JP2012245908A - Artificial satellite releasing system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an artificial satellite releasing system which allows an artificial satellite to be set or reused on an orbit and imposes less restrictions on the shape and size of the artificial satellite.SOLUTION: The releasing system A includes an adaptor 1 provided on an artificial satellite to be released and a base 2 supporting the artificial satellite by holding the adaptor 1. The base has a satellite releasing plunger 6 kept pushed forward by an elastic material 5, a clamp 7 which grabs and releases the adaptor 1 in contact with the satellite releasing plunger 6, and a lock mechanism 8 which restrains the satellite releasing plunger 6, retreated against the elastic material 5, in its retreated position, thereby allowing the artificial satellite to be set easily and reused repeatedly even on an orbit, and thus reducing restrictions on the shape and size of the artificial satellite to be released.

Description

  The present invention relates to a satellite emitting device used to release a satellite from a spacecraft such as a space station in outer space.

  Conventionally, as an apparatus for emitting an artificial satellite, there has been one as described in Non-Patent Document 1, for example. The device described in Non-Patent Document 1 holds a small satellite (piggyback satellite) with respect to the main satellite at the time of launching the rocket and separates the small satellite on the orbit of the main satellite. It has a structure in which the legs extended from the pillars at the four corners are gripped by the nail on the separation mechanism side. The separation mechanism locks the moving part with a nylon wire and latches the small satellite mechanically, and when separating the small satellite, the nylon wire is blown to release the latch by spring force. The small satellite is released by the pushing spring.

ISAS / JAXA 2007 Space Utility Res, 23 (2007), p. 1 1 7-1 20, “Dropping tower weightless test of separation mechanism system for micro satellite and on-orbit demonstration by MV rocket”

  However, since the conventional artificial satellite emitting device as described above emits a small satellite mounted on the main satellite, it is necessary to set a small satellite in advance before launch, and at the time of separation, a nylon wire is used. This is accompanied by fusing, that is, destruction of constituent parts. For this reason, the conventional satellite emission device cannot be set or reused in space orbit, and there is a problem that the shape and size of the emitted satellite are limited, It was a problem to solve such problems.

  The present invention has been made by paying attention to the above-described conventional problems, and can easily set an artificial satellite even on an orbit in outer space, and can be repeatedly used and released. The purpose is to provide a satellite emission device that can reduce the restrictions on the shape and size of the satellite.

  An artificial satellite emission device of the present invention is an apparatus for emitting an artificial satellite from a spacecraft in outer space, and includes an adapter provided on the emitted artificial satellite and a base for holding the artificial satellite at the adapter portion. At the same time, the base is equipped with a plunger for satellite release that is urged in the forward direction by the elastic body, a clamp that holds and releases the adapter that contacts the plunger, and a plunger that is retracted against the elastic body. The lock mechanism for restraining at the retracted position is provided, and the above configuration is used as means for solving the conventional problems.

  In a more preferred embodiment of the satellite satellite emitting device of the present invention, the clamp can be rotated with respect to the movement direction of the plunger, and can be moved backward with the retraction of the plunger to grip the adapter. At the same time, it is characterized by releasing the adapter by rotating forward with the advance of the plunger.

  According to the satellite emitting device of the present invention, the above configuration is adopted, so that the satellite can be easily set even on the orbit of outer space, and the component parts are not destroyed repeatedly. It can be used, and restrictions on the shape and size of the satellite to be emitted can be reduced.

In one Embodiment of the discharge apparatus of the artificial satellite which concerns on this invention, it is the perspective view (A) which shows a restraint state, and the perspective view (B) which shows a releasing state. It is the front view (A) and sectional drawing (B) explaining the adapter of a discharge device. It is sectional drawing (A) which shows the restraint state of the discharge | release apparatus, and sectional drawing (A) which shows a releasing state. It is explanatory drawing which looked at the housing | casing of the discharge | release apparatus shown in FIG. 3 from the lock mechanism side. It is a front view explaining the plunger of a discharge device.

Hereinafter, an embodiment of an emission device for an artificial satellite according to the present invention will be described with reference to the drawings.
A discharge apparatus A shown in FIG. 1 includes an adapter 1 provided on a satellite S to be released and a base 2 that holds the satellite S at a portion of the adapter 1, for example, a spacecraft such as a space station. The artificial satellite S is mounted on an orbit in outer space, and the artificial satellite S is released.

  As shown in FIG. 2, the adapter 1 is a member having a rectangular tube-shaped main body 1A. The adapter 1 has a mounting surface 1B joined to the artificial satellite S at the distal end of the main body 1A, and the base end of the main body 1A. In addition, a flange portion 1C corresponding to a circumscribed circle of the square tube is provided, and the flange portion 1C has inclined surfaces 1D directed in four directions. These inclined surfaces 1D serve as grip portions by clamps described later. The adapter 1 may be a separate body from the artificial satellite S or may be integrated with the artificial satellite in advance.

  The base 2 includes a leg portion 3 fixed to the platform P, and a housing 4 supported by the leg portion 3. The casing 4 is open at least in the emission direction of the artificial satellite S. In this embodiment, the emission direction is a direction parallel to the platform P as shown in FIG.

