KR20100107714A - Separation device for the spacecraft's appurtenances - Google Patents

Abstract

PURPOSE: A device for separating the adjuncts from a space vehicle is provided to minimize the current consumption since a locking device operates with little power to operate a separating device if a rotating unit consists of a spring and the locking device. CONSTITUTION: A device(100) for separating the adjuncts from a space vehicle comprises a separating body(1), a main body(2) and a screw jack device(3). The separating body is fixed to the adjuncts of a space vehicle. The separating body comprises a space with a groove. The main body is fixed to the space vehicle. The main body is separably inserted into the space. The main body comprises a penetration hole formed on the location corresponding to the groove. The screw jack device is installed in the main body.

Description

Separation device for the spacecraft's appurtenances}

The present invention relates to an apparatus for restraining and detaching an accessory of a space vehicle to a body, and more particularly, to an apparatus for separating an accessory of a space vehicle, which allows the separation of an accessory to be precisely performed while the attachment of the accessory is firmly constrained.

Spacecraft, such as satellites, are usually transported into space in the loading space of projectiles. At this time, the loading space of the projectile is to have a limited size, such that an antenna, a solar panel, and the like, which are expanded to the outside during operation of the space flight and occupy a large volume, are loaded on the projectile in a state that is properly folded to occupy a small space. The spacecraft then enters the orbit and releases the accessories and unfolds the accessories.

In this case, the accessory may have an elastic force to be unfolded by itself after the restraint is released, or may be configured to be unfolded by using a separate deployment apparatus after the restraint is released. For example, the solar panel is constrained while being folded with a plurality of rotational shafts, and springs are installed on the rotational shafts so that the solar panels can be configured to be unfolded by themselves after releasing the restraint of the solar panel.

The separation device of such a space vehicle restraint is required in the space that is not human involvement in an unmanned spacecraft, so very high operational reliability is required.

Conventional separators include explosive separators. That is, the explosives are installed in a fixing means such as a bolt that restrains the restraint to the main body, and the explosives are exploded at an appropriate altitude to break the fixing means to separate the restraint. Such an explosive separation device has an advantage in that the separation is performed immediately with operation, but has a disadvantage in that the cost of handling explosives safely is increased. In addition, there is a risk of damaging the accessories by the impact, vibration, or contamination of the sensitive devices such as lenses, electronic devices, etc. accompanying the explosion. In addition, even if the experiment is successful every time due to the nature of the explosives also has the disadvantage that can not guarantee the reliability of the operation of the mounted explosives.

Due to the problems of the explosive separator, a non-explosive separator has been developed. For example, U. S. Patent No. 74,2403 shown in FIG. 8 has a separation device that separates an accessory from a body using a shape memory alloy (SMA). That is, the two restraining elements 12 and 12 'are connected by the bolt 14, and the recess 23 is formed in the middle of the bolt thinner than other parts. In addition, an SMA driver 24 extending when heated is installed around the depression 23, and a heater 27 is mounted on an outer circumferential surface of the driver. Thus, when the SMA driver 24 is heated and extended by the operation of the heater 27, both ends of the SMA driver 24 break the depression 23 by pushing the nut 25 and the head 16, Both restraints 12, 12 'are to be separated.

This prior art has to break the depressions formed in the bolt, so that the SMA driver with a large tensile force should be provided accordingly. In order to operate the SMA driver, it takes a long time to be heated so that the accessory cannot be separated at the correct time, and in addition, the amount of power required for heating is increased.

In addition, the direction in which the impact is transmitted from the outside due to the launching vibration of the projectile is in the longitudinal direction of the bolt, which coincides with the direction in which the SMA driver operates. Therefore, the pull force and the external force by the SMA acts together, so there is a disadvantage in that it is not possible to determine the separation time by the separation device depending on the use place.

Therefore, the non-explosive separator needs to make the separation accurate while increasing the binding force on the heavy attachment.

The present invention has been made to solve the above-described problems, embodiments of the present invention has the object of separating the accessory from the body in a non-explosive manner so that there is no damage and contamination of the accessory. In addition, it has the purpose of operating in a direction perpendicular to the direction of the force acting by the appendage to be separated to greatly increase the constraint of the appendage.

