JP5417040B2 - Sliding fairing decapitation device and sliding fairing decapitation method - Google Patents

Description

  The present invention relates to a sliding fairing deheading device and a sliding fairing deheading method for deheading a fairing that covers the tip of a rocket body and forms a receiving space for storing a load.

  The conventional method for opening the fairing on the tip of the rocket body when exposing the space observation equipment to outer space or making the satellite separable is the clamshell open (divided open) method. There is a decapitation (integrated craniotomy) method.

FIG. 1 shows a clamshell cleaving (split cleaving) system described in Non-Patent Document 1.
The clamshell open (divided open) method is roughly divided into a parallel open method, a non-parallel open method, and a two-stage open method.
As shown in Non-Patent Document 1, the clamshell opening (divided opening) method has a structure in which the fairing can be divided into two or more. This is a system in which the divided fairing crest is separated from the aircraft by rotating it around a certain center of rotation. This will be described in detail with reference to FIG.

FIG. 1A shows a parallel craniotomy method. In this method, the head opening 101 is bisected symmetrically with the body axis 102, and each head opening piece is pushed out in the direction perpendicular to the body axis and without rotation by the front spring 103 and the rear spring 104.
FIG. 1B shows a non-parallel craniotomy method. In this method, the frontal spring 103 and the rearward spring 104 are adjusted in strength so that the craniotomy piece is rotated so as to open from the tip of the craniotomy.
FIG. 1 (C) shows a two-stage opening method. This is a system in which the head opening 101 is divided into a conical portion 105 and a cylindrical portion 106, the conical portion 105 is first opened nonparallel, and then the cylindrical portion 106 is opened parallel.

Non-patent document 2 describes the decapitation (integrated craniotomy) method. As shown in FIG. 2, the fairing 201 is separated and opened in the machine direction 202 while being integrated.
The fairing 201 of the decapitation (integrated crawling) method requires a relatively large separation force so that the fairing 201 can be separated and opened without contacting the airframe and the load, and the fairing 201 is parallel to the airframe axial direction 202. 201 needs to be separated. For this reason, springs or the like with small variations are arranged at several locations on the fairing 201.
In addition, after the fairing 201 is separated, in order not to bring the fairing 201 into contact with the aircraft, the aircraft is maneuvered (the jet fuel mounted on the aircraft is injected to correct the position and attitude of the satellite). It is necessary to avoid rear-end collision and contact with the fairing 201 due to airframe propulsion after separation.

About a few mechanisms of mu rocket, the University of Tokyo Aerospace Research Institute report Vol.8 No.2 (A) ISRAEL AIRCAFFT INDUSTRIES, LTD homepage URL: http: // www. ii. co. il / sip_storage / files / 8/35368. pdf

However, if the structure is such that the fairing can be divided as in the clamshell open (divided open) method, two or more fairings must be joined together without any gaps, requiring high-precision processing and assembly techniques. End up.
In addition, the split surface needs to be relatively long, which reduces the rigidity of the fairing. Therefore, the coupling / separation mechanism is continuously arranged or wrapped around the split surface so that it does not open due to aerodynamic loads during flight. It becomes necessary to provide a margin, and the fairing structure becomes complicated.
Furthermore, in order to prevent the separated fairing crest from coming into contact with the airframe and payload (satellite, observation equipment, etc.), many techniques and time are required for designing and selecting the size, rigidity, division, and separation form of the craniotomy piece. Is required.

In addition, even if the decapitation (integrated craniotomy) method is selected, a relatively large separation force is required to separate and open the decapitated fairing without contacting the aircraft or payload (satellite, etc.). In addition to the output spring and the structural strength required to antagonize the output, the size of the fairing to be separated is limited depending on the separation force.
Moreover, in order to separate in parallel with the machine axis direction, it is necessary to reduce the variation in separating force such as springs arranged at several places, and a large amount of labor is required for adjustment and management.
Further, since the aircraft and the fairing are still in the same straight line after the fairing is separated and opened, it is necessary to maneuver the aircraft to avoid the fairing.

