JP5552456B2 - Band coupling device used for spacecraft separation structure - Google Patents

Description

  The present invention relates to a band coupling device capable of mitigating an impact generated when separating a connected spacecraft by cutting a band member wound around the outer periphery of a connecting portion between the spacecrafts. About.

  When launching a spacecraft such as an artificial satellite, it is necessary to firmly fix and support the artificial satellite on the rocket body before launching the orbit into the rocket body and to disconnect it from the rocket body when the orbit is launched. Therefore, the rocket for launching the artificial satellite has a separation structure for connecting the artificial satellite to the rocket body and for separating it from the rocket body. As an example of the separation structure, for example, the separation structure of a spacecraft disclosed in Patent Document 1 can be given. The separation structure includes a hook provided at each of the connection end of the rocket body and the connection end of the artificial satellite, a fitting member that is fitted from the outside of the hook while the hooks are connected to each other, A band member (for example, a Marman clamp band) that is wound after being tightened to the outer periphery of the connecting portion including the fitting member.

  The band member is wound around the outer periphery of the connecting portion by coupling both ends with a coupling member made of a bolt or the like with the outer periphery of the fitting member tightened. Is attached. When the artificial satellite is separated, the band member is cut by the cutting device, and the artificial satellite is separated from the rocket body. As the cutting device, a blast bolt is generally used. A typical blasting bolt has a structure in which explosive is provided on the axial center of the bolt, and when separating an artificial satellite, the explosive explosive explodes the bolt, thereby cutting the band member.

  By the way, it is known that a large impact occurs when a spacecraft such as an artificial satellite is separated. Causes of this impact include (1) cutting of the band member in a tightened state and (2) ignition of a pyrotechnic product that is a cutting device. Therefore, conventionally, techniques for mitigating these impacts during separation have been proposed.

  For example, Patent Literature 2 discloses an impact mitigation structure for mitigating the cause (2), that is, an impact caused by pyrotechnics ignition. This shock absorbing structure is formed by alternately laminating metal plates and resin plates and bonding them together with an adhesive, and has sufficient rigidity against vibration and impact. Therefore, by disposing the shock absorbing structure between the separation mechanism and the structure of the spacecraft, it is said that the shock caused by the pyrotechnic fire can be attenuated and transmitted to the structure.

  Patent Document 3 discloses a plurality of types of band opening mechanisms in order to mitigate the cause (1), that is, the impact caused by the cutting of the band member. As an example, a configuration using a release mechanism including a pin and a valve needle will be described. In this configuration, the valve needle is a grooved chamber (annular chamber) filled with a viscous material (lead). And the duct connecting the empty chamber. A grooved chamber is formed between the housing and the piston that fit together, and an empty chamber is formed in the cap on the piston. When the opening mechanism is operated, the pin shifts the position of the valve needle, so that the viscous material moves from the grooved chamber to the empty chamber through the duct. Accordingly, since the piston continuously moves from the housing, the band member is opened in a predetermined time set in advance.

Japanese Patent No. 3922718 Japanese Patent Laid-Open No. 07-132899 International Publication No. 01/02248 Pamphlet

  However, in the conventional technique, in the structure in which the connection portion is fastened and fixedly supported by the band member, there is a possibility that a large impact generated in the artificial satellite when the band member is cut cannot be sufficiently mitigated.

  Since the connecting portion between the rocket body and the satellite is fastened by a band member, the connecting portion (frame or the like) is deformed by the tightening force. Therefore, when the band member is cut instantly by a pyrotechnic or the like, the strain energy accumulated in the deformed connecting portion is also released instantly, which causes a large impact on the artificial satellite. In order to mitigate this impact, it is only necessary to reduce the tension at the time of tightening the band member. However, if the tension is excessively reduced, the reliability of the fixed support of the artificial satellite is lowered. In addition, the impact resulting from this deformation | transformation of a connection part is called the impact by a cause (3) for convenience of explanation.

  Here, in the technique disclosed in Patent Document 2, it is assumed that an impact due to the cause (2) can occur, and an impact buffering structure is used to mitigate the impact. However, with regard to the impact due to the cause (1), Substantial consideration is not made. Therefore, if the separation structure of the spacecraft is configured to cut the band member without using pyrotechnics, neither the impact due to the cause (1) nor the impact due to the cause (3) can be mitigated.