  Further, as shown in FIG. 3, the base 2 holds a satellite discharge plunger 6 urged in the forward direction by an elastic body 5 and an adapter 1 in contact with the plunger 6 inside the housing 4. The four clamps 7 to be released and the lock mechanism 8 for restraining the plunger 6 retracted against the elastic body 5 at the retracted position are provided. Here, the emission direction of the artificial satellite S is the forward direction of the plunger 6. Further, the housing 4 has a partition wall 9 separating an intermediate portion in the release / counter release direction (vertical direction in FIG. 3) of the artificial satellite S. The partition wall 9 includes a part of the plunger 6. An opening 9A is formed to allow insertion of.

  The plunger 6 has an inner sleeve 6A corresponding to the axial portion, an interface portion 6B provided at the tip (upper end in FIG. 3) of the inner sleeve 6A, and an outer sleeve 6C provided on the outer periphery of the interface portion 6B in a coaxial manner. In addition, as shown in FIG. 5, four restraining projecting pieces 6 </ b> D projecting in the backward direction (downward in FIG. 3) are provided at a position inside the outer sleeve 6 </ b> C. The four restraining protrusions 6D are arranged at intervals of 90 degrees.

  The plunger 6 is accommodated in the housing 4 so that the inner sleeve 6A is inserted through the opening 9A of the partition wall 9, and is movable between the partition 9 and the interface portion 6B with the inner sleeve 6A as a center. It is urged in the forward direction by an elastic body (compression coil spring) 5 interposed between them. Further, the plunger 6 has its forward limit determined by an inward flange 4 </ b> A provided at the open end of the housing 4, and is further rotated about its axis by a key (not shown) fitted between the plunger 6. It is blocked and can move only in the axial direction.

  The clamps 7 are arranged at 90 ° intervals corresponding to the four restraining protrusions 6D of the plunger 6 on the discharge side with respect to the partition wall 9. These clamps 7 are members having an approximately L-shape as shown in FIG. 3, and each of the clamps 7 has a receiving portion 7A on the side of the partition wall 9 as a receiving portion 7A and the other piece as a pressing portion 7B. As shown in FIG. 4, the torsion coil spring 12 is supported by the moving shaft 11 and is urged in the forward rotation direction indicated by the arrow C in FIG. At the position indicated by the line. At this time, the clamp 7 is arranged so that the receiving portion 7A protrudes on the backward movement trajectory of the restraining protrusion 6D of the plunger 6, and when the artificial satellite S is restrained, as described later, Collaborate.

  As shown in FIG. 3, the lock mechanism 8 includes a restraint hole 13 provided in the plunger 6 on the side opposite to the partition wall 9, and a pin drive unit that engages and disengages the restraint pin 14 with respect to the restraint hole 13. 15 is provided. The restraining hole 13 is formed in the inner sleeve 6 </ b> A of the plunger 6.

  The pin driving unit 15 is fixed to a bracket 16 attached to the partition wall 9. The pin driving unit 15 is a pin puller that moves the restraining pin 14 in accordance with the volume change of solidification and liquefaction of paraffin filled therein. That is, the pin drive unit 15 (pin puller) incorporates a piston integrated with the restraining pin 14 and a return spring that biases the piston in a direction in which the restraining pin 14 protrudes, and is isolated by the piston. The pressure chamber is filled with paraffin, and in addition, a paraffin heating means is provided.

  In the pin drive unit 15, the paraffin is solidified in a state where the restraining pin 14 protrudes and the pin 14 is engaged with the restraining hole 13. Then, when the paraffin is heated and liquefied by energization, the piston moves due to the volume expansion of the paraffin and pulls the restraining pin 14. As a result, the restraining pin 14 is detached from the restraining hole 13. Further, when the pin driving unit 15 cools and solidifies the paraffin, the piston is pushed back and the restraining pin 14 returns to the protruding state. That is, it can be reused.

  Further, in the discharge device A, through holes 17 and 18 are provided in the inner sleeve 6A and the bracket 16 of the plunger 6 so as to communicate with each other when the plunger 6 is moved to the retreat limit. The plunger 6 can be temporarily fixed when the pin driving unit 15 is reset by passing the temporary fixing pin 19 through 18.

  Further, the discharge device A fixes the bracket 16 to the partition wall 9 with a plurality of fixing bolts 20, and at this time, a slight gap 21 is provided between the partition wall 9 and the bracket 16, An adjusting bolt 22 with which the tip end abuts against the partition wall 9 is provided. Thereby, after restraining by the lock mechanism 8, the adjustment bolt 22 is screwed to attract the plunger 6 to the partition wall 9 via the bracket 16, thereby preventing rattling between members during restraint.

  The discharge device A of the artificial satellite S having the above configuration makes the adapter 1 attached to the artificial satellite S abut on the interface portion 6B of the plunger 6. At this time, in the discharge device A, the four inclined surfaces 1D of the adapter 1 and the four restraining protrusions 6D of the plunger 6 are in the corresponding directions, but the adapter 1 and the interface unit 6B include Concavities and convexities and the like that engage with each other only in a predetermined phase around the axis are provided, thereby preventing erroneous installation of the artificial satellite S and mounting the artificial satellite S in the correct orientation.

