JP2000289697A - Payload damping mechanism - Google Patents

Abstract

(57) [Summary] [PROBLEMS] To effectively dampen and support vibration and rocking applied to a payload. SOLUTION: This is a payload vibration damping mechanism for supporting a payload 5 accommodated in a payload launch vehicle on a payload adapter 4 side and buffering vibration applied to the payload 5, wherein the annular vibration control mechanism is provided on an upper surface of the payload adapter 4. Between the lower platform 7 and the annular upper platform 8 provided at the lower part of the payload 5,
A shock-absorbing cylinder device 10 for supporting the load of the payload 5 and preventing vibration and locking in the direction of the rocket machine axis S;
A plurality of laterally-active semi-active dampers 19 are arranged substantially horizontally in the circumferential direction for damping vibrations in a direction perpendicular to the axis S of the payload 5.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a payload damping mechanism for supporting a payload (artificial satellite) provided in a payload launch vehicle on a payload adapter side.

[0002]

2. Description of the Related Art As shown in FIG. 5, a rocket for launching a payload (artificial satellite) is a multistage rocket in which a two-stage rocket 3 is accommodated in splittable fairings 2 and 2 provided at the tip of a single-stage rocket 1. Rocket and its two-stage rocket 3
Has a configuration in which a payload 5 is provided at a distal end portion thereof via a support member called a payload adapter 4.

[0003] The multi-stage rocket first has a single-stage rocket 1
After igniting the engine and launching the entire single-stage rocket 1 to a predetermined height above the sky, the fairings 2, 2 at the tip of the single-stage rocket 1 are opened to the left and right to expose the two-stage rocket 3, and then the two-stage rocket 3 is exposed. After igniting the engine of the staged rocket 3 and separating it from the staged rocket 1, the engine of the staged rocket 3 propelled itself and reached an orbit by the combustion of the engine.
The launch of the payload 5 is achieved by separating the payload 5 mounted on the tip from the payload adapter 4 and throwing it into orbit.

[0004]

As shown in FIG. 6, the above-mentioned payload 5 has a structure in which the lower surface of a structure 6 having a separating mechanism is supported on the upper surface of a payload adapter 4. ing.

Therefore, as described above, at the time of launch, a large vibration is directly applied to the entire payload 5 in the height direction (machine direction) by the propulsive force of the first-stage rocket 1 and the second-stage rocket 3, and at the same time, The rocket itself is subjected to vibration in the radial direction (perpendicular to the machine axis) due to friction with air and the like, and as a result, rocking (rocking) R is generated in the payload 5, thereby causing equipment and the like inside the payload 5 to move. There is a problem that it may have an adverse effect.

In order to dampen the vibration of the payload 5, it is conceivable to support the payload 5 on the payload adapter 4 by some means, but the payload 5 is surrounded by fairings 2, 2 which will be separated in the future. Only the upper part of the payload 5 cannot be supported from the payload adapter 4 side, and therefore, the payload 5 has a structure in which locking R is easily generated as shown by an arrow in FIG.

[0007] Therefore, even if a means for damping the vibration of the payload 5 is taken, if the locking means causes the locking R of the payload 5 and the locking width becomes large, the payload 5 and the surrounding area are surrounded. Due to the narrow interval between the fairings 2, 2, a problem that the payload 5 contacts the fairings 2, 2 may be considered.

SUMMARY OF THE INVENTION The present invention has been made to solve such a conventional problem, and has a payload damping mechanism capable of effectively damping and supporting vibrations applied to the payload in the machine axis direction and in the direction perpendicular to the machine axis. It is intended to provide.

[0009]

SUMMARY OF THE INVENTION The present invention relates to a payload damping mechanism for supporting a payload accommodated in a payload launch vehicle on a payload adapter side and buffering vibration applied to the payload. A cushion cylinder device for supporting the load of the payload to prevent vibration and locking in the axial direction of the rocket between the annular lower platform provided at the lower portion and the annular upper platform provided at the lower portion of the payload; The present invention relates to a payload damping mechanism, comprising: a plurality of laterally-active semi-active dampers arranged substantially horizontally in a circumferential direction for buffering vibration in the direction.