  The present invention has been developed to solve the above-described problems. That is, an object of the present invention is to provide a sliding fairing decapitation apparatus and a sliding fairing decapitation method that are easy to design, process and assemble, have a simple structure, and are easy to maintain rigidity. is there. In addition, the object of the present invention is to eliminate the need for adjusting and managing the variation of the separation force such as the spring, and to eliminate the fairing by maneuvering the airframe and the sliding fairing decapitation It is to provide a method.

According to the present invention, there is a sliding fairing decapitation device provided in a rocket that has a space for accommodating a load and releases the load to outer space,
A fairing that covers the tip of the rocket body and forms a storage space for storing the load,
A plurality of slide rails positioned between the fairing and the load,
Only one of the slide rails is longer than the other slide rails,
A sliding fairing decapitation device is provided, wherein the fairing slides along the slide rail and is decapitated by rotating around the end of a slide rail longer than the other slide rails. .

According to an embodiment of the present invention, only one of the slide rails is a long slide rail longer than the other slide rails,
The other slide rail is a short slide rail shorter than the long slide rail,
A hook-type slider that slides on the rail is attached to the long slide rail, and a slide end that stops the slide of the hook-type slider is provided at the end of the long slide rail,
A hook pin that is attached to an inner peripheral portion of the fairing so as to be hooked to the hook-type slider and can be detached from the hook-type slider, and an inner peripheral portion of the fairing are integrated with the short slide. An integrated slider that slides on the rail along the rail guide is attached.

In addition, a connecting portion is provided at the rear end of the fairing,
A single spring is provided on the inner side of the fairing on the central axis,
When the coupling part is opened, the fairing slides along the slide rail by the pushing force of the spring,
When the integrated slider reaches the end of the short slide rail, the fairing and the integrated slider are integrally removed from the short slide rail,
When the hook-type slider reaches the end of the long slide rail, the hook-type slider stops at the slide end. Rotate around
Thereafter, the fairing is removed from the rocket by removing the hook pin from the hook-type slider.

In addition, according to the present invention, the fairing that forms the accommodating space that covers the tip of the rocket body and accommodates the loaded object,
Only one slide between the fairing and the load and slides along a plurality of slide rails longer than the others,
There is provided a sliding fairing decapitation method characterized in that the head is decapitated by rotating around the end of a slide rail longer than the other slide rails.

  According to the sliding fairing decapitation apparatus and the sliding fairing decapitation method described above, since it is not necessary to divide the fairing, it is easy to maintain the rigidity of the fairing, and processing and assembly by integral molding Man-hours can be reduced.

  In addition, since the behavior at the time of fairing separation is constrained by the above-described slide rail, there is no need to worry about contact with the airframe or the load (payload of an artificial satellite, a probe, an observation device, etc.).

  In addition, since the spring is disposed in the dead space at the front end of the fairing and the behavior of the fairing by the slide rail is restricted, the load envelopment area can be expanded.

  In addition, since only one spring is provided on the inner side of the center axis of the fairing, the number of springs can be reduced compared to the form of pushing up from the rear end of the fairing as in the case of the decapitation (integrated craniotomy) method. In addition, it becomes unnecessary to manage the variation in the spring output.

Furthermore, since the fairing after separation is separated from the body axis direction by the hook type slider, the hook pin, and the slide end, a maneuver operation for avoiding re-collision with the fairing is not necessary.