  Further, the technique disclosed in Patent Document 3 is focused on releasing the tension of the band member in a timed process. Therefore, since the band member can be opened without using a strong pyrotechnic, it is possible to reduce the impact caused by the causes (1) and (2). However, in this technology, since the emphasis is on mitigating the tension energy stored in the band, the structure of the band opening mechanism is unique and the connection Substantially no consideration is given to the deformation of the part.

  If the band member can be opened gently, the impact due to the cause (3) can be mitigated. However, if the tension at the time of tightening the band member cannot be sufficiently maintained, the reliability of the fixed support of the artificial satellite can be reduced. Can not increase. Therefore, in the spacecraft separation structure, it is required not only to gently open the band member but also to realize sufficient tension at the time of tightening, but Patent Document 3 discloses a tension at the time of tightening with a simple configuration. There is no disclosure of a technology that can sufficiently ensure the above.

  The present invention has been made in order to solve such a problem, and in a separation structure in which a connection portion of spacecrafts is fastened and fixedly supported by a band member, an impact when the band member is cut can be reduced. Another object of the present invention is to provide a band coupling device that can sufficiently secure the tension at the time of tightening by the band member with a simple configuration.

  In order to solve the above problems, a band coupling device according to the present invention is used in a spacecraft separation structure that separably fixes a second spacecraft to a first spacecraft, and the spacecraft A band coupling device that maintains the ends of band members that are fixedly supported in a state where the outer periphery of the coupling part between the bodies is tightened in a separably coupled state, in which the coupling shaft portions intersect with each other in the longitudinal direction. Each of the tip ends is opened and closed with the connecting shaft portion as a starting point, and is a clamp portion that sandwiches and connects the connected portion provided at the end portion of the band member, and the connecting shaft portion The rear end portion of the lever is a lever portion that opens and closes in conjunction with the clamp portion, and is supported by the connecting shaft portion and the connecting shaft portion, and the rear end of the lever portion from the connecting shaft portion. Guide part extending to the side And a pair of link members rotatably supported by the lever portions of the band end coupling member and each other end of the band end coupling member coaxially and rotatably supported by the guide member; A link interlocking connecting portion provided on the guide member so as to be movable in a direction away from the connecting shaft portion with each other end of the link member being rotatably connected, and the lever portion is closed. In this state, the clamp part is closed, and the link interlocking connecting part is located in a state close to the connecting shaft part, so that the pair of link members are closed between the lever parts, As the lever portion opens, the link interlocking connecting portion moves away from the connecting shaft portion so that the pair of link members open.

  According to the said structure, a link mechanism is comprised by a pair of link member and link interlocking connection part, and the opening / closing of the lever part in a pair of band end coupling member is linked by the said link mechanism. As a result, the clamp portion opens relatively slowly due to the inertia (or moment) when the lever portion opens and the interlocking by the link mechanism. Further, since the lever portion is opened synchronously by the link mechanism, the clamp portion is also opened synchronously. Therefore, the connection between the end portions of the band member sandwiched between the clamp portions is gently released, and thereafter, the interval between the end portions of the band member is also opened substantially uniformly. Therefore, it is avoided that the band member is instantaneously cut, and the band member opens gently and substantially uniformly, so that the impact when the band member is cut can be reduced with a simple configuration. In addition, since the impact can be reduced, it is possible to increase the tension at the time of tightening by the band member with a simple configuration.

  In the band coupling device having the above-described configuration, in the state where the lever portion is completely opened, the link interlocking connection portion stops on the rear end side of the lever portion in the guide member, and the pair of link members includes: The other end connected to each other may be open so as to protrude to the rear end side of the lever portion. Thereby, the state which the lever part opened fully can be hold | maintained easily.

  In the band coupling device having the above-described configuration, the pair of link members have a shape that is bent at the center so that both end portions thereof are located on the rear end side of the lever portion when they are opened. A configuration is preferable. Thereby, the length of a link member can be shortened.

  In the band coupling device having the above configuration, the guide member may be provided with a slit that is movably held in a state in which the link interlocking connection portion is fitted.

  In the band coupling device having the above configuration, the coupled portion at the end of the band member may be a convex portion that projects toward the outer periphery of the band member.

  The band coupling device having the above configuration may include a lever fixing member that fixes the rear end portions of the lever portions so as to prevent the lever portions from opening.

  In the band coupling device having the above-described configuration, the band member may be a Marman clamp band that fixes the second spacecraft to the first spacecraft.