More specifically, it has the purpose of converting a rotational motion with a small force into a linear motion with a large force, so that the attachment of the accessory is surely made even with a small force.

In addition, even if the external force acting by the accessory has an object to enable to firmly restrain the accessory.

It also has the purpose of being able to provide rotational force while minimizing the consumption of current.

It also has the purpose of ensuring that the separation of appendages with large inertia can also be made reliably.

In order to solve the above problems, the present invention is constrained to the appendages of the cosmic body in an embodiment, the separator is formed with a separation space having a groove therein, and is constrained to the spaceship and detachably inserted into the separation space And a main body having a through hole formed at a position corresponding to the groove and the inside of the main body, and locking the locking part caught by the groove through the through hole to restrain the separator to the main body or to release the restraint. The present invention provides an accessory separating device comprising a screw jack device for horizontally moving to the groove.

In addition, the screw jack device has a screw thread formed on the outer circumferential surface, and the vertical screw shaft rotatable by the rotating portion, coupled to the vertical screw shaft to elevate by the rotation of the vertical screw shaft, the lifting nut with a flange formed on the outside and the elevating The present invention provides an accessory separating apparatus for a space vehicle comprising a nut and a link portion hinged to both ends of the locking portion.

In addition, when the locking portion is inserted into the groove, the longitudinal direction of the vertical screw shaft and the longitudinal direction of the link portion proposes an accessory separating apparatus of the space vehicle, characterized in that forming a vertical.

In addition, an upper male thread is formed at an upper portion of the vertical screw shaft, a lower male thread is formed at a lower portion thereof, and upper and lower lifting nuts are respectively coupled to upper and lower portions of the vertical screw shaft, and the upper and lower lifting nuts are respectively. An apparatus for separating accessories of a space vehicle, characterized in that connected to the locking unit by an upper link and a lower link.

In addition, the locking unit proposes an accessory separating apparatus of the space vehicle, characterized in that a plurality of radially installed.

In addition, the rotating unit is to present an accessory separation device of the spacecraft, characterized in that the spring spring coupled to the lower portion of the vertical screw shaft, and a lock device to prevent the release of the spring spring that stores the rotational force to release the prevention do.

In addition, one end is applied to the main body, the other end is applied to the separator, the elastic means for pushing the separator from the main body at the time of release of the lock by the locking portion further comprises a Present the accessory separator.

According to the detaching device of the appendage of the space vehicle according to the embodiment of the present invention as described above, as a non-explosive separating device using a screw jack device has all the problems that the conventional explosive separating device has been solved. In addition, the screw jack device converts a small rotational motion into a horizontal motion having a large force so that the separation of the separation body is performed. In the absence of time it has the effect that the separator is not separated.

In addition, the longitudinal direction of the vertical screw shaft and the longitudinal direction of the link portion form a vertical, so that the external force transmitted by the separator acts perpendicular to the vertical screw axis, thereby preventing the unintentional separation of the separating body. Has

In addition, since the locking portion is provided in a large number radially, it has the effect that it is possible to more tightly restrain the separator.

In addition, when the upper and lower lifting nuts are configured on the rotary shaft in the screw jack device, even if the coupling of either side can be operated as a complement of the other side, the operation reliability is increased.

In addition, when the elastic member is further included, since it helps the separation of the separator, there is an effect that the expansion is surely made even in the case of the accessory having a large inertia.

In addition, when the rotating part is made of a spring and the locker device, since the locker can be operated by using the locker with low power, the current consumption can be minimized.

Hereinafter, with reference to the preferred embodiment of the accompanying drawings, the function, configuration and operation of the accessory separating apparatus of the present invention the space flight will be described in detail. Hereinafter, the same reference numerals for the same components are used the same.

1 is a perspective view of an accessory separating apparatus of the space vehicle according to the first embodiment of the present invention.

