JPH04189700A - Flange tightening band in rocket structural body - Google Patents

Abstract

PURPOSE:To prevent application of a resilency energy accumulated at a flange tightening band on a rocket as an impact force when the rocket is separated by changing a distance from an axial line of the rocket to an engagement member, and providing an expansion member to get the engagement member from a flange at the band. CONSTITUTION:For connecting rocket structural bodies 10, 11, flanges 12, 13 formed at the rocket structural bodies 10, 11 are engaged with an engagement groove 24 of an engagement member 22 of a flange tightening band 20, and both end parts 21b of an arc-like member 21 are connected with each other through a fixing member 21c. Prior to separating the rocket structural bodies 10, 11, the connection length of the arc-like member 21 is elongated to increase a distance R(radius) from an axial line P of the rocket structural bodies 10, 11 to the engagement member 22 to get the engagement member 22 apart from the flanges 12, 13, and firing bolts 21c, 21c are exploded in this condition to separate the arc-like members 21, 21 of the band 20 from each other.

Description

Detailed Description of the Invention (Industrial Application Field) The present invention relates to a rocket structure in which flanges provided at opposing joining ends of rocket structures to be joined and separated from each other are joined in a separable manner. This invention relates to a band for fastening a flange on a body.

(Prior Art) Conventionally, as such a flange fastening band, for example, a flange fastening band as shown in FIGS. (See “Equipment”).

Fig. 7 is a plan view showing a state in which a conventional flange fastening band is fastened to a flange, Fig. 8 is an enlarged sectional view taken along the line ■-■ in Fig. 7, and Fig. 9 is a direction of arrow A in Fig. 8. This is a diagram viewed from above.

This clamping device is used for rocket components, for example, flanges 3 and 4 are formed at each joint end of a rocket structure 1.2 forming the rocket housing.
The flanges 3 and 4 are fastened together via a flange fastening band 5 (hereinafter referred to as a band at the end).

The band 5 is composed of an arcuate piece 6.6 and an engagement member 6b provided on the inner surface 6a of the arcuate piece 6.6. As shown in FIG. 8, this engagement member 6b is formed with an engagement groove 6C in which the flanges 3 and 4 are engaged with each other, and a plurality of engagement grooves 6C are formed on the inner surface 6a of the arcuate piece 6.6. They are placed at appropriate intervals.

The band 5.5 configured in this manner has respective locking portions 6d, 6d and 6e of the arcuate pieces 6,6.

6e are connected via the tinder bolts B, B, so that the flanges 3, 4 are fastened from their outer peripheries.

Moreover, in order to release the coupling of the flange 3.4 and separate the rocket structure 1.2, the tinder bolts B, B are cut or disassembled by explosives.

As a result, the locking portions 6d of the arcuate pieces 6,6.

The connection between 6d, 6e, and 6e is released, and the band 5.5 separates from the flange 3.4 and can be separated (as shown by the chain line in FIG. 7).

Furthermore, the band 5.5 after separation is attached to the band holding member H,
It is reliably held by H....

This band holding member H has an outer surface 6f of the arcuate pieces 6, 6.
an engagement arm 7 extending in the longitudinal direction of the band 5;
a bracket 8 defined proximally to the rocket structure 1;
and a rondo section 9.

When the engagement between the flange 3.4 and the bands 5, 5 is released, the spring 9a of the rod portion 9 is biased to cause the band 5 to reliably separate from the joint flange 3.4, and the band 5 is is configured to hold.

(Problem to be Solved by the Invention) However, in such a conventional clamping device, when connecting the bands 5.5, the bands 5.5 are forcibly deformed into a curved shape against the spring force, thereby creating a strong Since it was tightened with force, the tightening torque was large, and the energy of the torque was stored in the band 5.5 as a restoring force.

Therefore, when the tinder bolts B, B are cut or disassembled to release the connection of the band 5.5, the elastic energy due to the tightening of the band 5.5 is released instantaneously. A large impact was to be applied to rocket structure 1.2. Moreover, this impact force, combined with the impact caused by the cutting of the tinder bolts B and H, made it difficult to calculate the trajectory of the rocket and to design the satellite, which requires a precise trajectory.