FIG. 1 shows a conventional clamshell cleaving (divided cleaving) method described in Non-Patent Document 1. (A) is a parallel craniotomy system, (B) is a non-parallel craniotomy system, (C) is a figure which shows a two-stage craniotomy system. FIG. 2 shows a conventional technique of the decapitation (integrated craniotomy) method described in Non-Patent Document 2. FIG. 3 is an overall configuration diagram of a rocket having the sliding fairing decapitation apparatus according to the first embodiment of the present invention. FIG. 4 is a diagram illustrating the configuration of the hook-type slider and a mechanism for detaching the hook pin from the hook-type slider when the fairing is removed. FIG. 5 is a perspective view of a long slide rail, a hook-type slider, a slide end, and a hook pin. FIG. 6 is a diagram showing various configurations of the hook-type slider and trends of the hook pins. (A) is a type in which the buttocks are straight and short. (B) is a type in which the hook groove of the hook type slider draws an arc and the hook pin is easily rotated. (C) is the type which lengthened the buttocks of (B). FIG. 7 is a diagram for explaining a sliding fairing removal method using the sliding fairing removal device of the first embodiment of the present invention. FIG. 8 is a diagram for explaining a sliding fairing removal method using the sliding fairing removal device of the second embodiment of the present invention. FIG. 9 is a diagram for explaining a sliding fairing removal method using the sliding fairing removal device of the third embodiment of the present invention.

  Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

FIG. 3 is an overall configuration diagram of a rocket having the sliding fairing decapitation apparatus of the present invention. The present invention has a structure that includes a fairing that covers the tip of the rocket body and forms an accommodation space for accommodating a load, and a plurality of slide rails positioned between the fairing and the load.
In addition, the sliding fairing decapitation method of the present invention is mainly used for separating and opening the fairing of a rocket that has a space for accommodating a load such as a small satellite launch rocket or an observation rocket and that discharges the load to outer space. Is possible.

The fairing 1 has a structure including a cone having a rounded tip and a cylinder. The fairing 1 is placed on the tip of the rocket main body 2 to form an accommodation space for accommodating the load 3. The structural form may be a honeycomb sandwich shell structure. The surface plate from the sandwich not only reduces the weight, but also suppresses deformation of the structure due to external loads and increases the space-borne area for specific strength and specific rigidity. High CFRP may be applied. A single spring 4 is provided on the inner side of the center axis 20 of the fairing 1.
An integral slider 10 and a hook pin 14 (not shown) (see FIGS. 4 and 5) are attached to the inner peripheral portion of the rear end of the fairing 1. The integrated slider 10 and the hook pin 14 will be described in detail later.
Moreover, the coupling | bond part 21 is provided in the rear end of the fairing 1, and the coupling | bond part 21 can be open | released by pyrotechnics etc. now.

The spring 4 of the fairing 1 is provided between the outer cylinder 5 and the inner cylinder 6 provided on the inner side of the center axis 20 of the fairing 1. The front end of the outer cylinder 5 is provided so as to contact the inside of the front end of the fairing 1, and a hole through which the inner cylinder 6 passes is provided at the rear end. The inner cylinder 6 is designed so that the front end is in the outer cylinder 5 and the rear end is in contact with a frame 7 provided in the rocket body 2. The front end of the spring 4 is in contact with the front end on the central axis of the outer cylinder 5, and the rear end is in contact with the front end of the inner cylinder 6. The fairing 1 is coupled to the rocket body 2 by a coupling portion 21 in a state where the spring 4 is sufficiently compressed.
That is, when the coupling portion 21 at the rear end of the fairing 1 is opened, the inner cylinder 6 is pushed out of the outer cylinder 5 by the elasticity of the spring 4 attached to the fairing 1, and the fairing 1 is moved in the axial direction by the pushing force of the spring 4. Designed to slide into.

  The slide rail is located between the fairing 1 and the load 3. Also, there are a plurality of slide rails, and only one is configured to be longer than the other slide rails. The short slide rail is called a short slide rail 8, and the long slide rail is called a long slide rail 9.

  On the short slide rail 8, an integrated slider 10 attached integrally with the inner peripheral portion of the fairing 1 is configured to slide on the rail along the guide of the short slide rail 8. The terminal 17 of the short slide rail 8 is not provided with a device such as a stopper for stopping the sliding of the integrated slider 10. That is, the integrated slider 10 that slides together with the fairing 1 is configured to be detached from the short slide rail 8 together with the fairing 1. Two or three short slide rails 8 are preferable, but may be more or less.