Separator 1 is fixed to the accessory of the space vehicle according to the first embodiment of the present invention, the separation body 1 is formed in the separation space 11 having a groove 12 therein, The main body 2 is fixed to the spaceship and detachably inserted into the separation space 11, and a through hole 21 is formed at a position corresponding to the groove 12.

In addition, the through hole 21 is provided inside the main body 2 and locks 34 to the groove 12 to restrain the separator 1 from the main body 2 or release the restriction. It includes a screw jack device (3) for moving horizontally to the groove (12) through.

At this time, the separation space 11 is formed in the separator 1, and the horizontal groove 12 is formed in the separation space 11. When the separation space is formed in a cylindrical shape as shown in Figure 1, the groove 12 is formed along the circumferential direction.

At this time, the separator 1, as shown in Figure 1, the bottom surface is formed in an open cylindrical shape may have a configuration in which the upper part is fixed to the accessory by a known fastening means, such as bolts, If there is sufficient space, it is desirable to form recesses and grooves by recessing the surface of the appendage.

On the other hand, the body 2 is inserted into the separation space, it is fixed to the space flight. The outer shape of the main body may be cylindrical according to the shape of the separation space. On the other hand, the flange plate 22 may be further added to the lower portion of the main body to change the fixed position of the main body.

In addition, when the main body 2 is inserted into the separation space 11, the through hole 21 through which the locking part 34 protrudes is formed in the outer circumferential surface of the main body 2 corresponding to the groove 12 of the separation space 11. Is formed.

At this time, the locking portion 34 is projected to the outside of the main body along the through-hole 21 through the screw jack device which will be described in detail later, or is received into the main body. When the locking portion 34 protrudes to the outside of the main body and moves to the groove 12 formed in the separating space 11, the separating body 1 is restrained from being separated from the main body 2, and the locking unit 34 is again. When the inside of the main body 2 is accommodated, the locking part 34 is not caught by the groove 12, so that the separator 1 is detachable from the main body 2.

On the other hand, one end is applied to the main body 2 between the separator 1 and the main body 2, and the other end is applied to the main body 2, and the main body (when release of the restraint by the locking portion) is performed. In 2), the elastic means 4 for pushing the separator 1 may be further included.

At this time, the elastic means 4 may be a compression spring mounted to the spring receiving groove (C) formed on the upper inner wall surface and the upper end of the main body of the separator. Meanwhile, the elastic means may be installed between the lower end of the separator and the flange plate to which the main body is fixed.

The elastic means is further included so that the restrained separator can be pushed upward. In other words, if the attachment has an elastic force so that it can be unfolded after the restraint is released, or if it is not configured to be unfolded using a separate deployment device, the attachment is surely made. In particular, even in the case of an accessory having a large inertia, the deployment is surely made, and the operation reliability is improved.

In addition, even when the appendages are configured to unfold by themselves, the detachment of the appendages is more reliably made by initially moving the appendages in the separating direction.

On the other hand, Figure 2 is a cross-sectional view before the separation of the accessory separating apparatus of the space vehicle shown in Figure 1, Figure 3 is a cross-sectional view after the separation of the accessory separating apparatus of the space vehicle shown in FIG.

A screw thread is formed on an outer circumferential surface of the screw jack device 3 provided inside the main body, and is coupled to the vertical screw shaft 31 rotatable by the rotating part 35 and the vertical screw shaft 31. A lifting nut 32 which is lifted by the rotation of the 31 and the flange 32a is formed on the outside, and a link part 33 which is hinged at both ends to the lifting nut 32 and the locking part 34 are included.

At this time, the vertical screw shaft 31 is provided in the lower portion of the main body, or is coupled to the rotating portion 35 provided in the interior of the rotatable.

In addition, a flange 32a is formed on the outer circumferential surface of the lifting nut 32 to correspond to the number of the through holes 21, and is coupled to the vertical screw shaft 31 by a thread formed therein.

On the other hand, the link portion 33 is a length member that is inserted into each through hole 21 and hinged to both the inner side of the locking portion 34 which is horizontally slidable and the flange of the lifting nut 32.

