JP2737061B2 - Lock mechanism at launch applied to a small rocket microgravity experimental device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a lock mechanism at launch which is applied to a small rocket / microgravity maintenance technology experiment apparatus.

[Conventional technology]

Conventionally, small rocket and microgravity maintenance technology experiment equipment
As shown in Fig. 7, it is installed in a place surrounded by the stage 30 in the center of the small rocket experimental equipment part, and is used for pool boiling experiments, bubble behavior observation experiments, bubble manipulation experiments, etc. in space (microgravity) environment. Used. As shown in FIG. 8, the vertical movement of the experimental device was caused by the air mat support 34.
The movement in the left-right direction is stopped by the left and right movement stoppers 35 of the experimental apparatus.

In FIGS. 7 and 8, 1 is an upper vibration isolator support plate, 2 is an upper vibration isolator, 3 is a cover, 4 is a support base plate, 5 is a lock mechanism at launch, 6 is a main base plate, and 27 is a main base plate. Microgravity experiment equipment, 28 is a small rocket experimental equipment section, 29 is a watertight bulkhead, and 32 is an air mat.

[Problems to be solved by the invention]

The conventional small rocket / microgravity maintenance technology experimental apparatus has the following problems to be solved.

That is, although the technical problems required for the lock mechanism at launch of the microgravity maintenance technology experimental device are as shown in the following a to e, in the conventional air mat type,
As the ambient temperature changes, the volume of the internal body changes,
There was a problem that the experimental device attached thereto responded and could not be securely locked.

I. Be able to operate the lock mechanism during long-term launch.

B. The structure must be able to withstand the design limit load and the design ultimate load.

C. A structure that can be unlocked smoothly without generating unnecessary gravitational acceleration.

D. Unnecessary gravitational acceleration is not applied after unlocking.

E. Re-locking can be performed reliably.

[Means for solving the problem]

The present invention provides, as a means for solving the above problems, a support base plate provided in a direction perpendicular to the body axis of the rocket and supporting the microgravity experiment device, and a pivotally pivotally supported by the body side of the rocket, the tip of which is provided. Almost symmetric with the above-mentioned aircraft axis,
A plurality of support levers detachably provided on the support base plate; a spring for rotating the support lever to one side; and a support surface for rotating the support lever to the other side. Two electromagnetic wedges provided on the fuselage side at a predetermined interval substantially in parallel with the above, a tension spring for connecting the respective sensitive pieces of the two electromagnetic wedges, and the support lever of the respective sensitive pieces A lock mechanism at launch which is applied to a small rocket and a microgravity experimental device, comprising a sensitive piece on the side close to the side and a drive rod for connecting the support lever to the support lever. .

[Action]

Since the present invention is configured as described above, it has the following operation.

That is, a plurality of support levers symmetrically pivotally supported on the fuselage side are symmetrically engaged and disengaged from the support base plate supporting the microgravity experiment device. Mechanically connected and fixed by Therefore, the microgravity experimental device is fixed to the fuselage. When the engagement is released, the microgravity experimental device is in a free state. The engagement between the support lever and the support base plate is performed by a spring that rotates the support lever to one side. Disengagement activates the electromagnetic wedge farther from the support lever, fixes the sensitive piece on that side, releases the electromagnetic wedge connected with the support lever and the drive rod on the opposite side, and frees the sensitive piece to respond, Since the piece is pulled by the tension spring and moves to the fixed side, the drive rod pulls the support lever and turns to the release side, leaving the support base plate in a free state.

〔Example〕

One embodiment of the present invention will be described with reference to FIGS.
The same components as those in the conventional example are denoted by the same reference numerals, and description thereof will be omitted.

FIG. 1 shows a lock mechanism (lock mechanism at launch) 5 according to the present embodiment in which a small rocket microgravity maintenance technology experimental device 10 is used.
FIG. 2 is a side view (showing a locked state at launch) of the lock mechanism 5 of the present embodiment, FIG. 2 is a plan view of FIG. 2, and FIG. Is a side view of the lock mechanism 5 when the lock is released, FIG. 5 is a side view of the lock mechanism 5 when the lock is re-locked, and FIG.
101a is a detailed view, (a) is a side view, (b) is (a)
FIG. In FIG. 1, the lock mechanism 5 is used.
Although a plurality of lock mechanisms 5 are incorporated, when a plurality of lock mechanisms 5 are referred to, the lock mechanisms 5 are again called comprehensively.