A hook type slider 11 that slides on the long slide rail 9 along the guide of the long slide rail 9 is attached to the long slide rail 9. The hook-type slider 11 can slide on the rail with little resistance.
A slide end 12 is provided at the end of the long slide rail 9 and is configured to stop the sliding slider 11 from sliding.

  Carrying objects such as satellites and space observation equipment are mounted inside the slide rail.

Next, the hook type slider 11 will be described with reference to FIG. FIG. 4 is a diagram illustrating the configuration of the hook-type slider and a mechanism for detaching the hook pin 14 from the hook-type slider 11 when the fairing is removed.
A groove 13 is formed in the hook type slider 11, and a hook pin 14 attached to the inner peripheral portion of the fairing 1 is hooked in the groove 13. The groove 13 of the hook-type slider 11 is in a stage before the coupling portion 21 of the fairing 1 is opened (for example, fractured by pyrotechnics) as shown in (A) (that is, before the fairing 1 slides). When the accommodating portion 11a in which the hook pin 14 is accommodated and the coupling portion 21 of the fairing 1 are opened and begin to slide, the hook pin 14 is hooked together with the slide of the fairing 1 as shown in (B) and (C). The integrated slider 10 is disengaged from the push-out portion 11b for moving the mold slider 11 and the short slide rail 8, and the slide of the hook-type slider 11 is stopped by the slide end 12 and the fairing 1 rotates around the hook pin 14. At the time, as shown in (D), it consists of a hook part 11c that helps the rotation of the hook pin 14.

The hook-type slider 11 is pushed up by the hook pin 14 as the fairing 1 slides, and when the fairing 1 rotates around the hook pin 14, the hook pin 14 can be detached from the hook-type slider 11. It is configured.
Since the short slide rail 8 and the long slide rail 9 are installed in parallel, the fairing 1 slides in parallel with the slide rails 8 and 9. In other words, since the external force is applied to the hook type slider 11 from the hook pin 14 in the axial direction, the hook pin 14 is not detached from the hook type slider 11 before the integral slider 10 is detached from the short slide rail 8. In addition, since there is almost no external force other than the pushing force of the spring 4 in the zero-gravity state in outer space, even if the integrated slider 10 is detached from the short slide rail 8, the fairing 1 has the slide rails 8, 9 Continue to slide in parallel. Therefore, the hook pin 14 does not come off the hook-type slider 11 until the hook-type slider 11 is stopped from sliding by the slide end 12.
Further, if the hook type slider 11 collides with the slide end 12 immediately after the integrated slider 10 is detached from the short slide rail 8 and the fairing can be rotated, the thrust of the rocket is still present, Even when there is air resistance due to the atmosphere, craniotomy according to the present invention is possible.

FIG. 5 is a perspective view of the long slide rail 9, the hook type slider 11, the slide end 12, and the hook pin 14.
The hook pin 14 has a cylindrical shape bent at a right angle in this figure, but if it can slide in the groove 13 of the hook type slider 11, it will be bent in a U shape and fixed to the inner wall of the fairing 1 at two locations. It may be. Other shapes may also be used.
Further, in this figure, the projection 15 of the hook type slider 11 is configured to fit into the groove 16 on the rail, but other methods may be used as long as the hook type slider 11 can slide on the rail with little resistance.
In this figure, reference numeral 14a in the figure is a cross section of the hook pin 14 in contact with the fairing.