  In the band coupling device having the above configuration, the first spacecraft may be a rocket body, and the second spacecraft may be an artificial satellite.

  As described above, according to the present invention, in the separation structure in which the connection parts of the spacecrafts are fastened and fixedly supported by the band member, the impact when the band member is cut can be reduced, and the tension at the time of fastening by the band member can be reduced. There is an effect that a band coupling device that can be sufficiently secured with a simple configuration can be provided.

It is an example of composition of a band coupling device concerning Embodiment 1 of the present invention, and is a typical top view showing the state where the band coupling device was closed. FIG. 2 is a schematic plan view showing a state where the band coupling device shown in FIG. 1 is opened. (A) is a schematic top view which shows the structure of a Marman clamp band provided with the band coupling device which concerns on Embodiment 2 of this invention, (b) is a Marman clamp band shown in (a), a rocket main body and artificial It is a partial side view which shows typically the state which supports the connection of a satellite. It is a typical side view which shows an example of the structure by which the band coupling device with which the Marman clamp band shown in FIG.3 (b) is attached to the rocket main body.

  Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In the following description, the same or corresponding elements are denoted by the same reference symbols throughout the drawings, and redundant description thereof is omitted.

(Embodiment 1)
[Configuration of band combiner]
First, an example of a specific configuration of the band coupling device according to Embodiment 1 of the present invention will be described with reference to FIG. 1 and FIG. As shown in FIG. 1, the band coupling device 14A according to the present embodiment includes a first band end coupling member 141, a second band end coupling member 142, a lever opening / closing coupling portion 143, a guide member 144, a link mechanism 145, and A lever fixing member 146 is provided, and the ends (band ends 42a, 42b) of the band member 42 fixed and supported in a state in which the outer periphery of the connecting portion between the spacecrafts is tightened are maintained in a separably coupled state. Used to do.

  The first band end coupling member 141 and the second band end coupling member 142 are pivotally coupled by a lever opening / closing coupling portion 143 that is a coupling shaft portion in a state of crossing each other in the longitudinal direction. It becomes the 1st clamp part 141a and the 2nd clamp part 142a. The first clamp part 141a and the second clamp part 142a are configured to open and close with the lever opening / closing connection part 143 as a starting point. Further, the rear end side portion of the first band end coupling member 141 and the second band end coupling member 142 from the lever opening / closing connecting portion 143 opens and closes in conjunction with the opening and closing of the first clamp portion 141a and the second clamp portion 142a. A first lever portion 141b and a second lever portion 142b are provided. That is, the first band end coupling member 141 and the second band end coupling member 142 are divided into a front end portion and a rear end portion based on the lever opening / closing connection portion 143. Each front end portion (lower end portion in the figure) is a first clamp portion 141a and a second clamp portion 142a, and each rear end portion is a first lever portion 141b and a second lever portion 142b. Yes.

  The first clamp portion 141a and the second clamp portion 142a join the band ends 42a and 42b by picking the coupled portions 42c provided at the band ends 42a and 42b. The coupled portion 42c is provided on the band ends 42a and 42b as convex portions protruding to the outer peripheral side of the band member 42, and both ends of the coupled portion 42c are connected to each other with the band ends 42a and 42b facing each other. The band ends 42a and 42b are joined by being sandwiched between the one clamp part 141a and the second clamp part 142a.

  The first band end coupling member 141 and the second band end coupling member 142 are fixed to the guide member 144 by a lever opening / closing connecting portion 143. Since the guide member 144 is fixedly supported by a spacecraft (not shown), it also functions as a lever support member. The guide member 144 is supported by the lever opening / closing connecting portion 143 and has a shape extending at least from the lever opening / closing connecting portion 143 to the rear end side of the first lever portion 141b and the second lever portion 142b. In the present embodiment, as shown in FIG. 1, the first lever / link connecting portion 143 to the first lever / link connecting portion 141 c and the second lever / link with the first lever portion 141 b and the second lever portion 142 b closed. It is comprised as a pair of plate-shaped member which has the length of the grade which reaches the connection part 142c. Of the pair of plate-like members, the end portions on the first lever / link connecting portion 141c side and the second lever / link connecting portion 142c side may be connected to each other.