The locking portion 34 is composed of a ball 341 inserted into the groove and a support piece 342 supporting the ball from the inside, and the inside of the support piece 342 is hinged to the link portion. It is preferable that a plurality of the locking parts 34 are installed to secure the restraint of the separator, and in the case where a plurality of the locking parts 34 are installed, the locking parts 34 are arranged radially to separate the separating parts ( The restraint of 1) can be made evenly along the outer circumferential surface of the main body 2.

At this time, the number of installation of the locking unit may vary depending on the intention of the designer in consideration of the external force by the deployment device provided separately from the inertia of the separator.

On the other hand, the rotating unit 35 is to rotate the vertical screw shaft 31, for example, a motor may be used. Such a motor may be configured to rotate a vertical screw shaft through a reducer to obtain a large torque. In addition, the rotation unit is installed on the ground while storing the rotational force, it may have a configuration to rotate the vertical screw axis with the rotational force stored in the outer space.

Referring to FIG. 3, when the vertical screw shaft 31 is rotated by the rotating part 35, the lifting nut 32 has a locking part 34 and a link in which the flange 32a formed on the outer circumferential surface is inserted into the through hole of the main body. Since it is coupled through the portion 33 does not rotate with the vertical screw axis 31, it is raised along the vertical screw axis (31).

At this time, one end of the link portion 33 is also raised along the lifting nut 32, thereby sliding the locking portion 34 hinged to the other end of the locking portion 34 to the inside of the main body. Therefore, the locking portion 34 is moved to the inside of the main body to release the restraint.

At this time, when the locking part 34 is formed of the ball 341 and the support piece 342, the lower surface 121 of the groove formed in the separating body is inclined so that the ball 341 is accommodated in the through hole 21. Can be formed.

That is, the support piece 342 slides inwardly of the main body 2 to form a space in which the ball 341 is to be accommodated, and the separator 1 which is lifted due to a separate deployment device installed on the elastic means or the appendage. Due to the inclination of the bottom surface 121 of the groove), the ball 341 is moved to the inside of the through hole 21 to release the restraint of the separator.

Of course, when the ball and the support piece constituting the locking portion forms a body, the ball caught by the groove is moved into the main body together with the support piece by the rotation of the vertical screw shaft, so that the inclined surface is not formed in the groove of the separator. It becomes possible.

This screw jack device uses a small rotational force that rotates the vertical screw shaft, so that the lifting nut can be moved up and down with a large force, thereby smoothly sliding the locking part while consuming less power required for the separation device. Will be released.

More specifically, the screw jack device allows the rotating part to be designed to have a sufficiently small rotational force by converting the rotational movement of the vertical screw shaft with the small force into the horizontal linear motion of the locking portion with the large force, but conversely always Since the vertical screw shaft rotates itself by the locking part pressed inward by the separator having the external force to be pulled, it is difficult to release the unintentional separator.

Referring back to FIG. 2, when the locking part 34 is inserted into the groove 12 and the separator 1 is constrained, the longitudinal direction of the vertical screw shaft 31 and the longitudinal direction of the link part 33 are vertical. To prevent the vertical screw shaft from rotating itself even when the locking portion is pressed to move inward by the external force that raises the separator.

That is, the external force transmitted to the locking portion 34 by the separator 1 acts horizontally, whereas the lifting nut coupled to the vertical screw shaft 31 is transferred in the vertical direction, and thus horizontally through the link portion. As the lifting nut is raised or lowered by the external force acting, the vertical screw shaft becomes difficult to rotate. As a result, since the restraint of the separator is not released by the action of the external force, the reliability of restraining the attachment is further increased.

On the other hand, Figure 4 is a cross-sectional view of the accessory separating apparatus of the space vehicle according to the second embodiment of the present invention, Figure 5 is a cross-sectional view after the separation of the accessory separating apparatus of the space vehicle shown in FIG.

Apparatus separation apparatus 100 of the space vehicle according to the second embodiment of the present invention is the same as the first embodiment described above except for the following description. Therefore, the description of the same components are omitted because they overlap.

