through the elastic body 16 via the pulleys (15, 15) and the pulleys (15A, 15A). It is connected.

  Thereby, the second arm portion (8, 8) is configured to be held by the elastic body 16 in a state of being drawn into the first arm portion (7, 7) by the wire (13, 13). Yes.

The elastic body pressing plate 17 is connected to an operation wire 18 via a locking portion 19.
The operation wire 18 is extended to the control pit 36 so that the locking portion 19 can be operated from the control pit 36.

  In this way, the elastic body pressing plate 17 can be locked in a state where the telescopic arm portions (6, 6) are contracted by operating the locking portion 19 from the control pit 36 with the operation wire 18. Become.

  In the aircraft of the present invention configured as described above, as shown in FIG. 7A, in the state where the telescopic arm portions (6, 6) are contracted, for example, a flying object such as a rocket bullet filled with a fire extinguisher. 21 is installed.

In this way, the flying object 21 flies to the destination with the aircraft launcher 1 attached.
Here, when the flying object 21 is fired, the locking of the wires (13, 13) by the locking portion 19 is released by the operation of the operation wire 18, as shown in FIG.

  Thereby, the elastic body 16 contracts because the weight of the flying body 21 is loaded on the elastic body 16. As a result, the second arm portion (8, 8) attached to the wire (13, 13) is pulled out from the first arm portion (7, 7), and the telescopic arm portion (6, 6) is extended. It becomes a state.

  Next, as shown in FIG. 7B, the propulsion direction of the flying body 21 becomes the downward direction of the propeller 34 by the flying body 21 moving downward in the fuselage 31 by the telescopic arm portions (6, 6). It becomes possible for the propeller 34 to be fired without being obstructed at the time of launch.

  Further, after launching, the telescopic arm portions (6, 6) are contracted by the urging force of an elastic body (not shown) and the launcher 2 returns to the original position, so that the flight can be performed without any trouble.

  In this embodiment, the telescopic arm part having a first arm part and a second arm part slidably mounted in the longitudinal direction of the first arm part as an aircraft launcher will be described in detail. However, such a configuration is not necessarily required.

  For example, any mechanism may be used as long as the telescopic arm portion is contracted by the urging force of the elastic body, such as having the second arm portion connected and supported on the first arm portion. .

  In the <first embodiment>, <other embodiments of the first embodiment>, and <second embodiment>, the case where the flying object is a single body will be described in detail, but it is not necessarily a single body. There is no need for this, and it is desirable to adopt a configuration that allows a plurality of projectiles to be attached to the launcher, or a configuration that suits the situation, such as a multi-row rocket launcher.

  In the aircraft according to the present invention, it is possible to realize measurement and simplification of the launcher by attaching an aircraft launcher that uses the biasing force of an elastic body without requiring a driving force such as hydraulic pressure.

Further, when the flying object is launched, it is possible to move to a position where the propeller does not become an obstacle due to the weight of the flying object.
Thereby, for example, a flying object such as a fire extinguisher can be mounted on a single-shot aircraft such as a Cessna aircraft.

DESCRIPTION OF SYMBOLS 1, 1A, 1B Aircraft launcher 2 Launcher 3 One end 4 Other end 5 Fuselage body 6, 6A, 6B Telescopic arm part 7, 7A, 7B First arm part 8, 8A, 8B Second arm part 9 Mooring groove part DESCRIPTION OF SYMBOLS 10 Both ends 11 Joint part 12 Body lower part 13 Wire 14 Wire insertion hole 15, 15A Pulley 16, 16A, 16B Elastic body 17 Elastic body presser plate 18 Operation wire 19 Locking part 20 Launching board 21 Flying body 30 Aircraft 31 fuselage 32 Main wing 33 Tail 34 Propeller 35 Wheel 36 Control pit 37 Flying object holding member

Claims (4)

One end is attached to the underside of the aircraft, and the other end is a telescopic arm part attached to a launcher capable of attaching a flying object,
An elastic body attached so as to bias the telescopic arm portion in the contraction direction;
An aircraft disaster prevention launcher comprising: a locking portion that can be locked in a state where the telescopic arm portion is contracted. The telescopic arm part is
A first arm part;
The aircraft disaster launcher according to claim 1, further comprising a second arm portion slidably attached to the first arm portion in the longitudinal direction of the first arm portion. The telescopic arm part is
A first arm part;
The aircraft disaster prevention launcher according to claim 1, wherein the first arm portion includes a second arm portion that is pivotally connected to the first arm portion. A single propeller aircraft body,
A telescopic arm portion attached to a launcher having one end attached to the underside of the propeller aircraft main body and the other end capable of attaching a flying object;
An elastic body attached so as to bias the telescopic arm portion in the contraction direction;
An aircraft comprising: a locking portion that can be locked in a state in which the telescopic arm portion is contracted.

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