JPH0310998A - Satellite separation device - Google Patents

Abstract

PURPOSE:To prevent the occurrence of an attitude control error during a satel lite separation operation by providing a latch arm for constraining a hook body with the seat surface of the arm and the hook body engaged with each other, is provided while one end of the latch arm pressing and fixing a satellite to a rocket, and so constituting the hook body as to be pulled toward the rocket with a cable. CONSTITUTION:In the constitution wherein a satellite 01 and a satellite separa tion part body 02 are connected to each other with coupling bolts and separate nuts respectively at four positions equally divided circumferentially, and each latch device 1 is provided at the external surface of the connected part, the latch device 1 is so made that the hook 3 thereof is pulled as fastened to the side of the separation part body 02. Namely, a bracket 4 is secured to the external surface of the separation part body 02 just below the separation plane A of the satellite 01 and the separation part body 02. A latch arm 2 and the hook 5 are respectively fitted to the bracket 4 pivotally with pins 5 and 6, thereby energizing one end of the arm 2 to be separated from the satellite 01 with a spring 8, and the hook 3 to be released from engagement with the latch arm 2 via a spring 9.

Description

[Detailed Description of the Invention] [Field of Industrial Application] The present invention prevents attitude errors that occur in a satellite when the rocket is separated from the satellite using a point connection method using a coupling bolt/separation nut in an artificial satellite rocket immediately after launch. related to satellite separation equipment.

[Conventional technology]

For artificial satellites (hereinafter referred to as satellites) that are required to follow precise orbits, when the satellite and rocket are separated after the initial rocket flight, it is required that no attitude error (including rate) is given to the satellite side. be done.

Conventionally, rockets and satellites have been connected using a combination bolt/separation nut system, and when they are separated, the pyrotechnics in the separation device are automatically ignited.

[Problem to be solved by the invention]

The conventional satellite separation device described above had the following problems to be solved. That is, when the satellite and rocket were separated, attitude errors were unavoidable, and the causes are thought to be mainly due to the following three points.

(1) The initial attitude rate (limit cycle) fluctuates.

(2) Strongly affected by the operating impulse of the pyrotechnics of the separation device.

(3) Affected by variations due to delays in the operation of separation devices at multiple locations.

[Means to solve the problem]

The present invention provides a means for solving the above-mentioned problems, and includes a bracket attached to the outer periphery of the rocket near the separation surface between the satellite and the rocket of an artificial satellite rocket, and a pin shaft that rotates in a seesaw shape on the bracket, which is almost perpendicular to the axis of the rocket. The cable is pivotably supported, and has a seating surface that is substantially perpendicular to the machine axis on the outside when viewed from the machine axis at the end near the separation surface, and has an engaging portion of the cable on the outside when viewed from the machine axis at the other end. and a hook body rotatably pivoted to the bracket at a position closer to the separation surface than the hook body with a pin axis substantially parallel to the pin axis, and the side of the hook body engages with the seat surface of the hook body. A latch arm that has a seat surface that can be fitted together and whose other end is bent toward the satellite to fix the satellite while it is in contact with the rocket, and a spring that always acts in a direction to keep the other end of the latch arm away from the satellite. , a spring that acts in a direction that always releases the hook from engagement with the latch arm, and a spring that engages the cable locking portion of the hook to attract it toward the rocket, and the attracting force can be arbitrarily released by another means. An object of the present invention is to provide a satellite separation device characterized by comprising a cable installed in a satellite.

[Effect]

Since the present invention is configured as described above, it has the following effects. That is, while the latch arm presses the satellite against the rocket with its bent other end and fixes it, the bearing surface of the hook body engages with the bearing surface of the hook body and is restrained. Since the cable anchoring part on the opposite side is pulled to the rocket side by a cable, the satellite as a whole remains fixed to the rocket.

Under this condition, even if the conventional coupling bolt/separation nut operates in isolation, the satellite will not have an attitude error.

When the cable is cut and released by, for example, an automatic cutting device after the separation operation of the coupling bolt/separation nut is completed, the hook body is rotated by the spring and releases the engagement with the latch arm, and the latch arm is released by the spring. The satellite rotates to release the satellite from the rocket.

In this way, the satellite is separated from the rocket without causing any attitude errors.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 to 3.

Figure 1 shows the satellite 01 and the satellite separation unit body 0 on the rocket side.
This is a diagram of the vicinity of the separation part (which is also the contact part at the same time) with 2 (
A) is a plan view thereof, and (c) is a side view thereof.

Coupling bolts/separation nuts 03 are arranged at four positions on each quadrant of the circumference to connect the satellite O1 and the satellite separation part main body 02, and latch devices 1 are arranged on the outer periphery of each of the bolts/separation nuts 03. The cable 10 attracts the hook 3 of the launch device l, which will be described later, to the satellite separation device body 02 side in a secure manner. That is, the satellite separation device of this embodiment consists of a latch device 1 and a cable 10, and a cable cutter of another means (not shown) is connected to the cable 10.
It is attached to the satellite separation unit main body 02 in an optimal configuration so as to disconnect 0 at any time.

