JP2010181318A - Aircraft leg drop tester - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an aircraft leg drop tester for implementing a drop test without a trouble if an aircraft leg is a small leg having a small requirement of a plumb load. <P>SOLUTION: A leg support 20 is combined with a plumb, downwardly couples and fixes the aircraft leg 10, and vertically and movably supports it within a guide window 30. A support lifting means 40 with a coupling/releasing mechanism is provided within the guide window 30 along with the leg support 20. The support lifting means 40 downwardly couples the leg support 20, lifts the leg support 20 within the guide window 30, releases the leg support 20 from a predetermined level within the guide window 30 to drop, and includes an electromagnet 42 as the coupling/releasing mechanism of the leg support 20 for upwardly sucking the leg support 20. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a drop test apparatus used for performance / strength tests of aircraft legs.

  Conventionally, a drop test has been conducted as one of the performance and strength tests of aircraft legs. The structure of the test equipment used for the aircraft leg drop test is almost the same. The basic structure of a conventional drop test apparatus will be described below. The test apparatuses described in Patent Documents 1 and 2 also adopt this basic structure.

  An aircraft leg drop test apparatus basically includes the following three members. The first is a weight-supporting leg support that connects and fixes the aircraft legs downward, the second is a guide frame that supports the leg support so that it can move vertically, and the third is a leg support. It is a support raising / lowering means with a connection / release mechanism that is connected downward to raise and lower the inside of the guide frame and release and drop the leg support from a predetermined level in the guide frame.

  In the test, the aircraft leg to be strength tested is connected and fixed to the lower surface of the leg support. The leg support also serves as a weight. If the weight of the weight is insufficient with the leg support alone, the weight is separately mounted on the leg support. The leg support whose weight has been adjusted is connected to the lower part of the support lifting / lowering means, and is raised to a predetermined height in the guide frame by the support lifting / lowering means. Release the leg support from the support lifting means in the raised position. The released leg support naturally falls with the aircraft legs. As a result, the aircraft legs are subjected to an impact load accompanying a drop collision, and the shock absorption characteristics are investigated.

  There are various types of aircraft legs used for such a drop test, and various types of test equipment have been developed accordingly. As for a test apparatus for testing a large aircraft leg, if the test apparatus is enlarged and the weight load is insufficient, a weight may be separately mounted on the leg support as described above. It is easy to increase the weight load.

  However, it is not easy to reduce the weight load. This is because even if the test equipment is downsized, it is necessary for the leg support to have rigidity that can support the aircraft leg reliably and not to be deformed even when it is dropped. This is because there is a limit to reduction and weight reduction. Because of this limitation, when testing ultra-compact aircraft legs such as legs for unmanned airplanes, even if the test equipment is downsized, the necessary weight load may be exceeded only by the weight of the leg support, Depending on the type of aircraft leg, the test itself may not be possible.

  Incidentally, when a drop test of an aircraft leg is performed by a mass adjustment method, about half of the weight of the leg is assigned as a weight load. For example, the leg weight of an ultra-small leg such as an unmanned airplane is several tens of kg, the weight load required for the drop test is only several tens of kg, and the weight of the leg support is within several tens of kg. Due to the various restrictions, it is very difficult at present.

JP 2002-174573 A JP 2008-216160 A

  An object of the present invention is to provide an aircraft leg drop test apparatus capable of performing a drop test without any trouble even in the case of an ultra-compact leg having a small weight load requirement value.

  In order to achieve the above object, the present inventor has reviewed the factors for inhibiting the size reduction and weight reduction of the leg support when the aircraft leg drop test apparatus is miniaturized from various viewpoints. As a result, the following facts were found.

  If the height of the leg support is secured, the mechanical strength can be secured even if either the width or the depth is reduced. However, in the current leg support, it is difficult to reduce the width and depth. There are two factors that obstruct the width and depth of current leg supports, one of which is to secure the dimensions required for attachment determined by the legs, and the other is that the leg supports are at a predetermined level within the guide frame. More specifically, it is in a support / lifting mechanism for connecting and releasing the leg support below the support lifting / lowering means and for releasing from the lifting / lowering means.