Therefore, in view of the above-mentioned circumstances, the present invention provides a band for fastening a flange in a rocket structure in which the elastic energy accumulated in the band does not act on the rocket structure as an impact force when the rocket structure is separated. The purpose is to

(Means for Solving the Problems) In order to achieve the object, the present invention forms flanges at opposing joint ends of rocket structures that are coupled and separated from each other, and fastens flanges to the outer peripheries of both flanges. At the same time, an engaging member provided with an engaging groove that engages both flanges is provided at a plurality of locations on the band, and both flanges are fastened and fixed by the band and the engaging member. In addition, in the flange fastening band for a rocket structure in which the rocket structure is separated by separating the engagement member from the flange, the distance from the axis of the rocket structure to the engagement member is changed. The present invention is characterized in that the band is provided with a telescoping member that moves the engaging member in a direction away from the flanges, so that the tightening force by the band can be reduced.

(Function) In such a structure, when the rocket structures are coupled, the rocket structures are fastened by firmly tightening the band with the flanges meshing with the engagement grooves of the engagement member.

In addition, when separating the rocket structures, the elastic energy accumulated in the bands is released when the rocket structures are separated by extending the elastic member and reducing the tightening force by the bands before separation. .

(Example) An example of the flange fastening band in the rocket structure of the present invention will be described based on the drawings.

(First Embodiment) FIG. 1 is a plan view showing a state in which the flange fastening band of the present invention is fastened to a flange, and FIG. 2 is an enlarged sectional view taken along the line ■-■ in FIG. 1.

In the figure, rocket structures 10.1 connected to each other
1 has a flange 12.13 formed at each joint end of the rocket structure: Lo, 11, and the flange 12.13
are fastened via a flange fastening band 20 (hereinafter referred to as a band at the end).

The band 20 includes a plurality of arcuate pieces 21, 21 (expandable members) made of metal with a high coefficient of thermal expansion, and the arcuate pieces 21, 21 (expandable members).
．． It is composed of a plurality of engaging members 22, 22, . . . provided on the inner surfaces 21a, 21B of 21.

Both ends 21b, 21b, . . . of the arcuate pieces 21.21 are connected and fixed via nozzle bolts 21c, 21c.

Further, on the outer surface 21d of the arcuate piece 21, a plurality of electric heaters 23, 23, . . . are arranged at appropriate intervals.

The engagement member 22 is formed with an engagement groove 24 in the longitudinal direction of the engagement member 22, into which the flange 12.13 is engaged.

Reference numeral 25 denotes an extrusion device that assists in separating the rocket structures 10.11 when the rocket structures 10.11 are uncoupled.

The extrusion device 25 pushes the bottle 2 through a solenoid or cylinder (not shown) when the rocket structure 10.11 is separated.
5a is displaced upwards. In addition, this extrusion device 25
are arranged at several appropriate locations on the rocket structure 11 located below.

In the above configuration, the flange fastening band 2 of the present invention
0 is used to connect the rocket structure 10.11, the flange 12 formed on the rocket structure 10.11
．． 13 and the engagement groove 24 of the engagement member 22 are engaged.

In this state, both ends 21b of the arcuate piece 21.21.

21b... through fixing members 21c, 21c, the rocket structure 10.11 is fastened.

Before separating the rocket structure 10.11, the arcuate piece 21 is heated via electric heaters 23, 23...
．． Inflate 21.

As a result, the connecting length of the arcuate pieces 21.21 increases, and the distance R (radius) from the axis P of the rocket structure 10.11 to the engagement member 22 increases.

Due to this distance R becoming longer, both plungers 12.1
3, the engagement member 22 separates from the band 20, and the large elastic energy accumulated in the band 20 is released.

In this state, the elastic energy of the band 20 is transferred to the rocket structure 10 by detonating the crater bolts 21c and 21c and separating the band 200 arc-shaped pieces 21 and 21.
．． The separation of the rocket structures 10.11 takes place without any impact forces acting on the rocket structure 10.11.

(Second Embodiment) FIG. 3 shows a second embodiment of the present invention, and shows a plan view of the main parts of a flange fastening band.

The flange fastening band 30 illustrated in this example is
Opposite ends of the plurality of arcuate pieces 31.31 are connected via an actuator 32 (expandable member), and the engagement member 33 is provided at an appropriate location on the inner surface 31a of the arcuate piece 31. ing.