  Since the first band end coupling member 141 and the second band end coupling member 142 intersect at a position corresponding to the lever opening / closing connecting portion 143, the first lever portion which is the rear end portion of the first band end coupling member 141 141b is located on the left side in the figure, but the first clamp part 141a, which is the tip of the first band end coupling member 141, is located on the right side in the figure. Similarly, the second lever portion 142b, which is the rear end portion of the second band end coupling member 142, is located on the right side in the drawing, but the second clamp portion 142a, which is the front end portion of the second band end coupling member 142, is , Located on the left side in the figure. Therefore, the lever opening / closing connecting portion 143 serves as a fulcrum for opening and closing the first lever portion 141b and the second lever portion 142b.

  Therefore, if the first lever portion 141b and the second lever portion 142b are in the closed state, as shown in FIG. 1, the first clamp portion 141a and the second clamp portion 142a, which are the respective leading ends, are also closed, and the band ends. As shown in FIG. 2, when the first lever portion 141b and the second lever portion 142b are open, the first clamp portion 141a and the second clamp portion are sandwiched between the coupled portions 42c of 42a and 42b. 142a is also opened, so that the coupled portion 42c is released and the band ends 42a and 42b are separated as a result.

  As shown in FIG. 1, the guide member 144 that supports the first band end coupling member 141 and the second band end coupling member 142 has an elongated shape. When the front end side of the first band end coupling member 141 and the second band end coupling member 142 is the front and the rear end side is the rear, the lever opening / closing connecting portion 143 is located in front of the guide member 144. The first band end coupling member 141 and the second band end coupling member 142 are rotatably supported in front of the elongated guide member 144. In addition, a connecting portion moving slit 144a, which will be described later, is provided behind the guide member 144.

  As described above, the first band end coupling member 141 and the second band end coupling member 142 are directly supported by the guide member 144 via the lever opening / closing connecting portion 143, but are further guided via the link mechanism 145. 144 is indirectly supported. The link mechanism 145 includes a first link member 451, a second link member 452, and a link interlocking connection portion 453.

  One end of the first link member 451 is rotatably supported by the first lever portion 141b of the first band end coupling member 141 via the first lever / link connecting portion 141c, and the other end is linked and linked. It is rotatably supported by the guide member 144 via the portion 453. Further, one end of the second link member 452 is rotatably supported by the second lever portion 142b of the second band end coupling member 142 via the second lever / link connecting portion 142c, and the other end is linked. The guide member 144 is rotatably supported by the interlocking connecting portion 453. Further, the other ends of the first link member 451 and the second link member 452 are collectively supported by a single link shaft (coaxial) by the link interlocking connection portion 453.

  The link interlocking connection part 453 is provided so as to be movable in the front-rear direction with respect to the guide member 144 by fitting into the connection part moving slit 144a of the guide member 144. Further, as shown in FIG. 1, when the first clamp part 141a and the second clamp part 142a are closed, the link interlocking connection part 453 is located in front of the guide member 144, and as shown in FIG. In the state where the one clamp part 141a and the second clamp part 142a are opened, the inside of the connecting part moving slit 144a is moved back and forth so as to be positioned behind the guide member 144.

  In the state where the band ends 42a and 42b of the band member 42 are coupled, the rear ends of the first lever portion 141b and the second lever portion 142b are prevented so that the first clamp portion 141a and the second clamp portion 142a are not opened. The parts are connected by a lever fixing member 146.

  In the band coupling device 14A having the above-described configuration, the specific configurations of the first band end coupling member 141, the second band end coupling member 142, the lever opening / closing connecting portion 143, the guide member 144, and the link mechanism 145 are not particularly limited. Any of these may be obtained by materials, dimensions, processing methods and the like known in the field of spacecraft.

  Further, the lever fixing member 146 connects the rear end portions of the first lever portion 141b and the second lever portion 142b so that the first lever portion 141b and the second lever portion 142b do not open (that is, the front end portion). The first clamp part 141a and the second clamp part 142a may be strong enough to prevent the first clamp part 141a and the second clamp part 142a from opening. As the lever fixing member 146, a pin member, a wire member, a string-like member, or the like can be suitably used.

  Here, the position at which the first lever portion 141b and the second lever portion 142b are connected to each other by the lever fixing member 146 is the rear end portion in the present embodiment, but of course is not limited to this position. However, the first lever portion 141b and the second lever portion 142b are configured to be openable and closable by using the lever opening / closing connecting portion 143 adjacent to the distal ends of the first band end coupling member 141 and the second band end coupling member 142 as a fulcrum. Therefore, if the connection is made as far back as possible, the strength required for the lever fixing member 146 can be made relatively small. In consideration of this point, the lengths of the first band end coupling member 141 and the second band end coupling member 142, the position of the lever opening / closing connection portion 143, and the like can be appropriately set.