The vertical screw shaft 31 of the screw jack device 3 employed in the accessory separating apparatus 100 of the space vehicle according to the second embodiment of the present invention has a left number at the upper part based on the height at which the through hole 21 is formed. A thread is formed, and a right male thread is formed at a lower portion, an upper lifting nut 321 having a left female thread is coupled to an upper portion of the vertical screw shaft 31, and a lower lifting nut 322 having a right female thread formed at a lower portion thereof. Are coupled, and the upper and lower lifting nuts 321 and 322 are connected to the locking portion 34 by upper and lower link portions 331 and 332, respectively.

Therefore, referring to FIGS. 4 to 5, when the vertical screw shaft 31 is rotated to the left, the upper lifting nut 321 rises on the vertical screw shaft 31, and the lower lifting nut 322 is vertical. The screw shaft 31 is lowered, and the upper lifting nut 321 and the lower lifting nut 322 are separated from each other. In addition, by the upper and lower link portions 331 and 332, the locking portion 34 is slid to the inner direction of the main body 2 to release the restraint of the separator (1).

In this case, even when one of the couplings is loosely coupled and the function of sliding the locking portion inwardly is deteriorated, sliding of the locking portion is made as a complement of the other, so that the operating reliability of the separation device is increased.

At this time, the flange piece 342a which is hinged to the upper and lower link portions 331 and 332 up and down is formed inside the locking portion 34 so that the longitudinal and vertical screw shafts 31 of the upper and lower link portions 331 and 332 are formed. ) Longitudinal direction is configured to be perpendicular to each other.

On the other hand, Figure 6 is a partial cross-sectional perspective view of the rotating portion employed in the accessory separating apparatus of the space vehicle shown in FIG.

The rotating part 35 employed in the accessory separating apparatus 100 of the space vehicle according to the second embodiment of the present invention has a spring spring 351 coupled to a lower portion of the vertical screw shaft 31 and a spring spring storing rotational force. A locking device 352 is included to prevent the release of the 351 and then release the prevention.

At this time, one end of the mainspring 351 is fixed to the vertical screw shaft 31 and the other end is fixed to the housing, thereby storing the rotational force.

In addition, the locking device 352 has a function of preventing the arbitrary rotation of the vertical screw shaft 31, the release of the spring spring 351 to release the prevention. For example, the locking device 352 is fixed to the vertical screw shaft 31 and the disk 352a having a tooth tooth 352b is formed on the outside, and caught by the tooth tooth 352b to loosen the spring spring 351. It can be made of a stopping piece 352e to prevent, and a stopper pin 352g to release the spring spring by releasing the locking piece 352e. At this time, the locking piece 352e is freely rotatable based on the vertical rotation shaft 352f.

At this time, the locking device 352e is wound by the inclined surface 352c of the tooth 352b, as shown in FIG. ) Rotates to allow the passage of disk 352a.

After fully wound the spring 351, as shown in Fig. 7 (b), one side of the engaging piece 352e is applied to the vertical surface 352d of the tooth 352b, the other side is a stopper pin ( By touching 352g), rotation of the disk 352a is suppressed and loosening of the spring spring 351 is prevented.

Then, when the stopper pin 352g is pulled out and removed through a separate driver (not shown) at the time of deployment of the accessory, as shown in FIG. 7C, the locking piece 352e is rotated and the disk ( The restraint of 352a is released, and the vertical screw axis is rapidly rotated by the restoring force of the spring 351.

In this case, by providing a conventional driver that consumes little power and discharges the stopper pin downward, the separator is operated by operating with less power than when using a motor that consumes continuous power as in the first embodiment described above. As a result, the current consumption can be minimized. For example, the driver may be configured to remove the stopper pin by the restoring force using the SMA, or to remove the stopper pin by the rotation of the motor by a combination of a conventional motor and a lex gear. At this time, even if the driver is made of a motor, only a short moment for moving the stopper pin to the bottom to be removed, so that the power consumption is smaller than the rotating unit of the first embodiment described above.