In these figures, reference numeral 100 denotes a small rocket microgravity technology experimental device (hereinafter, simply referred to as an experimental device). The experimental device 100 includes a plurality of base plate mounting bolts 33.
Thus, the main base plate 6 fixed to the stage 30 on the rocket side, the locking mechanism 5 provided on the main base plate 6, and the support base plate 4 are attached via the upper vibration isolator support plate 1, the upper vibration isolator It comprises a member 2, a cover 3 containing the experimental apparatus 100, and a horizontal vibration isolator supporting structure 7 to which a horizontal vibration isolator 8 is attached. A support lever mounting bracket 12 and a spring mounting bracket 15 are fixed to the upper portion of the main base plate 6 of the lock mechanism 5 by welding, and the support lever 9 pivotally supported by the support lever mounting bracket 12 by a shaft 13 so as to be swingable. At the front end, an experimental device support bracket 11 is attached below the support base plate 4, and the experimental device support bracket 11 having the locking portion 31 is engaged with the support lever 9 to attach the experimental device support bracket 11. It is configured to lock. One end of the tip of the support lever 9 has a spring mounting bracket at one end.
A spring 14 fixed to 15 and acting in a direction to engage the support lever 9 with the experimental device support bracket 11 is mounted. On the other side, a spring 14 is connected via a drive rod 10 to a mounting shaft 26 of a cylinder 18. ing. The cylinder 18 has a cylindrical shape having sliding grooves 36 on both circumferential surfaces in the longitudinal direction, as shown in FIGS. 2 to 5 and the like, and is fixed to the main base plate 6 via a cylinder mounting bracket 20. I have. In the sliding groove 36, mounting shafts 19 and 26 penetrating in the orthogonal direction are provided so as to be slidable in the longitudinal direction of the sliding groove 36, and the mounting shaft 19 is shown in FIGS. 5 and 6. In this way, a piston-shaped sensitive piece 19a made of soft iron or the like that is sensitive to electromagnetism is fixed, and the sensitive piece 26a is fixed to the mounting shaft 26 as shown in FIG. Mounting shaft 19 and mounting shaft 2
6 are connected by a spring 17 acting as a tension spring.As will be described later, when the electromagnetic wedges 101a and 101b forming solenoids are energized, electromagnetic force is applied to both ends of the cylinder 18, respectively. Mounting shaft 19 attracted by
When the current is cut off and the electromagnetic force is extinguished, the mounting shaft 19 and the mounting shaft 26 are brought close to each other by the spring 17 and are in a free state. However, mounting shaft 26
Since is connected to the drive rod 10 as described above, it is difficult to be completely free. Coils 16 and 23 are wound on both ends of the cylinder 18, respectively.
1b, is connected to the power supply 22 via the switches 24 and 25,
When the switches 24 and 25 are turned on and off, the coils 16 and 23 function as solenoids, and the sensitive piece 26a integral with the mounting shaft 26 and the sensitive piece 19a integral with the mounting shaft 19 are fixed by electromagnetic force, respectively. , 101b.

Next, the operation of the launch lock mechanism during the launch of a small rocket will be described with reference to FIGS.

To perform the lock at launch, the mounting shaft 19 and the mounting shaft 26 are moved to both ends of the sliding groove 36, and the switches 24 and 25 are turned on. Then, the electromagnetic wedges 101a and 101b operate, and the mounting shafts 19 and 26 are fixed to both ends of the sliding groove by the electromagnetic force.
When the mounting shafts 19 and 26 are fixed to both ends of the sliding groove 36, the lock mechanism at the time of launching is operated by the support lever 9.

Next, unlocking (at the start of microgravity) will be described with reference to FIG. When the switch 24 is turned off by remote control from the ground control room at the start of microgravity after launching the small rocket, the coil 16 communicated via the lead wire 21a does not work as a solenoid, and the electromagnetic wedge 101a on the support lever 9 side is not operated. Stops working and the spring
The support lever 9 is moved by the force of
After rotating to the 18 side and separating from the experimental device support bracket 11, the experimental device 100 is separated from the experimental device support bracket 11, becomes free, and enters an experiment in a space (microgravity) environment. The tension of the spring is determined so as to satisfy “tension of spring 17> tension of spring 14”.

Next, at the time of re-locking (at the end of microgravity), the fifth
This will be described with reference to the drawings. After the end of microgravity, when the switch 25 is turned off by remote control from the ground control room, the other electromagnetic wedge 101b stops operating, and the spring 17,
The mounting shaft 19 is in a free state, and the support lever 9 rotates toward the experimental device support bracket 11 by the force of the spring 14 and is locked by the experimental device support bracket 11. At this time, the switch is turned on by remote control from the ground control room.
When 24 is turned on, the electromagnetic wedge 101a operates via the lead wire 21a, and the mounting shaft 26 integral with the sensitive piece 26a is fixed by the electromagnetic force, and the lock is re-locked.

As described above, in the present embodiment, one set of the lock mechanism 5 has been described. However, as shown in FIG.
As shown in FIG. 2 to FIG. 5, each pair is provided symmetrically with respect to 100 in the vertical direction which is the body axis direction of the rocket. The lock mechanism 5 on the opposite side (not shown) performs a symmetrical operation with respect to the lock mechanism 5. The experimental apparatus 100 can be operated in all directions in the horizontal direction, including not only the left and right directions but also the front and rear directions in the figure. Is completely locked, unlocked, and re-locked. Also, in the vertical direction in the figure, the support lever 9 engages with the locking portion 31 of the experimental device support bracket 11 in a manner that it bites in the horizontal direction. The device 100 may eventually be fully locked and arbitrarily released in all directions of the rocket's body axis and orthogonal to the body axis.

As described above, according to the present embodiment, the experimental apparatus 100 can be completely locked and unlocked with respect to the rocket, and the locking and unlocking operations are performed electrically, but the direct fixing is performed by the support lever 9. And experimental equipment support bracket 11
Since the locking portion 31 is mechanically operated, there is an advantage that it can withstand a large load and can be used for a long time as long as the capacity of the power supply 22 permits. Further, since the work of locking and unlocking is performed only by the operation of the inner system of the lock mechanism 5, there is an advantage that unnecessary gravitational acceleration is not applied to the experimental apparatus 100.

〔The invention's effect〕

Since the present invention is configured as described above, the following (1)
To (4).

(1) The experimental apparatus can be securely fixed for a long time by the lock mechanism at launch.

(2) The lock mechanism at launch can be structured to withstand the required design load.

(3) Unlocking and re-locking can be performed without applying unnecessary gravity acceleration to the experimental device.

(4) Even after the lock is released, a structure can be provided in which unnecessary gravitational acceleration is not applied.

[Brief description of the drawings]

FIG. 1 is a perspective view showing a state in which a small rocket / microgravity maintenance technology experiment apparatus 100 is locked by a lock mechanism 5 according to an embodiment of the present invention, and FIG. 2 is a side view of the lock mechanism 5 of the above embodiment. FIG. 3 is a plan view of FIG. 2, FIG. 4 is a side view of the lock mechanism 5 of the above embodiment at the time of unlocking, and FIG. 5 is a re-lock of the lock mechanism 5 of the above embodiment. FIG. 6 is an electromagnetic wedge 101b of the lock mechanism 5.
(A) is a side view thereof, and (b) is a b of (a).
FIG. 7 is a side view schematically showing a state in which the conventional small rocket / microgravity maintenance technology experimental device is mounted in the rocket, and FIG. 8 is a small rocket / microgravity maintenance technology. It is a longitudinal cross-sectional view of the conventional air mat support etc. which support a technical experiment device in a rocket. 1. Upper vibration isolator support plate (with upper vibration isolator attached),
2 ... upper vibration isolator, 3 ... cover, 4 ... support base plate, 5 ... lock mechanism (at launch), 6 ... main base plate, 7 ... horizontal vibration isolator support structure (horizontal vibration isolator) 8) Horizontal vibration isolator, 9 Support lever, 10 Driving rod, 11 Experimental support bracket, 12 Support lever mounting bracket,
13… Shaft, 14… Spring, 15… Spring mounting bracket, 16… Coil, 17… Spring, 18… Cylinder, 19… Mounting shaft, 19a… Sensitive piece, 20… Cylinder mounting bracket , 21a, 21b ……
Lead wire, 22… Power supply, 23… Coil, 24,25… Switch, 26 …… Mounting shaft, 26a …… Sensing piece, 27 …… Microgravity test equipment, 31 …… Locking part, 33 …… Mounting bolt, 36 ... sliding groove, 101a, 101b ... electromagnetic wedge.

Claims (1)

(57) [Claims] 1. A support base plate provided in a direction orthogonal to the body axis of a rocket and supporting a microgravity experiment device, and pivotally supported by the body of the rocket so as to be rotatable, and its tip is substantially symmetric with respect to the body axis. And a plurality of support levers detachably provided on the support base plate, a spring for rotating the support lever to one side, and a rotation surface on the side for rotating the support lever to the other side. Two electromagnetic wedges provided on the fuselage side at a predetermined interval substantially parallel to the support base plate, a tension spring for connecting the respective sensitive pieces of the two electromagnetic wedges, and the support of the sensitive pieces A launch lock mechanism applied to a small rocket / microgravity experimental device, comprising: a sensitive piece on a side close to a lever; and a drive rod connecting the support lever.