FIG. 6 is a diagram showing various configurations of the hook-type slider 11 and trends of the hook pins 14. (A) is a type in which the buttocks are straight and short. In the case of such a configuration, the hook pin 14 is rotated in the flange portion 11c and detached in the direction perpendicular to the aircraft axis, but the fairing 11 is rotating, and the rocket load 3 and the like advances in the aircraft axis direction. Therefore, it is thought that the fairing and the load will not collide.
(B) is a type in which the groove of the hook portion 11c of the hook type slider forms an arc, and the hook pin 14 is easily rotated. Compared to (A), the fairing 1 is more likely to go backward, and the possibility of a collision with the load 3 is further reduced.
(C) is the type which lengthened the collar part 11c of (B). (C) is not only easy to rotate as in (B), but also can release the fairing 1 by releasing it from the load or the like more than (B). Thereby, the possibility of the collision between the fairing 1 and the load 3 is further reduced as compared with (B).
(D) is a type in which the flange portion 11c is formed obliquely. By constructing the flange portion 11c obliquely, it is possible to satisfactorily balance the straight travel and the rotation without using all the force in the straight direction due to the pushing force of the spring 4 as the rotational force. (D) can be effectively used especially when the rocket body 2 is spinning.

Next, a sliding fairing removal method using the sliding fairing removal device will be described with reference to FIG.
(A) is a state before the coupling portion 21 of the fairing 1 is opened, (B) is a state where the integrated slider 10 of the fairing 1 is detached from the short slide rail 8, and (C) is a state where the fairing 1 is rotated. (D) is a figure which shows the state which the decapitation of the fairing 1 was completed from the rocket main body 2. FIG.
When the fairing 1 is decapitated, when the coupling portion 21 is opened, the fairing 1 slides along the slide rails 8 and 9 by the pushing force of the spring 4 as shown in FIG. When the integrated slider 10 reaches the terminal end 17 of the short slide rail 8, the fairing 1 and the integrated slider 10 are integrally removed from the short slide rail 8. At this point, the traveling direction of the fairing 1 and the traveling direction of the rocket body 2 are the same.
As shown in (C), when the hook-type slider 11 is pushed by the hook pin 14, is guided by the long slide rail 9 and slides, and reaches the end of the long slide rail 9, the hook-type slider 11 is moved to the slide end 12. The hooking pin 14 slides in the hook-type slider 11 and the hooking pin 14 is hooked on the flange portion 11c, so that the fairing 1 rotates around the hooking pin 14. Then, the fairing 1 is removed from the rocket when the hook pin 14 is detached from the hook-type slider 11.
(D) is a figure which shows the state which the decapitation of the fairing 1 was completed from the rocket main body 2. FIG. Since the load 3 is housed inside the slide rails 8 and 9, even when the fairing 1 is decapitated, the fairing 1 does not come into contact with the load 3 and is not damaged. Therefore, the load 3 can be safely stored and released into outer space.

FIG. 8 shows a second embodiment of the present invention. As shown in the figure, in the second embodiment, the upper frame 18 of the frame 7 attached to the rocket body 2 is attached to the rear end of the inner cylinder 6, and the upper frame 18 is discharged together with the fairing 1. Take.
Other configurations are the same as those in the first embodiment.
With this configuration, since the front of the load 3 is vacant, the load 3 can be released from the front of the rocket body 2.

FIG. 9 is a diagram showing a third embodiment of the present invention. As shown in the figure, in the third embodiment, after the decapitation of the fairing 1 is completed, the slide rails 8 and 9 are tilted outward. For example, a mechanism 19 (for example, a spring, an actuator, etc.) for tilting the slide rails 8 and 9 outward is installed inside the rear ends of the slide rails 8 and 9. Further, a mechanism (for example, a hinge or the like) that falls in a certain direction may be attached to the rear ends of the slide rails 8 and 9.
Other configurations are the same as those in the first embodiment.
As a result, since a large space can be formed around the load 3 when the load 3 is released, there is no fear of damaging the load 3 and a large size can be selected for the load 3. .

  According to the sliding fairing decapitation apparatus and the sliding fairing decapitation method of the present invention, since it is not necessary to divide the fairing 1, it is easy to maintain the rigidity of the fairing 1, and by integral molding. Reduction of processing and assembly man-hours can be achieved.