In the shock absorbing cylinder device, a plurality of vertical cylinders arranged in the circumferential direction, a head side oil chamber communicates with each load receiving chamber of the vertical cylinder via an oil passage, and each piston is a piston rod. It may include the same number of series cylinders as the vertical cylinders connected in series, and semi-active dampers and buffer springs arranged between the series cylinders.

Further, the semi-active damper may be a fluid viscosity adjusting damper, a servo valve type hydraulic damper, and the lateral semi-active damper may have a lateral buffer spring.

According to the present invention, the vibration in the machine direction applied to the payload can be effectively damped by the plurality of cushion cylinder devices provided in the circumferential direction, and the transversely active semi-active damper allows the vibration in the direction perpendicular to the machine axis to be applied to the payload. Vibration can be damped, which also suppresses payload locking, thus effectively damping the payload in all directions during launch and effectively reducing the impact of the payload on internal equipment. .

[0013]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows an example of an embodiment of the present invention applied to the rocket shown in FIG. 6, in which an annular lower platform 7 provided on the upper surface of a payload adapter 4 and a lower portion of the payload 5 are provided. The payload vibration damping mechanism is arranged between the upper platform 8 and the annular upper platform 8.

The payload damping mechanism shown in FIG. 1 has a lower platform 7 and an upper platform 8 at three circumferentially equally spaced positions (regular triangular positions) between an annular lower platform 7 and an annular upper platform 8. To support the load of the payload 5 to buffer vibrations in the direction of the rocket machine axis S, and
And a shock-absorbing cylinder device 10 for preventing locking of the cylinder.

The cushioning cylinder device 10 is shown in FIGS.
As shown in the figure, three vertical cylinders 11a, 11b, 11c are arranged at equal intervals in the circumferential direction, and the same number of series cylinders 12a, 12b, 12c connected to the vertical cylinders 11a, 11b, 11c are provided. ing.

The series cylinders 12a, 12b, 12c
Each piston 13 has a configuration in which the pistons 13 are connected in series by a piston rod 14 so as to be linear,
The series cylinders 12a, 12b, 12c, 12c, and 12c corresponding to the load receiving chambers 15 of the vertical cylinders 11a, 11b, 11c, respectively.
The head-side oil chamber 16 of 12c communicates via an oil passage 17.

Further, the piston 13 of the series cylinder 12a
A cushion spring 18 and a semi-active damper 9 are provided between the cylinder 13 and the series cylinder 12b. A cushion spring 18 and a semi-active damper 9 having the same resilient force are also provided between the piston 13 of the series cylinder 12b and the series cylinder 12c. Is provided.

Further, at three places at equal intervals in the circumferential direction between the lower platform 7 and the upper platform 8, the lower platform 7 and the upper platform 8 are positioned between fixed blocks 7a, 8a provided in the substantially horizontal direction. And a lateral semi-active damper 19 that buffers vibration of the payload 5 in a direction perpendicular to the axis S of the payload 5 is provided. In FIG. 19A, a semi-active damper 1 in a horizontal direction is shown.
9 are horizontal cushioning springs provided respectively.

FIG. 3 shows an example of a fluid viscosity adjusting damper 27 used as the semi-active dampers 9 and 19. The fluid viscosity adjusting damper 27 is supported inside the cylinder 20 by the piston rod 21 and the cylinder. 20
The cylinder 20 is provided with a piston 24 having an electromagnet 23 movable with an inner wall and a required gap 22. A magnetic fluid 25 in which a magnetic powder such as ferrite particles is mixed with a liquid such as oil is provided inside the cylinder 20. Is filled. In the configuration shown in FIG. 3, a current is caused to flow through the electromagnet 23 via the electric wire 26 and the piston rod 21, so that the electromagnet 23 can form a magnetic field outside including the gap 22. In the fluid viscosity adjusting damper 27 of FIG. 3, when a magnetic field is formed by the electromagnet 23, the resistance of the magnetic fluid 25 flowing through the gap 22 increases, so that the voltage supplied to the electromagnet 23 is changed to increase the strength of the magnetic field by the electromagnet 23. By controlling the displacement, the movement resistance of the piston 24 can be arbitrarily adjusted.

