JP2009174752A - Holding device and flying object - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a simple expansion structure capable of thinning widths of expansion wings of a compact flying object, and not using a complicated mechanism such as a lock pin and a torsion bar. <P>SOLUTION: In this flying object 1 having the expansion wings 4 supported by a launcher 7 in a state that the expansion wings 4 are folded, and expanding by being released from the support by the launcher 7, this holding device comprises fixing members 3 of which one end is fixed to a barrel body of the flying object 1, and the other end is applied as an expansion shaft 5 to which one end of each expansion wing 4 is rotatably mounted, a rotating shaft 8 orthogonal to the expansion shaft 5, holding members 10 having fitting portions 11 of each of which one end is rotatably mounted on the fixed member 3, and the other end is fitted to a wing end of the expansion wing 4, and elastic members 9 mounted on the rotating shaft 8, energizing the fitting portion 11 to a position separating from the expansion wing 4, fitted to the wing end of the expansion wing 4 by a self-restoring force acting when released from the external support, and expanding the expansion wing 4 to a fitting position. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a holding device for a deployment wing and a flying body including the holding device in a small flying body having a deployment wing.

  Conventionally, when a flying object is stored in a launcher, in order to increase the efficiency of storing the flying object per unit area, the accommodation area of the launcher may be reduced. In that case, the wing attached to the flying body is a folding wing composed of a fixed wing that is fixed to the flying body and a wing that can be bent with the wing tip of the fixed wing as a bending axis, and the wing is bent. And store in the launcher.

  As a method of deploying the expansion blade after the flying object comes out of the launch tube, for example, the expansion blade is rotated around the bending axis by the expansion mechanism such as a torsion bar provided on the bending shaft and expanded. There is a way.

  Further, as a method for holding the expanded wing, a lock pin built in the fixed wing is used. In other words, the lock pin is held inside the fixed wing by the hinge of the folding shaft until the expansion blade is deployed, and when the expansion blade is deployed, the lock pin is attached to the hinge by the restoring force of the spring attached to one end of the lock pin. The extending wing is held by penetrating the opened hole and reaching the lock hole formed in the expanding wing (see, for example, Patent Document 1).

Japanese Patent Laid-Open No. 10-141896 (pages 3 to 4, FIG. 4)

  Here, for example, in the case of a small flying body having an overall length of several hundred mm (millimeters) and a diameter of about several tens of millimeters, the deployment wing is reduced in size and weight in order to increase the range of the flying object. There is a need. In that case, in order to reduce the air resistance in the axial direction, it is preferable to make the width of the deployed wing viewed from the axial direction thin, for example, about several mm.

  However, if the width of the deployment wing is kept thin, the lock pin and the diameter of the spring attached to one end of the lock pin must be reduced, making it difficult to manufacture the lock pin mechanism. Further, when the spring diameter is reduced, it is difficult to obtain an elastic force sufficient to allow the lock pin to penetrate the hinge.

  Even if a small lock pin mechanism can be built into the fixed wing, the diameter of the lock pin is small, so the deployment wing cannot be held by the aerodynamic load received by the wing surface of the deployment wing during flight. There is a possibility of bending with the lock pin.

  In addition, when the deployment blade is held using a lock pin with a conventional diameter ignoring the width of the deployment blade viewed from the axis direction, the portion where the lock pin penetrates becomes a deployment blade having a bulge, and the aerodynamic characteristics for the deployment blade There is also a problem that there is a risk of deterioration, and that the deployment blade itself has a complicated shape, making it difficult to manufacture.

  The present invention has been made to solve such problems, and has an object of providing a holding device outside the deployment blade and further deploying and holding the deployment blade by deploying the deployment blade by the holding device. To do.

The holding device according to the present invention includes:
In a flying body having a deployment wing that is deployed to the outside in a state where the deployment wing is folded and opened by the release of the external support,
One end is fixed to the body of the flying body, and a fixing member to which one end of the deployment wing is rotatably attached with the other end facing the one end as a deployment axis;
A rotation axis orthogonal to the deployment axis;
One end is rotatably attached to the fixed member, and the other end is a holding member having a fitting portion that fits the blade tip of the deployment wing,
Provided on the rotating shaft, urges the fitting portion to a position away from the deployment blade, and causes the fitting portion to move to the blade tip of the deployment blade by its own restoring force that acts by opening the external support. And an elastic member that expands the deployment wing to the engagement position,
It is provided with.

