JP2005037072A - Flight vehicle launcher - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a flight vehicle launcher capable of being repeatedly used at low launching cost with a simple structure. <P>SOLUTION: This flight vehicle launcher 1 has at least a spring means 10 obtained by connecting a compression spring 12 and a tension spring 13 in series through a cradle 11, an engaging means 30 formed on the cradle 11 and engaged with the flight vehicle 2, a tensing means 40 for moving the cradle 11 in one direction to simultaneously achieve the compression of the compression spring 12 and the tension of the tension spring 13, and a latching means 70 for positioning and supporting the cradle 11 tensed in one direction by the tensing means 40. The latching by the latching means 70 is released, whereby the compressed compression spring and the tensed tension spring are simultaneously released to move the cradle 11 and to launch the flight vehicle 2. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  This invention is a flying object such as food, water, fuel, etc., fireworks launched at a tourist spot, and a large flying object. The present invention relates to improvements in launching devices for launching missiles, spacecrafts, and the like.

  Generally, in order to launch the above-mentioned flying object, conventionally, an apparatus (for example, a rocket engine) for burning a combustible material such as explosives or aviation fuel is used, and the flying object is obtained by utilizing the propulsive force obtained by the combustion. Was going to be launched.

  By the way, the conventional flying object launching devices using the above-mentioned combustible materials such as explosives, for example, using a rocket engine, can not be reused once used, and can be reused. However, it cannot be used without reinjecting the fuel, and therefore, the cost of launching the flying object was high.

  In addition, since combustible materials such as explosives are used, accidents such as explosions are often dangerous due to the occurrence of abnormal combustion, and there is a problem that careful attention must be paid to handling such combustible material injection processing. It was.

  In view of the circumstances described above, an object of the present invention is to provide a flying object launching apparatus that has a simple structure, low launch costs, and that can be used repeatedly.

  In order to solve the above-described problems, in the flying object launching apparatus of the present invention, spring means in which a compression spring and a tension spring are connected in series via a cradle and the cradle are formed and engaged with the flying object. An engaging means; a pulling means for moving the cradle in one direction and simultaneously compressing the compression spring and pulling the tension spring; and a latch for positioning and supporting the cradle moved in the one direction by the pulling means And releasing the latch of the cradle by the latch means to simultaneously open the compression spring and the tension spring, and the receiving force by the resultant force of the compression spring and the tension spring. The platform is moved to fire the flying object.

 According to the above-described flying object launching device, the flying object is fired by utilizing the compression and tension action of the spring means comprising the compression spring and the tension spring, so the structure is simple, and when the flying object is re-launched Therefore, it is only necessary to compress and tension the spring means again, so that it is not necessary to replenish and replenish new members necessary for re-firing such as fuel re-injection as in the past, and the launch of the flying object can be made inexpensively. It can be repeated safely, the launch cost of the flying object can be significantly reduced, and the flying object can be safely launched.

  Hereinafter, an embodiment of a flying object launching apparatus according to the present invention will be described in detail.

  FIG. 1 is a conceptual cross-sectional view showing a flying object launching apparatus 1 according to the present invention, and particularly shows a case where it is applied to a launching apparatus that ejects a large flying object 2.

  The flying object launching apparatus 1 is composed of a launch pad 3 arranged in a building or on the ground surface.

  The launch pad 3 includes a launch casing 4 disposed with a predetermined elevation angle α, and a support 5 that supports the launch casing 4. Needless to say, this elevation angle α can take any angle within the range of 0 to 90 degrees, depending on the shape and size of the flying aircraft and its reach.

  On the other hand, a spring means 10 which is a main component of the present invention is disposed in the launch casing 4.

  The spring means 10 is composed of a compression spring 12 disposed below the launch casing 4 and a tension spring 13 disposed above the launch casing 4 with a cradle 11 described later as a boundary. . One or a plurality of compression and tension springs 12 and 13 of the spring means 10 are arranged in accordance with the weight and launch distance of the flying vehicle 2 to be ejected, and the tip 12a of the compression spring 12 and the tension spring 13 The rear ends 13b are arranged in series so as to face each other. In the embodiment, since the large and large aircraft 2 is fired, a plurality of compression and tension springs 12 and 13 of the spring means 10 are arranged accordingly.