FIG. 4 shows a semi-active damper 9,1.
9 shows an example of a servo-valve type hydraulic damper 40 used as 9. In the servo-valve type hydraulic damper 40, a piston 30 supported by a piston rod 29 is movable inside a cylinder 28 filled with oil. Is provided in
A control valve element 36 for adjusting an opening ratio of an opening 35 of the oil passage 34 between an oil passage 32 communicating with one chamber 31 of the cylinder 28 and an oil passage 34 communicating with the other chamber 33 of the cylinder 28. Is provided. The axial movement position of the spool 37 can be adjusted by an input voltage 38 via a servo valve 39. In the servo valve type hydraulic damper 40 of FIG. 4, when the spool 37 is moved by the servo valve 39 and the opening ratio of the opening 35 of the oil passage 34 is adjusted by the adjusting valve body 36, the oil flowing between the oil passages 32 and 34. , The movement resistance of the piston 30 can be arbitrarily adjusted.

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

As shown in FIG. 6, when a large vibration in the direction of the rocket machine axis S is applied from the payload adapter 4 to the payload 5 side by the propulsive force of the rocket, the cushioning cylinder device 10 shown in FIGS. Vertical cylinder 1
1a, 11b and 11c are contracted and deformed, and each vertical cylinder 1
1a, 11b, and 11c are supplied from the load receiving chamber 15 through the oil passage 17 to each of the series cylinders 12a, 12b, 1c.
The piston 13 is moved into the head side oil chamber 16 of 2c to move the piston 13, but the series cylinders 12a, 12b, 1
The movement of the piston 13 is suppressed by the semi-active damper 9 and the buffer spring 18 provided between 2c. Thereby, the vibration in the direction of the rocket machine axis S transmitted from the lower platform 7 to the upper platform 8 is effectively buffered.

On the other hand, due to friction with the air during the propulsion of the rocket, vibrations in a direction perpendicular to the axis S act on the payload adapter 4 or the payload 5 side, and a force for locking the payload 5 is generated.

In the above, when the lower platform 7 and the upper platform 8 are relatively inclined, that is, when the locking is about to occur, the series cylinder in which the piston 13 is connected by the piston rod 14 and moves integrally. The corresponding vertical cylinders 11a, 11b, 1 are provided in the head-side oil chambers 16 of 12a, 12b, 12c.
Since each load receiving chamber 15 of FIG. 1c has a configuration communicating with the oil passage 17, the vertical cylinders 11a, 11b, 11
c cannot expand and contract simultaneously and make separate movements. For this reason, the lower platform 7 and the upper platform 8 do not tilt relatively, and locking of the payload 5 can be reliably prevented.

When vibration in the direction perpendicular to the axis S is applied to the payload adapter 4 or the payload 5 side, the vibration is effectively buffered by a plurality of laterally semi-active dampers 19 arranged substantially horizontally in the circumferential direction in FIG. .

That is, the absolute acceleration / velocity of the payload 5 is detected by an acceleration sensor, and the fluid viscosity adjusting damper 27 shown in FIG.
To adjust the strength of the magnetic field of the electromagnet 23 and the position of the control valve element 36 by the spool 37 of the servo valve type hydraulic damper 40 shown in FIG.
And the damper grade of the semi-active damper 19 in the horizontal direction is changed. Thereby, the semi-active damper 9
In addition, the response frequency of the laterally-active semi-active damper 19 changes, and the vibration of the payload 5 in the direction perpendicular to the axis S can be effectively buffered. Since the semi-active damper 19 is provided with the buffer spring 19A, the payload 5 is buffered so that it does not move significantly and is always kept at the initial origin position. Further, the vertical cylinders 11a, 11b, 11c and the series cylinders 12a, 12b, 12c constituting the cushioning cylinder device 10 are lightweight and excellent in responsiveness, and can be suitably used as a vibration damping mechanism for the payload 5. .