  One of the connection / release mechanisms is described in detail in Patent Document 2. This mechanism includes a pair of rotating hooks attached to the lower surface of the support lifting / lowering means, a hook synchronous rotating mechanism using a pair of links on both sides, and an actuator. Since the leg support is in the shape of a heel frame that combines aggregates, the support lifting and lowering means also has a shape that combines the aggregates into a rectangle, and the connecting and releasing mechanism of the rotary hook type is easy to incorporate, On the other hand, the connecting / releasing mechanism limits the reduction in the width and depth of the leg support.

  Therefore, the present inventor sought a new connection / release mechanism to replace the rotary hook type and investigated and examined the suitability for a small device. As a result, the electromagnet connection / release mechanism, commonly known as rifmag (trade name), can secure the necessary and sufficient suction force to hold and connect the leg support even if the suction surface is reduced. As a result, it has been found that the width and depth of the leg support can be made significantly smaller than before, and that the leg support can be easily connected and released by demagnetization and demagnetization.

  The aircraft leg drop test device of the present invention was developed on the basis of such knowledge, and supports a weight support combined with and fixed to the aircraft leg downward, and the leg support movably in the vertical direction. And a support body lifting / lowering means with a connecting / releasing mechanism for connecting and lowering the leg support downward to raise and lower the inside of the guide frame and releasing and dropping the leg support from a predetermined level in the guide frame. The support lifting / lowering means includes an electromagnet that is attracted to the leg support from above as a connecting / releasing mechanism for the leg support.

  In the aircraft leg drop test apparatus of the present invention, the leg support is pulled up to a predetermined height in the guide frame by attracting the leg support with the electromagnet provided in the support lifting / lowering means and operating the lifting / lowering means. . If the electromagnet is demagnetized in this state, the leg support is released and falls. That is, the leg support can be connected and released by magnetizing and demagnetizing the electromagnet by electrical remote operation.

  An electromagnet called rifmag exerts a large attracting force on a small attracting surface. By using this as a connecting and releasing mechanism, the width and depth of the leg support can be reduced, and the weight can be reduced. be able to. Therefore, an appropriate weight load can be applied even when a drop test is performed on an ultra-small aircraft leg used for an unmanned aerial vehicle. For example, the suction surface of a riff mug (trade name) having a maximum lifting force of 150 kg is a circle having a diameter of about 200 mm. Since the maximum lifting force is indicated by 1/4 of the maximum adsorption force, the maximum adsorption force reaches 600 kg even with a circular adsorption surface having a diameter of 200 mm.

  If an electromagnet is used as a connecting / releasing mechanism for the leg support, the support lifting / lowering means can be substantially composed of this electromagnet and a winch type elevator that lifts and lowers the electromagnet. Is greatly simplified. The remote operation mechanism is also very simple because it only needs to perform up and down operation by magnetizing and demagnetizing the electromagnet, hoisting and unwinding the elevator.

  An adsorption plate made of a magnetic material is preferably provided on the upper surface of the leg support so as to face the electromagnet. By doing so, the attractive force of the electromagnet can be maximized.

  The aircraft leg drop test apparatus according to the present invention connects the leg support downward and supports it at a predetermined height in the guide frame. By using an adsorbing electromagnet, the lateral width and depth of the leg support can be reduced while reducing the weight load while ensuring the mechanical strength of the leg support, so there is no problem even in the case of a small leg with a small weight load requirement. A drop test can be performed. In addition, since the structure of the support lifting / lowering means and the remote control mechanism can be simplified, it is possible to obtain an economic effect more than the cost reduction due to the downsizing.

It is a front view of an aircraft leg drop test device showing an embodiment of the present invention. FIG. 2 is a side view of the aircraft leg drop test device, and is an arrow B view in FIG. 1. FIG. 2 is a plan view of the aircraft leg drop test apparatus, and is an A arrow view in FIG. 1.