[Operation of band combiner]
Next, the operation of the band coupling device 14A having the above configuration will be described with reference to FIGS. First, a first spacecraft and a second spacecraft (not shown) are detachably fixed by a separation structure. This separation structure includes a band member 42 that is fixedly supported in a state in which the outer periphery of the connection portion between the spacecrafts is tightened. As shown in FIG. 1, the band member 42 is in a closed state by connecting the band ends 42a and 42b, which are both ends thereof, with the band coupling device 14A.

  The first lever portion 141b and the second lever portion 142b of the band coupling device 14A are in a closed state with the lever opening / closing connecting portion 143 as the opening / closing axis. At this time, as shown in FIG. 1, the first link member 451 and the second link member 452 are in a state along the first lever portion 141b and the second lever portion 142b. It is located between the parts 142b. At this time, the link interlocking connection part 453 is located at the front end in the connection part moving slit 144a.

  As described above, the other ends of the first link member 451 and the second link member 452 are rotatably connected by the link interlocking connection portion 453. One end of the first link member 451 is rotatably connected to the first lever portion 141b via the first lever / link connecting portion 141c, and one end of the second link member 452 is connected to the second lever portion 142b. The second lever-link connecting portion 142c is rotatably connected. Therefore, if the first lever portion 141b and the second lever portion 142b are closed, the connected first link member 451 and second link member 452 are bent such that the link interlocking connection portion 453 is a starting point. Therefore, the link interlocking connection part 453 is located in front of the guide member 144.

  Next, when the band member 42 is opened to separate the first spacecraft and the second spacecraft (not shown), the lever fixing member 146 (the pin member in FIG. 1) is cut. Accordingly, the connection between the rear end portions of the first lever portion 141b and the second lever portion 142b is released, so that the first lever portion 141b and the second lever portion 142b are gradually opened. At this time, the opening operation of the first lever portion 141b and the second lever portion 142b is synchronized by the link mechanism 145.

  When the operations of the first lever portion 141b and the second lever portion 142b are synchronized by the link mechanism 145, the first clamp portion 141a and the second clamp portion 142a are also opened while being synchronized. Further, since the link mechanism 145 is provided, the opening operation of the first clamp part 141a and the second clamp part 142a is relatively slow due to the inertia when the first lever part 141b and the second lever part 142b are opened. Become. Therefore, the band ends 42a and 42b coupled to each other by the band coupling device 14A are gradually opened at equal intervals with reference to the position in contact with the coupling.

  The operation in which the first clamp part 141a and the second clamp part 142a are opened synchronously by the link mechanism 145 will be specifically described. As the first lever portion 141b and the second lever portion 142b open to each other, one end of the first link member 451 and one end of the second link member 452 move so as to increase the distance from each other. As a result, the first link member 451 and the second link member 452 that have been bent at the link interlocking connecting portion 453 are opened so as to be close to a substantially straight line, as shown in FIG. Along with this operation, the link interlocking connecting portion 453 gradually moves from the front end in the connecting portion moving slit 144a to the rear side.

  That is, when the first lever portion 141b and the second lever portion 142b are closed, the first clamp portion 141a and the second clamp portion 142a are closed, and the link interlocking connection portion 453 is close to the lever opening / closing connection portion 143. The first link member 451 and the second link member 452 are closed between the first lever portion 141b and the second lever portion 142b by being positioned in the state, but the first lever portion 141b and the second lever portion 142b are As the link interlocking connection part 453 moves away from the lever opening / closing connection part 143 as it opens, the first link member 451 and the second link member 452 open.

  Therefore, the operation of opening the first lever portion 141b and the second lever portion 142b and the operation of opening the first link member 451 and the second link member 452 are linked. When the first lever part 141b and the second lever part 142b are opened, the first clamp part 141a and the second clamp part 142a are operated by interlocking the inertia (or moment) with the first link member 451 and the second link member 452. Will open at a relatively low speed.

  Further, since the first lever portion 141b and the second lever portion 142b are opened in synchronization with the opening operation of the first link member 451 and the second link member 452, the first clamp portion 141a and the second clamp portion are opened. 142a also opens in synchronization. When the first clamp part 141a and the second clamp part 142a are opened, the band ends 42a and 42b that have been joined by the sandwiched part 42c being sandwiched are gently released, but the band ends 42a and 42b are If the position that was in contact at the time of coupling is a reference (joining position), the first clamp part 141a and the second clamp part 142a are gently opened in synchronization, so that the band ends 42a and 42b are separated from each other from the joining position. It opens so that the distance to band edge 42a, 42b increases at equal intervals.