  On the other hand, an inner plate 6 is fixed to each of the peripheral surface 4 a and the bottom surface 4 b in the above-described launch housing 4, and the spring means 10 is disposed in a space S surrounded by the inner plate 6.

  The compression spring 12 and the tension spring 13 constituting the spring means 10 are disposed in the space S in their natural length state, and the tension spring 13 is a hook (not shown) connected to the tip 13a. Engages with the eyebolt 7 screwed to the inner plate 6, and the rear end 13b of the tension spring 13 is also related to the eyebolt 8 screwed to the cradle 11 with a hook (not shown) connected to the rear end 13b. Match.

  Therefore, the tension spring 13 has a structure in which the front end 13 a is always connected to the front end of the launch housing 4 via the upper inner plate 6 and the rear end 13 b is always connected to the cradle 11.

  On the other hand, the front end 12 a of the compression spring 12 is in contact with the cradle 11, and the rear end 12 b is also in contact with the lower inner plate 6. Therefore, the compression spring 12 is merely positioned between the cradle 11 and the lower inner plate 6.

  On the other hand, the upper surface of the above-described launch housing 4 is covered with a plate-shaped runway 20, and the longitudinal direction of the runway 20 is at the center thereof as shown in FIG. A slit 21 is formed along the slit 21, and an engagement means 30 formed above the cradle 11 projects into the slit 21. In addition, since the cross section of the runway 20 mentioned above is carrying out circular arc shape, since it is anticipated that a raindrop etc. will flow into the center, in that case, the discharge groove which discharges a raindrop etc. is formed in the center part However, raindrops may be discharged to the outside.

  On the other hand, the engaging means 30 described above is a comparative example in which the rectangular protrusion 31 protruding into the slit 21 is fixed to one side surface of the protrusion 31 as shown in FIG. A buffer member 32 in which a soft spring and a hard spring are connected in series, and the buffer member 32 is in contact with the engaging portion 2 a of the flying object 2.

  On the other hand, as shown in FIG. 1, a tension means 40 that pulls the compression spring 12 and the tension spring 13 of the spring means 11 at the same time is disposed on the cradle 11 on the compression spring 12 side.

  The pulling means 40 is composed of a winch 42 for winding the rope, and a plurality of ropes 43 wound by the winch 42. At the tip of the rope 43, there is a hook as shown in a partially enlarged view shown by an arrow C. 44 is connected, and the hook 44 is engaged with an eyebolt 45 fixed to the cradle 11.

  By the way, in the above-described embodiment, since the relatively heavy flying body 2 is launched, the compression spring 12 and the tension spring 13 constituting the spring means 11 have, for example, a material diameter of 10 cm and a coil inner diameter of 165 cm. A meter, a coil outer diameter of 185 cm, and a free height of about 100 m may be used. In this case, the weights of the compression spring 12 and the tension spring 13 are also increased. Therefore, when these springs are compressed and tensioned, the frictional force in the above-described launch housing 4 also increases and the launch energy is lost. Can be considered.

  Therefore, in the embodiment, as shown in FIG. 4, among the coils of the compression spring 12 and the tension spring 13, a sliding plate 50 is disposed in each of the coils 12 a and 13 a at positions adjacent to the inner plate 6, and A steel ball 51 that can freely rotate at a predetermined pitch is arranged on the plate 6, whereby each coil 12 a, 13 a is moved on the steel ball 51 via the sliding plate 50, so You may make it set the energy loss by friction when the spring 13 compresses and tensions to the minimum.

  Further, in consideration of the fact that the weight of the cradle 11 also increases and the frictional force with the inner plate 6 increases, as shown in FIG. 2, a rotatable steel ball 51 is disposed on the lower surface of the cradle 11 in the width direction. In this case, the energy loss due to the friction may be set to a minimum by running on the rail 52 provided on the inner plate 6.