  Embodiments of the present invention will be described below with reference to FIGS.

  As shown in FIGS. 1 to 3, the aircraft leg drop test apparatus of the present embodiment is used for a drop test of an aircraft leg 10 and is suitable for a drop test of a small aircraft leg 10. 10 is set to the drop test device in the front-rear direction.

  This drop test apparatus includes a leg support 20 that fixes an aircraft leg 10 to be dropped, a portal guide frame 30 that supports the leg 10 so as to be movable in the vertical direction, and the leg support 20 as a guide frame. And a support lifting / lowering means 40 that is suspended and supported by 30 and lifted and dropped to a predetermined level.

  The leg support 20 has a rectangular parallelepiped main body 21 in which aggregates are combined, and a right-triangular subframe 22 protruding rearward. The rectangular parallelepiped main body 21 is configured in a vertically long shape in which the width and depth are limited in order to ensure strength and reduce weight. The sub-frame 22 is an attachment attached to the rear surface of the main body 21 in order to set the aircraft leg 10 to be tested facing forward and backward. By attaching the subframe 22, the lower surface of the leg support 20 is a rectangle that is narrow in the side and long in the depth direction. An aircraft leg 10 to be tested can be attached to the rectangular lower surface of the leg support 20, and a circular suction plate 23 made of a magnetic material is attached to the upper surface of the leg support 20 (the upper surface of the main body 21). It has been.

  The leg support 20 also serves as a weight, and the weight of the weight can be increased by setting the weight of the leg support 20 to the minimum weight and mounting the weight separately. The sub-frame 22 can be replaced with a different shape depending on the type of the aircraft leg 10 to be dropped.

  The gate-shaped guide frame 30 includes a pair of left and right main frames 31 and 31 configured by combining aggregates, and a gate-shaped subframe 32 attached over the main frames 31 and 31. ing. A pair of vertical straight guides 33 and 33 are attached to the opposing surfaces of the main frames 31 and 31 so as to face each other. The pair of linear guides 33, 33 support the leg support 20 so as to be movable in the vertical direction between the left and right main frames 31, 31. A base 50 for receiving a collision load of the aircraft leg 10 attached to the lower surface of the leg support 20 is installed on the base between the main frames 31 and 31. The pedestal 50 has a function of measuring a collision load.

  The lifting / lowering stroke of the leg support 20 by the linear guides 33 and 33 is supported even when the aircraft leg 10 connected to the lower side of the leg support 20 is in contact with the pedestal 50, and the aircraft leg 10 is lifted to the upper limit. The leg support 20 is set so as to be supported even when it is pulled up to the level.

  The support lifting / lowering means 40 includes an elevator 41 suspended from the central portion of the portal subframe 32 in the guide frame 30 and an electromagnet 42 suspended from the elevator 41. The elevator 41 is a winding / rewinding device called a winch, and the electromagnet 42 is suspended from a hook at the lower end of a wire hanging from the device. The elevator 41 raises the electromagnet 42 by winding the wire with the motor, and lowers the electromagnet 42 by rewinding the wire with the motor.

  The electromagnet 42 is a thick disk-shaped magnetic adsorption device called a riffmag (trade name), and constitutes a connection / release mechanism for the leg support 20. That is, the electromagnet 42 is magnetized when the power is turned on, and in this state, the leg support 20 is connected downward by adsorbing the circular lower surface, which is the adsorption surface, to the adsorption plate 23 of the leg support 20. Further, when the power is turned off, the demagnetization state is established, and the leg support 20 is released in this state. The circular magnetized surface formed on the lower surface of the electromagnet 42 has the same diameter as the circular attracting plate 23 attached to the upper surface of the leg support 20.

  Next, the usage method, function, and superiority of the aircraft leg drop test device of the present embodiment will be described.