  Since the band coupling device 14A operates in this manner, the coupling between the band ends 42a and 42b sandwiched between the first clamp part 141a and the second clamp part 142a is not likely to be suddenly released. It is avoided that 42 is instantaneously cut, and the band member 42 opens gently and substantially evenly.

  The band member 42 is not simply wound around the outer periphery of the connecting portion between the spacecrafts, but is wound in a tightened state. Therefore, the connecting portion (frame or the like) is deformed by the tightening force, and strain energy is accumulated. If the band member 42 is gradually opened in this state, the deformation of the connecting portion is gradually relaxed, and therefore the strain energy is gradually released. Moreover, the distance between the band ends 42a and 42b is increased substantially uniformly. Therefore, the relaxation of the deformation of the connecting portion proceeds as a whole, so that the strain energy is also released in a balanced manner. As a result, the impact at the time of separation occurring in the spacecraft can be sufficiently reduced.

  In particular, when the first spacecraft is a rocket body and the second spacecraft is an artificial satellite, the deformation due to tightening is relatively large because the artificial satellite is smaller than the rocket body. If the tightening of the band member 42 is suddenly released in such a state, the influence of the impact becomes large particularly on the artificial satellite side. On the other hand, in the present embodiment, the band members 42a and 42b are not simply opened gently but opened by synchronizing the first clamp part 141a and the second clamp part 142a. Since the intervals of are expanded almost uniformly at a low speed, the release of strain energy is slowed and biased. As a result, it is possible to further reduce the impact generated on the artificial satellite side.

  Further, as shown in FIG. 2, when the link interlocking connecting portion 453 reaches the rear end in the connecting portion moving slit 144a, the first link member 451 and the second link member 452 are stopped in an open state. In particular, in the present embodiment, both of the first link member 451 and the second link member 452 are bent at the center so that both end portions are located on the rear side and the center portion is on the front side when both are opened. It has a different shape. As a result, in the state where the first lever portion 141b and the second lever portion 142b are completely opened, the link interlocking connection portion 453 stops at the rear end side of the guide member 144, but the first link member 451 and the second link The member 452 is opened in a state where the link interlocking connecting portion 453 protrudes rearward.

  The link interlocking connection part 453 is a part where the other ends of the first link member 451 and the second link member 452 are connected to each other, and the first link member 451 and the second link member 452 are bent. Therefore, when viewed from at least the center portions of the first link member 451 and the second link member 452, the link interlocking connection portion 453 which is the other end to be connected becomes convex from the center portion toward the rear side. Is located. In this state, since the first link member 451 and the second link member 452 function like a beam between the first lever portion 141b and the second lever portion 142b, the first lever portion 141b and the second lever The part 142b is held in the fully opened state.

  Therefore, even if the band coupling device 14A leaves the band member 42 and drifts in outer space after the ring member 42 is opened, the first lever portion 141b and the second lever portion 142b repeatedly open and close, and the frame of the artificial satellite. It is possible to avoid collision with the belt member or contact with the end of the band member 42. Therefore, the possibility that the separation behavior of the spacecraft is hindered by the band coupling device 14A becomes very low, and a more stable separation operation can be realized.

  In addition, the fact that the impact generated on the satellite side can be further reduced makes it possible to set the tightening force of the connecting portion by the band member 42 large. Therefore, the connection state of the spacecraft can be further stabilized, and the allowable range such as variation in tension when the band member 42 is wound, setting error of the tightening force of the band member 42, and the like is expanded. be able to. As a result, it is possible to improve the reliability and operability of the spacecraft separation structure.

[Modification]
The length of the first link member 451 and the second link member 452 or the length of the connecting portion moving slit 144a of the guide member 144 depends on various conditions such as the type of spacecraft and the size of the connecting portion. Adjusting the opening time of the first clamp part 141a and the second clamp part 142a, or adjusting the angle when the first lever part 141b and the second lever part 142b are fully opened. Can do. As a result, it is possible to further improve the relaxation of the impact and to further reduce the influence of the band coupling device 14A after ring opening.