  On the other hand, as shown in FIG. 2, the flying object 2 of the embodiment has wings 2b on the left and right sides, and support arms 2c are disposed on the lower surfaces of the wings 2b. A sliding plate 2d is provided. Then, on the runway 20 in the direction in which the sliding plate 2d moves, a sliding plate 53 in which a plurality of unillustrated rotatable steel balls are arranged at a predetermined pitch is provided, and the flying object 2 is launched. The frictional force between the runway 20 and the flying object 2 when traveling on the runway 20 is reduced as much as possible.

  Next, the operation of the above-described flying object launching apparatus 1 will be described, and the configuration will be described in more detail. In addition, you may make it comprise the sliding plate 2d mentioned above with a wheel.

  As shown in FIG. 3, as shown in FIG. 3, the engaging portion 2a of the flying body 2 is first engaged with the engaging means at the initial position where the compression spring 12 and the tension spring 13 constituting the spring means 10 are in the natural length. 30 buffer members 32 are brought into contact with each other.

  Next, the hook 44 connected to the tip of the rope 43 of the pulling means 40 is engaged with the eyebolt 45 fixed to the pedestal 11 as shown in the enlarged view of the main part shown by the arrow C in FIG.

  When engaging the hook 44 of the rope 43 with the eyebolt 45 of the cradle 11, it may be difficult to manually move the rope 43 from the winch 42 if the weight of the rope 43 is heavy. 5, the crawler belt 60 is rotated by the power of a motor or the like, and the claw 61 projecting from the periphery of the crawler belt 60 engages with the coil 12 a of the compression spring 12 to move the inner diameter of the compression spring 12. Use car 63.

  According to such a towing vehicle 63, the rope 43 can be easily moved by engaging the hook 44 of the rope 43 with the eyebolt 64 screwed at the rear end thereof and moving the rope 43 to the cradle 11 shown in FIG. It can be towed.

  In this way, as shown in FIG. 1, the hooks 44 of the plurality of ropes 43 are engaged with the plurality of eyebolts 45 of the corresponding base 11 as shown in FIG. 1. The reason why the hooks 44 of the plurality of ropes 43 are engaged with the corresponding eyebolts 45 arranged at predetermined positions on the cradle 11 is that the cradle 11 is in a parallel posture from its initial position. It is for moving it with maintaining.

  Thereafter, when the winch 42 of the pulling means 40 is driven and the plurality of ropes 43 are evenly wound, as shown in FIG. 6, the cradle 11 is maintained on the inner plate 6 of the launch housing 4 while maintaining the parallel posture. As a result, the compression spring 12 is compressed for a certain length by the movement of the cradle 11, and the tension spring 13 is similarly pulled for a certain length.

  In this way, the winch 42 of the pulling means 40 is operated, whereby both the compression spring 12 and the tension spring 13 are compressed and pulled for a certain length by the movement of the receiving base 11, and then the operation of the winch 42 of the pulling means 40 is stopped. .

Thereafter, as shown in the enlarged view of the main part shown by the arrow D in FIG. 6, the latch means 70 disposed on the side of the launch housing 4 is driven, whereby the latch claw 71 is rotated counterclockwise around the shaft 72. To the cradle 11 to lock the cradle 11.

  In this way, after the lock of the cradle 11 by the latch means 70 is completed, the engagement between the cradle 11 and the plurality of ropes 43 is released. That is, in this state, the movement of the cradle 11 is restricted only by the latch of the latch means 70.

  Next, from the locked state of the cradle 11 shown in FIG. 6, as shown in FIG. 7, the latch claw 71 of the latch means 70 is rotated clockwise about the shaft 72, and thereby the cradle 11 is locked. When released, a resultant force F (F = F1 + F2) of the pressing force F1 of the compression spring 12 and the tensile force F2 of the tension spring 13 acts on the cradle 11, and the cradle 11 is fired as shown by an arrow G. It moves vigorously toward the tip of 4.