  In order to secure a predetermined weight load, another weight is appropriately mounted on the leg support 20 as necessary. Before and after this, the electromagnet 42 in the support lifting / lowering means 40 is turned on, and the suction surface thereof is attracted to the suction plate 23 of the leg support 20. After adjustment of the weight load and adsorption of the leg support 20 are finished, the elevator 41 in the support lifting / lowering means 40 is operated until the space for mounting the aircraft leg 10 is secured under the leg support 20. The support 20 is raised. Then, the aircraft leg 10 is attached to the lower surface of the leg support 20 in the front-rear direction.

  When the attachment of the aircraft leg 10 is completed, the aircraft leg 10 is held at the test height by operating the elevator 41 and raising the leg support 20 while the leg support 20 is attracted by the electromagnet 42. Thereafter, the electromagnet 42 is switched from the magnetized state to the demagnetized state. As a result, the leg support 20 is released from the support lifting / lowering means 40 and naturally falls to cause the lower aircraft leg 10 to collide with the base 50. Before the aircraft leg 10 is raised to the test height, a rotating drum (not shown) may be brought into rolling contact with the wheels of the aircraft leg 10 to provide rotation in the traveling direction during landing.

  In this way, a drop test assuming landing of the aircraft leg 10 is performed.

  Here, in the aircraft leg drop test apparatus of the present embodiment, the electromagnet 42 is used as a connection / release mechanism in the support lifting / lowering means 40. The electromagnet 42 has a smaller magnetized surface than the magnetized force. For this reason, the width and depth of the main body 21 of the leg support 20 can be reduced. For example, the weight load required for a drop test of a leg for a small machine is several tens of kg. In order to achieve this, the width and depth of the leg support 20 are required to be within 1 m, and the suction surface of the riff mug (trade name) having a maximum lifting force of 150 kg (maximum suction force of 600 kg) is the diameter. Since it is a circle of 200 mm, it is easy to reduce the width and depth of the leg support 20 to 1 m or less, and further to several tens of cm or less.

  Further, the support raising / lowering means 40 is basically composed of an elevator 41 called a winch and an electromagnet 42 called a riff mag (trade name) suspended from the elevator.

  Regarding the operability, the connection / release operation of the leg support 20 by the support lifting / lowering means 40 is performed by the on / off operation of the electromagnet 22, so that it is very simple, and the lifting and lowering of the aircraft leg 10 and the leg support 20 is performed. Is easily performed by the elevator 41. Therefore, the operability of the aircraft leg drop test device of this embodiment is also good.

  In this embodiment, the aircraft leg 10 to be dropped is set on the leg support 20 in the guide frame 30 with the front and back facing, but a configuration in which the aircraft leg 10 is set sideways is also possible. In the case of this configuration, the leg support 20 is horizontally long, and accordingly, the space between the main frames 31 and 31 of the guide frame 30 also expands.

DESCRIPTION OF SYMBOLS 10 Aircraft leg 20 Leg support body 21 Main body 22 Sub frame 23 Suction plate 30 Guide frame 31 Main frame 32 Sub frame 33 Linear guide 40 Support body raising / lowering means 41 Elevator (winch)
42 Electromagnet 50 Pedestal

Claims (3)

A weight-supporting leg support that connects and fixes the aircraft legs downward, a guide frame that supports the leg supports so as to be movable in the vertical direction, and guides the legs support downward to move up and down in the guide frame. And a support lifting / lowering means with a connection / release mechanism for releasing and dropping the leg support from a predetermined level in the frame,
The aircraft leg drop test apparatus, wherein the support lifting / lowering means includes an electromagnet that is attracted to the leg support from above as a leg support connecting / releasing mechanism.   2. The aircraft leg drop test apparatus according to claim 1, wherein the support lifting / lowering means includes a winch type lift that suspends and lifts an electromagnet. 3. The aircraft leg drop test device according to claim 1 or 2, wherein the leg support includes an adsorption plate made of a magnetic material on an upper surface.

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