As described above, the weight of the payload 5 is supported by the shock-absorbing cylinder device 10 and the vibration applied to the payload 5 in the direction of the axis S of the rocket machine is effectively damped, and the locking of the payload 5 can be prevented. Further, the laterally-active semi-active damper 19 can prevent vibration applied to the payload 5 in a direction perpendicular to the axis S, thereby effectively damping the vibration of the payload 5 in all directions generated at the time of launching the rocket. Adverse effects on internal equipment can be significantly reduced. Further, it is desired that the payload vibration damping mechanism of the rocket be lightweight. In the above-described embodiment, the vibration of the payload 5 can be effectively damped by a lightweight and simple device configuration, thereby facilitating the design.

In the above embodiment, the cushion cylinder device 10 and the lateral semi-active damper 19 have been described as being arranged in a triangular form. However, the arrangement may be quadrangular or more. The active damper 19 includes various fluid viscosity adjusting dampers 27 and servo valve type hydraulic dampers 4 not shown.
Of course, 0 can be adopted, and various changes can be made without departing from the spirit of the present invention.

[0030]

According to the present invention, the vibrations in the machine direction applied to the payload can be effectively damped by the plurality of shock absorbing cylinder devices provided in the circumferential direction. The vibration in the right-angle direction can be damped, and the locking of the payload can be suppressed at the same time, thus effectively damping the vibration of the payload in all directions generated when launching the rocket, and greatly reducing the adverse effect of the payload on the internal equipment. There is an effect that can be reduced.

[Brief description of the drawings]

FIG. 1 is a perspective view illustrating an example of an embodiment of a payload damping mechanism according to the present invention.

FIG. 2 is a circuit configuration diagram showing an example of a buffer cylinder device in FIG.

FIG. 3 is a schematic sectional side view showing an example of a semi-active damper using a fluid viscosity adjusting damper.

FIG. 4 is a schematic sectional side view showing an example of a semi-active damper using a servo valve type hydraulic damper.

FIG. 5 is a schematic side view showing an example of a rocket for launching a payload.

FIG. 6 is a schematic side view showing an example of a conventional payload support section.

[Explanation of symbols]

 Reference Signs List 4 payload adapter 5 payload 7 lower platform 8 upper platform 9 semi-active damper 10 buffer cylinder device 11a, 11b, 11c vertical cylinder 12a, 12b, 12c serial cylinder 13 piston 14 piston rod 15 load receiving chamber 16 head side oil chamber 17 oil Road 18 Buffer spring 19 Semi-active damper 19A Buffer spring 27 Fluid viscosity adjusting damper 40 Servo-valve type hydraulic damper S Rocket axle

Claims (5)

[Claims] 1. A payload damping mechanism for supporting a payload housed in a payload launch vehicle on a payload adapter side and buffering vibration applied to the payload, comprising: an annular lower platform provided on an upper surface of the payload adapter; A cushioning cylinder device for supporting the load of the payload to prevent vibration and locking in the axial direction of the rocket, between the annular upper platform provided at the lower portion of the payload, and a cushioning device for cushioning vibration in the direction perpendicular to the payload axis. A payload damping mechanism comprising a plurality of semi-active dampers arranged side by side substantially horizontally in a circumferential direction. 2. A vertical cylinder in which a plurality of buffer cylinder devices are arranged in a circumferential direction, a head side oil chamber communicates with each load receiving chamber of the vertical cylinder via an oil passage, and each piston is a piston rod. The payload damping mechanism according to claim 1, further comprising: the same number of serial cylinders as the vertical cylinders connected in series, and a semi-active damper and a buffer spring disposed between the serial cylinders. 3. The payload damping mechanism according to claim 1, wherein the semi-active damper is a fluid viscosity adjusting damper. 4. The payload damping mechanism according to claim 1, wherein the semi-active damper is a servo valve type hydraulic damper. 5. The payload damping mechanism according to claim 1, wherein the horizontal semi-active damper includes a horizontal buffer spring.