FIG. 2 is a detailed view of the latch device 1, in which (a) is a plan view thereof and (a) is a side view thereof. Satellite O1 in both figures
and the separation plane A between the satellite separation unit main body 02 which is the rocket side.
A bracket 4 is screwed onto the outer periphery of the satellite separation unit main body 02 directly below the satellite separation unit main body 02, and a pin bolt 6 passes through the bracket 4 almost perpendicularly to the axis of the satellite separation unit main body 02. A hook 3 is pivotally supported so as to be rotatable. The hook 3 has a hook engagement floor 3a, which is a seating surface substantially perpendicular to the machine axis, on the outside of the end near the separation surface A, that is, on the outside of the side far from the machine axis of the guard 1 separation part main body 02. It is configured to engage with a latch engagement floor 2a of a latch arm 2, which will be described later.

The other end of the hook 3 is connected to the above cable 1 on the outside when viewed from the machine axis.
It has a cable receiver 3b which is a recess for locking the cable 10, so that it does not slip when the cable 10 is hooked. A latch arm 2 rotatably supported on the bracket 4 by a pin bolt 5 substantially parallel to the pin bolt 6 is provided at a position closer to the separation surface A than the hook 3; The side has a launch engaging floor 2a that can be engaged with the hook engaging floor 3a of the hook 3, and the
Until the cable 1 and the satellite separation unit main body 02 are separated, strictly speaking, until the cable 10 is cut, the cable 10 is engaged with the hook engagement floor 3a of the hook 3 as shown in FIG. 2, etc.). The other end of the latch arm 2 is bent toward the satellite 01 side, and holds the satellite 01 almost parallel to the axis through an adjustment bolt 2b provided at its tip, and holds the satellite 01 almost parallel to the axis of the satellite, which is the rocket side of the satellite separation unit main body 0.
It is fixed in contact with 2. As shown in the figure, one end of a torsion spring 8 with a pin bolt 5 as an axis is hooked to the latch arm 2, and the other end is hooked to a bracket 4, so that the latch arm 2 is rotated in the direction of arrow T1, that is, the adjustment bolt It works to always rotate the end where 2b is provided in the direction to move away from the satellite 01. Further, one end of a torsion spring 9 with a pin bolt 6 as its axis is hooked to the hook 3, and the other end is hooked to a bracket 4.
is acting in the direction of arrow TtO, that is, in the direction of always releasing the hook engaging floor 3a from the latch engaging floor 2a of the latch arm 2. The function of this torsion hook 9 is hook 3
is restrained by the tensile force of the cable 10 hooked on the cable holder 3b.

With the above configuration, the hook 3 restrains and binds the rotation of the latch arm 20, and the latch arm 2 restrains the separation of the satellite 01 and the satellite separation unit main body 02 via the adjustment bolt 2b. As shown in FIG. 1, the latch device 1 configured as described above is connected to the satellite O1 at four decoy stations on the circumference of the satellite separation unit main body 02 and the satellite separation unit main body 0 on the rocket side using one cable 10.
Even if the coupling bolt/separation nut 03 is actuated, the satellite 01 and the satellite separation part main body 02 remain fixed to each other and will not separate unless the cable 10 is cut as described later.

In addition, when fixing the satellite O1 with the launch device 1, raise the launch arm 2 located at the position shown by the two-dot chain line in FIG. 2(b) to the position shown by the solid line in the figure against the torque of the torsion spring 8, The hook 3, which is also located at the position indicated by the two-dot chain line, is rotated counterclockwise against the torque of the torsion spring 9 to engage the hook engagement base 3a with the latch engagement base 2a, and the cable 1
Constrain with 0. When rotating the hook 3 counterclockwise to engage the launch engagement floor 2a, a stopper pin 7 is attached to the bracket 4 so that the hook engagement floor 3a does not overlap the latch engagement floor 2a more than a certain range. is provided with hook 3
The extra counterclockwise rotation of the is now suppressed.

After installing the cable 10, remove the adjustment bolt 2b.
is turned to adjust the restraining force of the latch arm 2 against the satellite O1 so that the four latch devices 1 equally restrain the satellite O1.

Next, the operation of the above embodiment will be explained.

When the fuel of the rocket launched together with the satellite 11 is exhausted, the spent rocket is separated from the satellite 01 together with the satellite separation unit main body 02. Therefore, first, a pyrotechnic device (not shown) of the coupling bolt/separation nut 03 is activated to release the coupling of the coupling bolt. After all the connecting bolts of the four decoy stations are released, a cable cutter (not shown) is operated to cut the cable IO. Then 4 launch devices 1
At the same time, the hook 3 is released from its restraint and rotated by the torsion spring 9 to the position shown by the two-dot chain line in FIG.
The engaging dust 3a is removed from the latch engaging floor 2a of the latch arm 2. Then, the launch arm 2 is rotated by the torque of the torsion spring 8 to the position indicated by the two-dot chain line in the figure.
1 are all released from restraint. Next, the satellite separation unit main body 02
The satellite 0 was quietly released by retrothrust along with the rocket.
It separates from 1. .