On the other hand, since the rotating part is configured in a double, the separation of the separator by the rotation of the vertical screw shaft can be configured to be made more sure. For example, a motor may be further coupled to a vertical screw shaft that extends further to a lower portion of the rotating unit according to the second embodiment. At this time, the motor is coupled to the rotating screw shaft through the clutch, the clutch is independent of the rotation of the rotating screw shaft and the rotation of the motor coupled to the spring and the lock device in ordinary times, and rotates the rotational force of the motor during the rotation of the motor It may have a conventional configuration for transmitting to the shaft. Thus, if the separation of the separation is not made smoothly by the malfunction of the rotating part consisting of the spring and the lock device, the separation of the separation is made surely by forcing the rotation of the vertical screw shaft by the additional operation of the motor. .

The separation of the separator from the dual configuration of the rotating portion is surely has the advantage that the operation reliability is further improved.

1 is a perspective view of the detachment of the accessory separating apparatus of the space vehicle according to the first embodiment of the present invention.

Figure 2 is a cross-sectional view before separation of the accessory separating device of the space vehicle shown in FIG.

Figure 3 is a cross-sectional view after the separation of the accessory separating device of the space vehicle shown in FIG.

Figure 4 is a cross-sectional view of the accessory separating apparatus of the space vehicle according to the second embodiment of the present invention.

5 is a cross-sectional view after the separation of the accessory separating device of the space vehicle shown in FIG.

FIG. 6 is a partial cross-sectional perspective view of a rotating part employed in the accessory separating apparatus of the space vehicle shown in FIG. 4. FIG.

7 is a view schematically showing the use state of the rotating part shown in Figure 6, (a) is a plan view showing a winding state, (b) is a plan view showing a locked state, (c) is a lock release Top view showing the state.

8 is a cross-sectional view showing a conventional technology.

Explanation of symbols on the main parts of the drawings

100: separator

1: Separator

11: separation space 12: groove

2: body

21: through hole

3: screw jack device

31: vertical screw axis

32: lifting nut 321: upper lifting nut 322: lower lifting nut

33 link portion 331 upper link portion 332 lower link portion

34: locking part 341: ball 342: support piece

35: rotating part 351: hand spring 352: locking device

4: elastic means

Claims (7)

A separator 1 fixed to an accessory of the space flight body and having a separation space 11 having a groove 12 therein; A main body (2) fixed to the spaceship and detachably inserted into the separation space (11) and having a through hole (21) formed at a position corresponding to the groove (12); And The through hole 21 is provided inside the main body 2 and locks 34 to the groove 12 to restrain the separator 1 to the main body 2 or to release the restraint. And a jack jack device (3) for horizontally moving to the groove (12) by passing through). In claim 1, The screw jack device (3) A screw thread is formed on the outer circumferential surface and is rotatable by a rotating part 35; A lifting nut (32) coupled to the vertical screw shaft (31) to elevate with the rotation of the vertical screw shaft (31) and having a flange (32a) formed on the outside thereof; And And a link portion (33) hinged at both ends of the flange (32a) and the locking portion (34). In claim 2, When the locking portion 34 is inserted into the groove 12, The longitudinal direction of the vertical screw shaft (31) and the longitudinal direction of the link portion 33, the accessory separating apparatus of the spacecraft, characterized in that forming a vertical. 4. The method of claim 3, The upper portion of the vertical screw shaft 31 is formed with the left male thread, the lower portion is formed with the right male thread, Upper and lower lifting nuts 321 and 322 are coupled to the upper and lower portions of the vertical screw shaft 31, respectively. The upper and lower lifting nuts 321 and 322 are connected to the locking unit 34 by upper and lower link units 33, respectively. In claim 4, The locking unit 34 is separated from the appendages of the space vehicle, characterized in that a plurality of radially installed. In claim 2, In the rotating part 35 A spring spring 351 coupled to the lower portion of the vertical screw shaft 31; And Preventing loosening of the spring spring 351, which stores the rotational force, the attachment device of the spacecraft, characterized in that it comprises a locking device 352 for releasing the prevention. In claim 6, One end of the main body 2 and the other end of the main body 2 are pressed against the separating body 1 to push the separating body 1 out of the main body 2 when the restraint is released by the locking part 34. Apparatus separation apparatus of the space vehicle, characterized in that it further comprises an elastic means (4).

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