  In addition, since the behavior at the time of separation of the fairing 1 is restricted by the slide rails 8 and 9, there is no need to worry about contact with the airframe or the load 3 (payload of an artificial satellite, a probe, an observation device, etc.).

  Further, since the spring 4 is disposed in the dead space at the tip of the fairing 1 and the behavior of the fairing 1 is constrained by the slide rails 8 and 9, the envelope region of the mounted object 3 can be expanded.

  In addition, since only one spring 4 is provided on the inner side of the center axis of the fairing 1, the number of springs 4 is smaller than that in the form of pushing up from the rear end of the fairing as in the case of the decapitation (integral opening) method. This eliminates the need to manage the variation in spring output.

  Furthermore, since the separated fairing 1 is pulled away from the body axis direction by the hook type slider 11, the hook pin 14, and the slide end 12, a maneuver operation for avoiding re-collision with the fairing 1 is not necessary.

  Although the embodiments of the present invention have been described above, the embodiments of the present invention disclosed above are merely examples, and the scope of the present invention is not limited to these embodiments. . The scope of the present invention is indicated by the description of the scope of claims, and further includes meanings equivalent to the description of the scope of claims and all modifications within the scope.

DESCRIPTION OF SYMBOLS 1 Fairing 2 Rocket main body 3 Mounted object 4 Spring 5 Outer cylinder 6 Inner cylinder 7 Frame 8 Short slide rail 9 Long slide rail 10 Integrated slider 11 Hook type slider 11a Housing part 11b Extruding part 11c Eave part 12 Slide end 13 Groove 14 Hook pin 15 Protrusion 16 Groove 17 on rail End of short slide rail 18 Upper frame 19 of frame 19 Spring 20 Central shaft 21 Joint

Claims (5)

A sliding fairing decapitation device provided in a rocket that has a space for accommodating a load and releases the load to outer space,
A fairing that covers the tip of the rocket body and forms a storage space for storing the load,
A plurality of slide rails positioned between the fairing and the load,
Only one of the slide rails is longer than the other slide rails,
A sliding type fairing decapitation device, wherein the fairing slides along the slide rail and is decapitated by rotating around the end of a slide rail longer than the other slide rails. Only one of the slide rails is a long slide rail longer than the other slide rails,
The other slide rail is a short slide rail shorter than the long slide rail,
A hook-type slider that slides on the rail is attached to the long slide rail, and a slide end that stops the slide of the hook-type slider is provided at the end of the long slide rail,
A hook pin that is attached to an inner peripheral portion of the fairing so as to be hooked to the hook-type slider and can be detached from the hook-type slider, and an inner peripheral portion of the fairing are integrated with the short slide. 2. A sliding fairing decapitation device according to claim 1, further comprising an integrated slider that slides on the rail along the guide of the rail. A connecting portion is provided at the rear end of the fairing,
A single spring is provided on the inner side of the fairing on the central axis,
2. The sliding fairing decapitation device according to claim 1, wherein when the coupling portion is opened, the fairing slides along the slide rail by the pushing force of the spring. 3. A connecting portion is provided at the rear end of the fairing,
A single spring is provided on the inner side of the fairing on the central axis,
When the coupling part is opened, the fairing slides along the slide rail by the pushing force of the spring,
When the integrated slider reaches the end of the short slide rail, the fairing and the integrated slider are integrally removed from the short slide rail,
When the hook-type slider reaches the end of the long slide rail, the hook-type slider stops at the slide end. Rotate around
3. The sliding fairing decapitation device according to claim 2 , wherein the fairing is deheaded from the rocket when the hook pin is removed from the hook type slider. A fairing that covers the tip of the rocket body and forms a storage space for storing the load,
Only one slide between the fairing and the load and slides along a plurality of slide rails longer than the others,
A sliding fairing decapitation method, wherein the head is decapitated by rotating around the end of a slide rail longer than the other slide rails.

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