  Next, when the releasing device A pushes the artificial satellite S in the anti-emission direction, the plunger 6 moves backward while compressing the elastic body 5, and in the backward movement process, the clamp 7 in the state indicated by the phantom line in FIG. The restraining protrusion 6D is brought into contact with the receiving portion 7A, and the clamp 7 is rotated backward in the direction opposite to the arrow C direction in FIG. As a result, when the pressing portion 7B of the clamp 7 comes into contact with the inclined surface 1D of the adapter 1 and the plunger 6 reaches the retreat limit, the adapter 1 is gripped with the plunger 6 by the clamp 7.

  Further, after the plunger 6 reaches the retracted eye as described above, the plunger 6 is temporarily fixed by passing the temporary fixing pins 19 through the through holes 17 and 18 of the plunger 6 and the bracket 16. Then, after engaging the restraining pin 14 of the pin drive unit 15 with the restraining hole 13 of the plunger 6, the temporary fixing pin 19 is removed, and the adjustment bolt 22 is tightened to completely restrain the plunger 6. As a result, the artificial satellite S is securely held on the base 2 as shown in FIG.

  When the artificial satellite S is emitted, it is only necessary to operate the pin driving unit 15. That is, when the paraffin is liquefied by the heating means in the pin drive unit (pin puller) 15, the restraining pin 14 is moved by the volume expansion of the paraffin and is detached from the restraining hole 13 of the plunger 6, and the restraint of the plunger 6 is performed. Canceled. Then, the plunger 6 advances by the repulsive force of the elastic body 5 that has been compressed so far, and in this advancement process, the clamp 7 moves forward in the direction of arrow C in FIG. 3 to release the adapter 1. Then, at the same time when the plunger 6 reaches the forward limit where the plunger 6 contacts the inward flange 4A of the housing 4, the plunger 6 and the adapter 1 are separated as shown in FIG. Thereby, the artificial satellite S is discharged smoothly and promptly.

  As described above, the emission device A for the artificial satellite S described in the above embodiment can easily set the artificial satellite S even on an orbit in outer space, and does not involve destruction of the constituent parts, so that it is repeated. It is possible to use. In addition, since the adapter 1 provided in the artificial satellite S is adopted, restrictions on the shape and size of the artificial satellite to be released are reduced, and the artificial satellite S can be used for the emission of various artificial satellites S.

  Further, in the above-described discharge device A, the clamp 7 is rotatable with respect to the moving direction of the plunger 6, and retracts and rotates with the plunger 6 to grip the adapter 1. The adapter 1 is released by rotating forward with the forward movement. Thereby, although the discharge device A has a simple device configuration, the artificial satellite S can be set and held more easily and reliably, and then the smooth release operation of the adapter 1 and the artificial satellite can be performed. Smooth discharge operation of S can be performed continuously.

  Furthermore, since the discharge device A employs the lock mechanism 8 including the restraining hole 13 of the plunger 6 and the pin driving portion 15 that allows the restraining pin 14 to be removed from the restraining hole 13, the structure is simple. As a result, the plunger 6 and the satellite S can be held more securely and discharged smoothly. Further, by adopting a pin puller incorporating paraffin as the pin driving unit 15 in the lock mechanism 8, for example, even when the elastic body 5 has a large repulsive force and a large shearing stress acting on the restraining pin 14, it resists the force. The releasing operation can be performed smoothly and reliably.

  The configuration of the artificial satellite emission device of the present invention is not limited to the above embodiment, and the details of the configuration can be appropriately changed without departing from the gist of the present invention. The form of the constituent members, the number of functional parts such as clamps, and the like can be changed, and a solenoid-type means or the like can be used for the pin driving part.

A discharge device S artificial satellite 1 adapter 2 base 5 elastic body 6 plunger 7 clamp 8 lock mechanism 13 restraint hole (lock mechanism)
14 Restraint pin (lock mechanism)
15 pin drive (lock mechanism: pin puller)

Claims (4)

A device for emitting an artificial satellite from a spacecraft in outer space,
With an adapter provided on the satellite to be released and a base for holding the satellite on the adapter part,
On the base, a plunger for satellite release urged in the forward direction by an elastic body,
A clamp that grips and releases the adapter that contacts the plunger;
An emission device for an artificial satellite comprising a lock mechanism for restraining a plunger retracted against an elastic body at the retracted position.   The clamp is rotatable with respect to the direction of movement of the plunger, and retracts as the plunger moves backward to grip the adapter, and moves forward as the plunger moves forward to release the adapter. The artificial satellite emitting device according to claim 1.   3. The artificial satellite release according to claim 1, wherein the lock mechanism includes a restraining hole provided in the plunger and a pin driving unit for engaging and disengaging the restraining pin with respect to the restraining hole. apparatus.   4. The artificial satellite emitting device according to claim 3, wherein the pin driving unit in the locking mechanism is a pin puller that moves the restraining pin in accordance with a change in volume of solidified and liquefied paraffin filled therein. .

Images