In the flange fastening band 30 configured in this way, the circumference of the band 30 can be expanded and contracted simply by adjusting the expansion and contraction of the actuator 32 after connection, and the distance R from the axis P to the engagement member 33 can be varied. The elastic energy stored in 30 is released.

(Third Embodiment) FIG. 4 shows a third embodiment of the present invention, and shows a plan view of the main parts of a flange fastening band.

The flange fastening band 40 illustrated in this example is
The arc-shaped pieces 41, 41... are connected via piezoelectric elements 42 and 42 (expandable members), and the engagement members 43 are provided at appropriate locations on the inner surface 41a of the arc-shaped pieces 41. ing.

In the flange fastening band 40 configured in this way, the circumference of the band 40 expands and contracts as the piezoelectric element 42 expands and contracts, and the distance R from the axis P to the engagement member 43 changes.
The elastic energy stored at 0 is released.

(Fourth Embodiment) FIG. 5 shows a fourth embodiment of the present invention, and shows a plan view of the main parts of a flange fastening band.

The flange fastening band 5o illustrated in this example is
It consists of an arcuate piece 51 and an engaging member 53 provided at an appropriate location on the inner surface 51a of the arcuate piece 51 via a piezoelectric element 52 (expandable member).

In the flange fastening band 50 configured in this manner, the distance R from the axis P to the engagement member 53 changes as the piezoelectric element 52 expands and contracts, and the elastic energy accumulated in the band 50 is released.

(Fifth Embodiment) FIG. 6 shows a fifth embodiment of the present invention, and shows a plan view of the main parts of a flange fastening band.

The flange fastening band 60 illustrated in this example is
It consists of an arcuate piece 61 and an engaging member 63 provided at an appropriate location on the inner surface 61a of the arcuate piece 61 via an actuator 62 (expandable member).

In the flange fastening band 6° configured in this way, the distance R from the axis P to the engagement member 63 changes as the actuator 62 expands and contracts, and the elastic energy accumulated in the band 60 is released. Ru.

(Effects of the Invention) As explained above, in the flange fastening band for a rocket structure of the present invention, the distance from the axis of the rocket structure to the engagement member is changed, and the engagement member is attached to both sides. By providing the band with an expandable member that moves in the direction away from the flange and reducing the tightening force by the band, when the rocket structure is separated,
The elastic energy stored in the band does not act on the rocket structure as an impact force.

[Brief explanation of drawings]

The drawings show an embodiment of the flange fastening band in the rocket structure according to the present invention, and FIG. 1 is a plan view showing the state in which the flange fastening band of the present invention is fastened to the flange.
2 is an enlarged sectional view taken along the line ■-■ in FIG. FIG. 5 is a plan view of the main part of the flange fastening band showing the fourth embodiment of the present invention, and FIG. 6 is a plan view of the main part of the flange fastening band showing the fourth embodiment of the present invention. A plan view of the main part of a flange fastening band showing an example, FIGS. 7 to 9 show a flange fastening band in a conventional rocket structure, and FIG. 7 shows a conventional flange fastening band fastened to a flange. A plan view showing the state, FIG. 8 is an enlarged sectional view taken along the line ■--■ in FIG. 7, and FIG. 9 is a view seen from the direction of arrow A in FIG. 8. 10.11... Rocket structure 12.13... Flange 20... Flange fastening band 21... Expandable member 22... Engagement member 24... Engagement groove P... Axis line R ···distance

Claims (1)

[Scope of Claims] Flanges are formed at opposing joint ends of the rocket structures to be joined and separated from each other, and a band for fastening the flanges is disposed around the outer periphery of both flanges, and a band for fastening the flanges is disposed on the outer periphery of both flanges. By providing engaging members provided with matching grooves at a plurality of locations on the band, fastening and fixing both flanges to the band by the engaging member, and separating the engaging member from the flange. In the flange fastening band for a rocket structure in which the rocket structures are separated, the distance from the axis of the rocket structure to the engagement member is changed to separate the engagement member from both the flanges. 1. A band for fastening a flange in a rocket structure, characterized in that the band is provided with an expandable member that moves in the direction so as to be able to reduce the tightening force exerted by the band.