  According to the present invention, since the holding device is provided outside the deployment blade, it is not necessary to manufacture a small lock pin mechanism or a deployment blade having a complicated shape. Further, it is not necessary to provide a developing device such as a torsion bar on the developing shaft.

Embodiment 1 FIG.
Embodiment 1 of the present invention will be described with reference to the drawings. FIG. 1 is a diagram showing a state before a deployment blade is deployed and a state where the deployment blade is deployed and held using the retention device of the present invention in a flying object having the retention device of the present invention. FIG. 2 is a view showing a state in which the flying wing is folded and the flying object is stored in the launch tube. FIG. 3 is a diagram for explaining that the deployment blade is deployed using the holding device of the present invention. FIG. 4 is a view showing a state in which the developing blade is held using the holding device of the present invention.

  Fig.1 (a) is a figure which shows the state before an expansion | deployment blade | wing expand | deploys. FIG. 1B is a diagram showing a state where the deployment blade 4 is held by the holding member 10 after being deployed. As shown in FIG. 1, the fixing member 3 is attached to the body of the flying body 1. For example, one end of the fixing member 3 is fixed to the body of the flying body 1 using the stopper 2. The deployment blade 4 is attached to the other end of the fixing member 3 so as to be rotatable by a hinge 6. Further, a holding member 10 having a fitting portion with which the developing blade 4 is fitted is attached to the fixing member 3.

  FIG. 2 is a view showing a state in which the flying wing 4 is folded and the flying object 1 is housed in the launch tube 7, as seen from the white arrow A in FIG. As shown in FIG. 1, one end of the fixing member 3 is fixed to the body of the flying body 1. Further, the other opposite end of the fixing member 3 is a deployment shaft 5 as shown in FIG. 2, and one end of the deployment blade 4 is attached to be rotatable using a hinge 6.

  Further, as will be described later, one end of the holding member 10 is on the blade surface side of the deployment blade 4 with respect to the fixed member 3 from the extension line of the blade tip of the deployment blade 4 that is not opposed to the deployment shaft 5. It is displaced and attached to the rotation shaft 8 at a position orthogonal to the surface of the deployment shaft 5 and the fixed member 3 on which it rotates.

  Further, an elastic member is attached with the rotary shaft 8 as the center, and the holding member 10 is rotated by the restoring force of the elastic member to expand and hold the deployment blade 4. As the elastic member, for example, a torsion spring (spring steel) wound around the rotating shaft 8 or a torsion bar attached in the axial direction of the rotating shaft 8 may be used. In the following description, the torsion spring 9 is used as the elastic member.

  As shown in FIG. 2, as a method of folding the deployment blade 4 and setting the flying body 1 to the launch tube 7, for example, the holding member 10 is positioned away from the blade tip of the deployment blade 4 that is not opposed to the deployment shaft 5. In a state where the deployment blade 4 is bent from the deployment shaft 5, the flying body 1 is temporarily fixed to the flying body 1 with a tape or the like, and the flying body 1 is set on the launch tube 7. After the flying body 1 is set, the temporary fixing tape may be removed. In the state where the flying body 1 is housed in the launch tube 7, even if the temporarily fixed tape is removed, the deployment blade 4 can be restrained from being deployed on the inner wall of the launch tube 7 as shown in FIG. 2. Thus, the deployment wing 4 of the flying body 1 is supported by the launch tube 7 (outside) in a folded state, and the deployment wing 4 is ejected from the launch tube 7 so that the deployment wing 4 becomes the launch tube. 7 is released from the support and unfolds.

  The material of the fixing member 3 and the deployment blade 4 may be aluminum. The material of the hinge 6, the stopper of the holding member 10 at the rotating shaft 8, and the torsion spring 9 may be iron. However, stainless steel may be used when it is desired to ensure the strength of the hinge 6, the holding member 10, and the torsion spring 9. The material of the holding member 10 may be aluminum. However, stainless steel may be used to secure the strength of the holding member 10.

  FIG. 3 is a diagram for explaining the deployment of the deployment blade 4 using the holding member 10, and FIG. 3A is viewed from the white arrow E in FIG. 2. FIG. 3B shows the broken line portion of FIG.

  As shown in FIG. 3A, one end of the holding member 10 is on the blade surface side of the deployment blade 4 from the extension line of the blade tip of the deployment blade 4 that is not opposed to the deployment shaft 5 with respect to the fixed member 3. It is displaced from the deployment shaft 5 and is pivotably attached to the rotation shaft 8 at a position orthogonal to the deployment shaft 5 and the surface of the fixing member 3 on which the deployment shaft 5 rotates. A torsion spring 9 is attached with the rotary shaft 8 as the center. The torsion spring 9 is joined to the holding member 10 so as to rotate the holding member 10 about the rotation shaft 8 by the restoring force of itself.

  When the flying body 1 is accommodated in the launch tube 7, the fitting portion 11 of the holding member 10 is spread to a position away from the blade tip of the deployment blade 4 as shown in FIG. When the flying body 1 comes out of the launch tube 7, the restoring force of the torsion spring 9 acts, and the holding member 10 rotates about the rotation shaft 8 as an axis as shown in FIG. When the holding member 10 is rotated, a contact force is applied to the folded deployment blade 4 as shown in FIG. 3B, and a force for pushing up the deployment blade 4 by the restoring force of the torsion spring 9 acts. With this force, the deployment blade 4 is deployed.

  As shown in FIG. 3A, when the deployment blade 4 is pushed up using the holding member 10, the deployment blade 4 comes into contact with the holding member 10 so that the holding member 10 is pushed up smoothly without being caught by the deployment blade 4. The part (fitting part 11) may be curved or chamfered. Further, if possible, the expanding blade 4 may be tapered so that the holding member 10 can be pushed up smoothly.

  4 is a view showing a state in which the deployment blade 4 is held using the holding member 10, and FIG. 4 (a) is a view as seen from the white arrow D in FIG. 1, and FIG. ) Is seen from the white arrow C in FIG. The other end of the holding member 10 having one end attached to the rotating shaft 8 has a fitting portion 11 as shown in FIG. When the deployment blade 4 is deployed, the deployment blade 4 is deployed to a position where the fitting portion 11 is fitted to the deployment blade 4 by rotating the fitting portion 11 of the holding member 10 in contact with the deployment blade 4.

  When the deployment blade 4 is deployed, the deployment blade 4 is held by fitting the fitting portion 11 of the holding member 10 so as to contact the blade tip of the deployment blade 4 as shown in FIG.

  For example, when the deployment blade 4 is held by holding the lock pin without changing the thinness of the width in the deployment shaft 5 direction so as not to deteriorate the aerodynamic characteristics of the deployment blade 4 in the deployment shaft 5 direction, for example, When the thickness of the deployment blade 4 viewed from the direction is about several millimeters, the diameter of the lock pin and the spring serving as the power for penetrating the lock pin must be reduced. However, as shown in FIG. 4A, an aerodynamic load is applied to the deployment blade 4 with respect to the blade surface of the deployment blade 4. Therefore, the aerodynamic load applied to the blade surface of the deployment blade 4 cannot be received and the lock pin may be broken.

  Further, if the diameter of the spring serving as the driving force for penetrating the lock pin 12 and the lock pin 12 is left as is, as shown in FIG. It becomes a complicated shape with a bulge in the lock pin penetration part. In this case, although the aerodynamic load applied to the blade surface of the deployment blade 4 can be received, the shape of the deployment blade 4 becomes complicated, and the aerodynamic characteristics of the deployment blade 4 are deteriorated.

  However, as shown in FIG. 4, the fitting portion 11 of the holding member 10 receives and aerodynamic load on the blade surface of the deployment blade 4 by fitting and holding the deployment blade 4 as shown in FIG. It becomes possible. Further, since the shape of the deployment blade 4 is not complicated, it is possible to prevent the aerodynamic characteristics of the deployment blade 4 from being deteriorated.

  3 and 4, the holding member 10 is provided at both ends of the deployment blade 4, but may be provided only at one end of the deployment blade 4 as long as the deployment blade 4 can be deployed and held.

  By providing the holding device 10 outside the deployment blade 4 as in the present invention, there is no need to hold the lock pin through the deployment blade 4, so that a small lock pin mechanism or a lock pin penetration location is inflated. Therefore, it is not necessary to manufacture the deployment blade 4 having a complicated shape, and the holding device 10 and the deployment blade 4 can be easily manufactured.

  The aerodynamic load received by the blade surface of the deployment blade 4 can be received by the holding device 10 provided outside. Further, since the shape of the deployment blade 4 is not complicated, it is possible to prevent the aerodynamic characteristics of the deployment blade 4 from being deteriorated.

  Furthermore, by deploying the deployment blade 4 by the holding device 10, it is not necessary to provide a deployment device such as a torsion bar on the deployment shaft 5.

  Further, as a configuration for assisting the deployment of the deployment blade 4 by the holding member 10, as shown in FIG. 6, a magnetic body, for example, a magnet 13 may be attached at a position where the body of the flying body 1 and the deployment blade 4 are opposed to each other. Here, as shown in FIG. 6, the magnet 13 of the flying body 1 and the magnet 13 of the deployment blade 4 have the same polarity, for example, N pole, so that the body of the flying body 1 A magnetic repulsive force is applied between the developing blade 4 and the deployment blade 4 is deployed. The fuselage of the flying body 1 and the magnets 13 included in the deployment wings 4 may be embedded in each or attached to each.

  Further, as a configuration for assisting the deployment of the deployment blade 4 by the holding member 10, an elastic body is disposed between the body of the flying body 1 and the deployment blade 4 as shown in FIG. 7. The elastic body may be a spring 14 as shown in FIG. The spring 14 is sandwiched between the body of the flying body 1 and the deployment wing 4 when the deployment wing 4 is housed in the folding launch tube 7. The restoring force of the spring 14 works so that when the flying body 1 exits the launch tube 7, the deployment blade 4 rotates around the deployment axis 5 and deploys.

  The spring 14 may be temporarily fixed to the flying body 1 with a tape or the like, or simply sandwiched between the flying body 1 and the deployment wing 4. After assisting the deployment of the deployment wing 4, it may be dropped from the flying body 1.

  In this way, using the same-polarity magnetic body attached to the position where the body of the flying body 1 and the deployment wing 4 are opposed to each other, or the elastic body sandwiched between the body of the flying body 1 and the deployment wing 4, the deployment wing 4 The deployment blade 4 can be deployed more smoothly by assisting the deployment.

In the flying object which has a holding device of the present invention, it is a figure showing the state before expanding a deployment wing, and the state where the deployment wing is developed and held using the holding device of the present invention. It is a figure which shows the state which folded the expansion | deployment wing | wing and accommodated the flying body in the launcher. It is a figure explaining developing a deployment wing using the holding device of the present invention. It is a figure which shows the state holding the expansion | deployment blade | wing using the holding | maintenance apparatus of this invention. It is a figure at the time of the width | variety of an expansion | deployment blade | wing being thin, and the diameter of the lock pin 12 being left as it is. It is a figure which shows having used the magnet (magnetic body) as an expansion | deployment assistance of an expansion | deployment blade. It is a figure which shows having used the spring (elastic body) as expansion | deployment assistance of an expansion | deployment blade.

Explanation of symbols

1. Flying object 2. Stopper 3. 3. Fixing member 4. Deployment wing Deployment axis6. Hinge 7. Launch tube8. Rotating shaft9. Torsion spring (elastic member)
10. Holding member 11. Fitting part 12. Lock pin 13. Magnet (magnetic material)
14 Spring (elastic body)

Claims (4)

In a deployment device for a deployment wing that is supported externally in a folded state and is deployed by opening the external support,
One end is fixed to the body of the flying body, and the other end facing the one end is a deployment shaft, and one end of the deployment wing is rotatably attached,
A rotation axis provided on the fixed member and orthogonal to the deployment axis;
One end is rotatably attached to the rotating shaft, and the other end is a holding member having a fitting portion that fits into the blade tip of the deployment blade,
Provided on the rotating shaft, urges the fitting portion to a position away from the deployment blade, and causes the fitting portion to move to the blade tip of the deployment blade by its own restoring force that acts by opening the external support. And an elastic member that expands the deployment wing to the engagement position,
A holding device comprising: In a deployment device for a deployment wing that is supported externally in a folded state and is deployed by opening the external support,
One end is fixed to the body of the flying body, and the other end facing the one end is a deployment shaft, and one end of the deployment wing is rotatably attached,
A rotating shaft that is on the blade surface side of the deployment blade from the extension line of the side end of the deployment blade with respect to the fixed member, is displaced from the deployment shaft, and is at a position orthogonal to the deployment shaft;
A holding member having one end rotatably attached to the rotary shaft and the other end rotating from a position away from the blade tip of the deployment blade to a fitting position with the blade tip;
Provided on the rotating shaft, urges the fitting portion to a position away from the deployment blade, and causes the fitting portion to move to the blade tip of the deployment blade by its own restoring force that acts by opening the external support. And an elastic member that expands the deployment wing to the engagement position,
A holding device comprising:   The holding device according to claim 1, wherein the fitting portion has a curved shape in contact with the deployment blade.   A flying body comprising the holding device according to any one of claims 1 to 3.

Images