  Thus, when the cradle 11 moves as indicated by the arrow G, the force F is transmitted to the flying object 2 with little shock via the protrusion 31 and the buffer member 32 of the engaging means 30.

  As described above, when the resultant force F of the compression spring 12 and the tension spring 13 of the spring means 10 is transmitted to the flying object 2 through the cradle 11 and the engaging member 30, the flying object 2 becomes as shown in FIG. From the tip 20b of the runway 20, it is launched into the air at a predetermined elevation angle α.

  When the flying object 2 is fired again, the above-described operation may be repeated. Therefore, new members necessary for re-launching such as fuel re-injection can be replenished and replenished as in the past. Therefore, the launch of the flying object can be repeated inexpensively and safely, and thus the launch cost of the flying object can be significantly reduced and the launching of the flying object can be repeated safely.

  In the above embodiment, Although the launching device 1 for launching the large flying object 2 having a relatively heavy weight has been described in detail, the present invention is not limited to the large flying object 2 described above. Of course, it can be applied to lighter vehicles such as food, water, fuel, etc. that are ejected to gliders or ship in case of distress, and fireworks launched at sightseeing spots. If the weight of the compression and tension spring is small and the friction with the housing that houses it is negligible, the winch of the winding means, the runway with the steel ball, and the steel ball are arranged. The provided inner plate or the like is not necessary and may be omitted.

    The present invention is suitable for a flying object launching apparatus capable of repeatedly firing a flying object safely and inexpensively with a simple structure.

FIG. 1 is a conceptual sectional view of a flying object launching apparatus according to the present invention. 2 is an enlarged sectional view of the AA concept of FIG. 3 is a conceptual cross-sectional view of BB in FIG. FIG. 4 is an enlarged cross-sectional view of a main part of the spring. FIG. 5 is a conceptual diagram of a cable towing vehicle. FIG. 6 is a conceptual sectional view showing the operation of the flying object launching apparatus according to the present invention. FIG. 7 is a conceptual sectional view showing the operation of the flying object launching apparatus according to the present invention. FIG. 8 is a conceptual sectional view showing the operation of the flying object launching apparatus according to the present invention.

Explanation of symbols

1… Aircraft launcher
2 ... flying body 4 ... launch housing 12 ... compression spring 13 ... tension spring 11 ... cradle 10 ... spring means 30 ... engagement means 31 ... projection 32 ... buffer member 40 ... tension means 42 ... winch 43 ... rope 51 ... steel Sphere 50 ... Sliding plate 70 ... Latch means 71 ... Latch claw

Claims (7)

Spring means connected in series via a cradle with a compression spring and a tension spring;
Engagement means formed on the cradle and engaged with the flying object;
Tension means for moving the cradle in one direction and simultaneously compressing the compression spring and tensioning the tension spring;
Latch means for positioning and supporting the cradle moved in one direction by the pulling means;
By releasing the latch of the cradle by the latch means, the compression spring and the tension spring that have been compressed and tensioned are simultaneously opened, and the cradle is moved by the resultant force of the compression spring and the tension spring, so that the flight A flying object launcher characterized by firing a body. 2. The flying object launcher according to claim 1, wherein the spring means is accommodated in a launch housing. 3. The flying object launching apparatus according to claim 2, wherein friction reducing means for reducing the friction between the cradle and the spring means is disposed in the launch casing. The friction reducing means is disposed on a plurality of rollable steel balls disposed on a peripheral edge of the firing casing, and on the spring means at a position adjacent to the peripheral edge of the firing casing. The flying object launcher according to claim 3, comprising: a sliding plate that is in pressure contact, and a rollable steel ball disposed on the cradle adjacent to the periphery of the launch housing. 2. The flying object launching apparatus according to claim 1, wherein the pulling means includes a rope that is detachably attached to the cradle and a winch that winds the rope. The said engaging means consists of the protrusion protruded from the end of the said cradle, and the buffer member fixed to one side surface of this protrusion, and contact | abutted with a part of said flying body. Aircraft launcher. 2. The flying object launcher according to claim 1, wherein the latch means comprises a pivotable latch claw that engages with the cradle.

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