  In the present embodiment, a combination of a rocket body and an artificial satellite is given as an example of a spacecraft, but the present invention is not limited to this, and various spacecrafts are connected. The present invention can be used.

  Further, in the present embodiment, the first clamp part 141a and the second clamp part 142a of the band coupling device 14A sandwich (pick) the coupled parts 42c and 42c protruding outside the band ends 42a and 42b. The band ends 42a and 42b are connected to each other, but the coupled portion 42c is not limited to a configuration protruding outward. For example, the band ends 42a and 42b may have recesses, and the first clamp part 141a and the second clamp part 142a may be inserted into the recesses. Alternatively, as a coupled portion, a portion that is a three-dimensional shape other than a convex portion or a concave portion and can be sandwiched between the first clamp portion 141a and the second clamp portion 142a when the band ends 42a and 42b are connected to each other. You may have.

  In the present embodiment, the link interlocking connecting portion 453 is configured to move in the connecting portion moving slit 144a formed in the guide member 144. However, the present invention is not limited to this, and the link interlocking connecting portion is provided. It is only necessary for the portion 453 to move away from or close to the lever opening / closing connection portion 143 (movement in the front-rear direction) at a position behind the lever opening / closing connection portion 143 in the guide member 144. For example, the guide member 144 may be provided with a rail-like structure, and the link interlocking connecting portion 453 may be fitted so as to be movable on the rail structure, or a mechanical structure such as a rack-pinion may be used. A configuration may be provided. Furthermore, the guide member 144 may not have an elongated shape, but may have a shape spreading so as to cover the first band end coupling member 141 and the second band end coupling member 142.

  Further, the first link member 451 and the second link member 452 may not be bent, but may be substantially linear or curved. However, if it is the shape bent in the center part like this Embodiment, compared with the case where the 1st link member 451 and the 2nd link member 452 are linear shapes, the 1st lever part 141b and the 2nd When the lever portion 142b is fully opened, the link interlocking connecting portion 453 can be projected rearward with a shorter dimension, which is preferable.

(Embodiment 2)
In the second embodiment of the present invention, the present invention will be described more specifically based on a specific example of a spacecraft separation structure to which the band coupling device according to the first embodiment is applied. The spacecraft separation structure according to the present embodiment includes a Marman clamp band, and a band coupling device is used to release the coupling of the Marman clamp band.

[Marman clamp band]
First, the Marman clamp band will be specifically described with reference to FIGS. 3 (a), 3 (b) and FIG. As shown in FIG. 3A, a Marman clamp band 41 according to the present embodiment includes a metal band member 42 and a band coupling device 14B that detachably couples the end portions of the band member 42. A coupling device fixing member 43 for fixing the band coupling device 14B to a rocket main body (not shown), a band fastening portion 44 for tightening or loosening the band member 42, and a plurality of members for fixing the band member 42 to a rocket main body (not shown). The band catcher 45 is provided. The band coupling device 14B includes a lever fixing mechanism 10 having a mechanical configuration instead of the lever fixing member 146 that is the pin member described in the first embodiment. In addition, the specific structure of the lever fixing mechanism 10 is not specifically limited, A well-known structure can be used suitably.

  Further, as shown in FIG. 3B, the rocket body 51 and the artificial satellite 52 are fixedly connected by a known separation structure (not shown), and the Marman clamp band 41 surrounds the outer periphery of the connection portion. Is wound and provided. The rocket body 51 is provided with a satellite connection surface 51a indicated by a two-dot chain line in the figure, and a plurality of band catchers 45 and a coupling device fixing member 43 are attached around the satellite connection surface 51a. The band catcher 45 supports the band member 42 while being fixed to the rocket body 51, and the coupling device fixing member 43 supports the band coupling device 14 </ b> B while being fixed to the rocket body 51. With such a configuration, the Marman clamp band 41 is fixed to the rocket body 51.

  As shown in FIG. 4, in this embodiment, the coupling device fixing member 43 is a member that protrudes to the outside from the side surface in the vicinity of the satellite connection surface 51a of the rocket body 51, and has a shape bent substantially at a right angle. doing. One end is attached to the outer peripheral surface of the rocket main body 51, and the band coupling device 14B including the lever fixing mechanism 10 is attached to the other end. The specific configuration of the coupling device fixing member 43 is not particularly limited, and a support member known in the field of spacecraft can be suitably used.

  In FIG. 3B, the band catcher 45 adjacent to the coupling device fixing member 43 is shown by a broken line for convenience of explaining the positional relationship among the band coupling device 14B, the coupling device fixing member 43, and the rocket body 51. Yes. Moreover, each member or mechanism which comprises the Marman clamp band 41 shown to Fig.3 (a), (b) is not specifically limited, The thing of various well-known structures can be used conveniently. Similarly, the configurations of the rocket main body 51 and the artificial satellite 52 that are separably held by the Marman clamp band 41 are not particularly limited. Furthermore, the spacecraft maintained in the connected state by the Marman clamp band 41 is not limited to a rocket, an artificial satellite, or the like, and may be a spacecraft of another configuration.

  It should be noted that the present invention is not limited to the description of the above-described embodiment, and various modifications are possible within the scope shown in the scope of the claims, and are disclosed in different embodiments and a plurality of modifications. Embodiments obtained by appropriately combining the technical means are also included in the technical scope of the present invention.

  INDUSTRIAL APPLICABILITY The present invention is a separation structure for connecting and fixing a spacecraft so as to be separable, and is widely and suitably used in the field of a separation structure including a band member that is wound in a state where a connection portion is tightened. Can do.

DESCRIPTION OF SYMBOLS 10 Lever fixing mechanism 14A, 14B Band coupling device 20 Female coupling body 30 Male coupling body 41 Marman clamp band 42 Band member 42a, 42b Band end (end part of band member)
42c Coupled part 51 Rocket body (first spacecraft)
52 Artificial satellite (second spacecraft)
141 First band end coupling member (band end coupling member)
141a First clamp part (clamp part)
141b First lever part (lever part)
142 Second band end coupling member (band end coupling member)
142a Second clamp part (clamp part)
142b Second lever part (lever part)
143 Lever opening / closing connection part (connection shaft part)
144 Guide member 144a Connecting portion moving slit (slit)
145 Link mechanism 146 Lever fixing member 451 First link member (link member)
452 Second link member (link member)
453 Link interlocking connection part

Claims (8)

A band member that is used for a spacecraft separation structure that separably fixes a second spacecraft to the first spacecraft, and that is fixedly supported in a state where the outer periphery of a connection portion between the spacecrafts is tightened. A band coupling device that maintains the ends in a separably coupled state,
In a state where they intersect with each other in the longitudinal direction, they are connected to each other by a connecting shaft part, and each end part opens and closes with the connecting shaft part as a starting point, and is connected by sandwiching a connected part provided at an end part of the band member. A pair of band end coupling members, which are clamp portions, and which are lever portions that open and close in conjunction with the clamp portions at the rear end side from the connecting shaft portion;
A guide member supported by the connecting shaft portion and extending from the connecting shaft portion to the rear end side of the lever portion;
A pair of link members each having one end rotatably supported by each lever portion of the band end coupling member and each other end rotatably supported coaxially by the guide member;
A link interlocking connecting portion provided on the guide member, wherein the other end of the pair of link members is rotatably connected, and is movable in a direction away from the connecting shaft portion.
When the lever portion is closed, the clamp portion is closed, and the link interlocking connecting portion is located in a state of being close to the connecting shaft portion, so that the pair of link members are located between the lever portions. Closed with
The band coupling device is configured to open the pair of link members by moving the link interlocking connecting portion away from the connecting shaft portion as the lever portion opens. .   In the state where the lever portion is fully opened, the link interlocking connecting portion stops on the rear end side of the lever portion in the guide member, and the pair of link members are connected at the other end to the lever portion. The band coupling device according to claim 1, wherein the band coupling device is opened so as to protrude to the rear end side of the band.   The pair of the link members have a shape that is bent at a central portion so that both end portions thereof are located on a rear end side of the lever portion in a state where they are opened. A band coupling device according to claim 1.   The band coupling device according to claim 1, wherein the guide member is provided with a slit that is movably held in a state in which the link interlocking connection portion is fitted.   2. The band coupling device according to claim 1, wherein the coupled portion at the end of the band member is a convex portion projecting toward an outer periphery of the band member.   2. The band coupling device according to claim 1, further comprising a lever fixing member configured to connect the rear end portions of the lever portions so as to prevent the lever portions from being opened.   The band coupling device according to claim 1, wherein the band member is a Marman clamp band that fixes the second spacecraft to the first spacecraft. The band coupling device according to claim 7, wherein the first spacecraft is a rocket body, and the second spacecraft is an artificial satellite.

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