In order to further clarify the structure and function of the latch device 1, FIG. 3 is a view seen from a different direction from FIG. bb arrow sectional view of a),
(C) is a sectional view taken along the line c-c in (a).

Therefore, (b) is shown with the left and right opposite to that of FIG. 2 0)). In FIG. 3(b), the hunting latch arm 2 and the hook 3 are engaged with each other, that is, the satellite 01
The position indicated by the two-dot chain line indicates a state in which the satellite 01 and the satellite separation unit main body 02 are fixed, and the position indicated by the two-dot chain line indicates a state in which the satellite 01 and the satellite separation unit main body 02 are separated. , l indicates the direction in which the latch arm 2 rotates upon release, and arrow T2' similarly indicates the direction in which the hook 3 rotates.

The processes from the operation of the coupling bolt/separation nut 03 to the operation of the separation device of this embodiment are all performed in sequence in a preset order. Therefore, if all connecting bolts/separating nuts are not fully activated due to slow deflagration speeds of the pyrotechnics, for example, the cable 10
It is impossible for the

As described above, according to this embodiment, the operation of the coupling bolt/separation nut 03 immediately connects the satellite 01 and the satellite separation part main body 0.
After the operations of those four units are completed, the latch device l releases the satellite 01 at the four points by cutting the cable 10, instead of separating the satellites 01 and 2, which affects the attitude of the satellite 01 when it is released and separated. Separation is achieved very naturally without any non-uniform force, vibration, vibration, etc. Therefore, it is possible to obtain an ideal satellite separation device that does not cause attitude errors or unnecessary rolling of the satellite 01 during separation.

In the above embodiment, a cable cutter (not shown) was used to release the cable 10, but a cable cutter (not shown) was used in all of the plurality of latch devices l to move the hook 3 from the engagement position to the release position (the position indicated by the two-dot chain line). If it is not possible to apply the stroke, the cable 11 may be tightened by appropriate means, or by other suitable means, instead of by cutting. Further, the use of the launch device 1 is not limited to four locations.

(Effects of the Invention) Since the present invention is configured as described above, it has the following effects. Namely, the attitude error (disturbance) due to the operation delay of the separation device and the impulse imbalance that occurs when the satellite and rocket are separated is reduced. In addition, even if a disturbance from the satellite acts on the latch arm while the satellite is being held, no rotational force is applied to the hook body, so no extra tension is applied to the cable. Since it has an irreversible structure, there is no concern that the reliability of the device will be impaired due to external disturbances.

[Brief explanation of drawings]

FIG. 1 is an overall view of an embodiment of the present invention, (a) is a plan view thereof, (b) is a bottom view of (a) (i.e., a side view of the embodiment), and FIG. 2 is a diagram of the above embodiment. A detailed diagram of the launch device 1 of (
a) is a plan view thereof, ra) is a side view of (a), FIG. 3 is a view of the latch device 1 of FIG. 2 seen from another direction, and (a) is a view in the direction of the ■ arrow in FIG. (a) is a sectional view taken along line bb in (a), (
C) is a cross-sectional view taken along line c-c in (a). 1...-launch device, 2-...-latch arm,
2a--Latch engagement pressure, 2b--Adjustment bolt,
3.-hook, 3a-.~hook engagement pressure,
3b-cable receiver, 4--bracket, 5.
6...pin bolt, 7-sudotsupa pin, 8, 9-)
--Shishin spring, lO-cable.

Claims (1)

[Claims] A bracket is attached to the outer periphery of the rocket near the separation surface between the satellite and the rocket of the artificial satellite rocket, and a bracket is pivoted to the same bracket so as to be rotatable in a seesaw manner with a pin shaft that is almost perpendicular to the rocket's axis and is close to the separation surface. A hook body having a seating surface on the outside when viewed from the machine axis at one end and having a seating surface substantially perpendicular to the machine axis at the other end, and a hook body having a cable engagement part on the outside when viewed from the machine axis at the other end; The bracket is rotatably supported by a pin axis substantially parallel to the pin axis at a position close to the separation surface, and the hook body side has a seat surface that can be engaged with the seat surface of the hook body, and the other end a latch arm that bends toward the satellite and fixes the satellite in contact with the rocket; a spring that always acts in a direction to keep the other end of the latch arm away from the satellite; and an engagement of the hook with the latch arm. a spring that always acts in a direction to release the hook; and a cable that engages the cable locking portion of the hook and draws it toward the rocket, and is provided so that the attracting force can be arbitrarily released by another means. A satellite separation device characterized by: