JP2009208605A - Satellite instrument mounting structure - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To suppress micro-disturbance generated by operation of a reaction wheel. <P>SOLUTION: This satellite instrument mounting structure having the reaction wheel 2 mounted on a satellite instrument mounting panel 1 provided to an artificial satellite includes: the satellite instrument mounting panel formed with a notch; and a retainer fixed to the satellite instrument mounting panel and retaining the reaction wheel in order to insert a part of the reaction wheel into the notch. The reaction wheel is mounted in the optional position of the retainer. A distance between the instrumental mounting panel and the position of the center of gravity of the reaction wheel can be shortened and changed. Thereby, it is possible to suppress structure disturbance and adjust to optional structure resonance. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a satellite device mounting structure in which a satellite device is mounted on a structure of an artificial satellite. More specifically, the present invention relates to a satellite device mounting structure suitable for mounting a reaction wheel for controlling the attitude of a satellite.

High orientation accuracy is required in orbit for onboard equipment such as optical observation equipment and highly directional antennas onboard satellites. In the orbit, the attitude control of the entire satellite is always performed in order to control the directivity direction of the solar battery panel and the like. Although minute vibrations are generated by performing attitude control, these minute vibrations are transmitted to these satellite-borne devices that require high pointing accuracy via the satellite structure.
The attitude control of the artificial satellite is controlled by, for example, a reaction wheel. However, this reaction wheel generates minute disturbances due to the rotation of the motor, and minute vibrations are transmitted to the onboard equipment, causing deterioration of the pointing accuracy of the onboard equipment.
2. Description of the Related Art Conventionally, a support mount technique for absorbing dynamic disturbances such as vibration generated in an orbiting satellite structure or the like has been disclosed (for example, see Patent Document 1).

JP 2000-213596 A

  In order to suppress vibration generated in the reaction wheel, measures such as reinforcing the rigidity of the device mounting structure and providing a structural disturbance suppressing device that suppresses structural disturbance can be considered. However, in the case of such a countermeasure, it is necessary to add a structural member and a structural disturbance suppressing device necessary for rigidity reinforcement, and there is a problem that the mass and cost of the entire satellite increase.

  The present invention has been made to solve such problems, and to obtain a satellite device mounting structure capable of suppressing the structural disturbance of an artificial satellite without adding a structural member and a structural disturbance suppressing device, etc. necessary for rigidity reinforcement. With the goal.

  The satellite device mounting structure of the present invention is a satellite device mounting structure in which a satellite device is mounted on a satellite device mounting panel included in an artificial satellite, and the satellite device mounting panel in which a notch is formed, and the satellite device mounting panel is fixed to the satellite device mounting panel. And a holding member for holding the satellite device so that a part of the satellite device is inserted into the notch.

  According to the satellite device mounting structure of the present invention, the structural disturbance of the artificial satellite can be suppressed without adding a structural member, a structural disturbance suppressing device, and the like necessary for rigidity reinforcement.

Embodiment 1 FIG.
FIG. 6 is a diagram illustrating an example of a wheel configuration serving as an actuator in a conventional attitude control device for an artificial satellite. In FIG. 6, reference numeral 111 denotes a momentum wheel, and 112 to 114 are reaction wheels. The function of the momentum wheel 111 is to give the artificial satellite an angular momentum in the x-axis direction, and the attitude of the artificial satellite can be kept passive to some extent by this angular momentum. The reaction wheel 112 is held with its rotational axis in the xy plane and tilted by θ1 from the x axis. The reaction wheel 112 is held with its rotation axis inclined at θ1 with respect to the x-axis and θ2 with respect to the y-axis. The reaction wheel 114 is held with its rotation axis inclined by θ1 with respect to the x axis and θ3 with respect to the y axis. These three reaction wheels 112 to 114 and the four wheels of the momentum wheel 111 constitute a redundant system to control the attitude of the artificial satellite.

  FIG. 5 is an example of a satellite device mounting structure in which the reaction wheel 112 is mounted on the device mounting panel 120. FIG. 5A is a rear perspective view of the reaction wheel 112 as viewed obliquely from the rear, and FIG. 5B is a rear view of the reaction wheel 112 as viewed from the rear. The reaction wheel 112 needs to be held at a predetermined angle with respect to the upper surface of the device mounting panel 120. For this reason, conventionally, a support base 121 having an inclined portion is used, the reaction wheel 112 is fixed to the inclined portion of the support base 121, and the bottom surface of the support base 121 is fixed to the upper surface of the device mounting panel 120. However, in this case, the position of the center of gravity of the reaction wheel 112 comes to a high position having a distance (offset distance) with respect to the surface position of the device mounting panel 120, so when controlling the attitude of the satellite, that is, when the motor of the reaction wheel rotates. As a result, a larger vibration is transmitted to the on-board equipment. If the rigidity of the satellite equipment mounting structure is reinforced to suppress this vibration, the mass and cost of the entire satellite increase.

  Next, the satellite equipment mounting structure according to the present embodiment will be described with reference to the drawings. 1-3 is a figure which shows the satellite equipment mounting structure based on Embodiment 1 of this invention. FIG. 1 is a rear perspective view of the reaction wheel 3 when mounted in the satellite device mounting structure of the present embodiment as viewed obliquely from the rear, FIG. 2 is a cross-sectional view of the reaction wheel 3 when mounted from the side, and These are the rear views which looked at the reaction wheel 3 at the time of mounting from the back. The reaction wheel is an example of a satellite device.

1-3, the apparatus mounting panel 1 which mounts the reaction wheel 2 is provided with the notch part 3. As shown in FIG. As shown in FIG. 2, the notch 3 is a hole provided so as to penetrate the upper and lower sides of the device mounting panel 1, or may be a recess provided on the upper surface of the device mounting panel 1. . Further, the notch 3 may be provided so as to penetrate through the upper and lower sides of the device mounting panel 1 obliquely in accordance with the inclination of the device interface fitting 4 described later.
The device interface bracket 4 has a structure for sandwiching the device mounting panel 1 from above and below, and is fixed by an adhesive or by screwing so that the device mounting panel 1 is sandwiched from above and below. The device interface fitting 4 includes an inclined portion that is inclined with respect to the upper surface of the device mounting panel 1. The inclination angle of the inclined portion is set based on the use conditions of the reaction wheel. This equipment interface fitting is an example of a holding member.
The reaction wheel 2 is inserted into a notch 3 provided on the device mounting panel 1, and the reaction wheel 2 is screwed with the back surface of the reaction wheel 2 aligned with the inclined portion of the device interface fitting 4.

  FIG. 2 shows the center of gravity position 5 of the reaction wheel 2. The device mounting panel 1 is provided with a notch 3, and a part of the reaction wheel 2 is inserted into the notch 3 and held in an inclined state. Thereby, the center-of-gravity position 5 of the reaction wheel 2 can be made closer to the surface of the device mounting panel 1 than the conventional structure shown in FIG. The offset distance 6 (the distance in the height direction between the surface of the device mounting panel 1 and the center of gravity 5 of the reaction wheel 2) shown in FIG. 2 can be shortened. Thus, in this Embodiment, the gravity center position of the height direction of a reaction wheel can be brought closer to the apparatus mounting panel surface conventionally.

  FIG. 4 shows a mounting example in which three reaction wheels 2 (2a, 2b, 2c) are mounted on the device mounting panel 1. The three reaction wheels 2 are each held by a device interface fitting 4 and inserted into a notch 3 provided on the device mounting panel 1 and mounted on the device mounting panel 1 at different angles. The satellite performs attitude control with a reaction wheel.

  As described above, in the first embodiment, the notch portion 3 is provided in the device mounting panel 1 and the reaction wheel 2 mounted with an inclination angle is inserted into the notch portion 3 so that the center of gravity position of the reaction wheel is obtained. Can be brought closer to the device mounting panel 1. As a result, when controlling the attitude of the satellite, it is possible to reduce the vibration caused by rotating the motor of the reaction wheel, and to suppress the influence on the satellite-mounted equipment such as the image acquisition device.

Embodiment 2. FIG.
Next, a second embodiment will be described. In Embodiment 1, the reaction wheel is inserted into the notch 3 provided in the device mounting panel 1 to bring the center of gravity of the reaction wheel closer to the device mounting panel 1 to reduce vibration itself. However, the vibration cannot be made zero. In the second embodiment, the frequency of this vibration (structural resonance) is moved, for example, by actively moving the frequency of this structural resonance to a frequency band away from a frequency band in which structural disturbance excitation is likely to occur, thereby obtaining an image acquisition device. Try to reduce the impact on satellite equipment.

  In the present embodiment, the mounting position at which the reaction wheel 2 is mounted on the device interface fitting 4 is adjusted. Specifically, the position of the center of gravity of the reaction wheel with respect to the position of the device mounting panel 1 is changed by adjusting the height position of the reaction wheel 2 with respect to the device mounting panel 1. Thereby, the frequency of vibration (structural resonance) generated when the reaction wheel is operated can be moved outside the frequency range that affects satellite-equipped equipment such as an image acquisition device. The vibration (structural resonance) itself cannot be made zero, but the influence on the satellite equipment can be suppressed.

Embodiment 3 FIG.
Next, Embodiment 3 will be described with reference to FIG. In the present embodiment, a plurality of fixing holes 7 for fixing the reaction wheel with screws are provided in the inclined portion of the device interface fitting 4.
When mounting the reaction wheel 2, a desired fixing hole 7 is selected from the plurality of holes, and the reaction wheel 2 is mounted on the inclined portion of the equipment interface fitting 4 using the selected fixing hole 7.

  Thereby, it becomes possible to adjust the gravity center position of the reaction wheel with respect to the position of the apparatus mounting panel 1 by simple operation. Since the center of gravity of the reaction wheel can be adjusted with a simple operation, the influence of vibration (structural resonance) that occurs during the reaction wheel operation is acquired at the test stage, and the structural resonance frequency is calculated based on the result and satellite-equipped equipment such as an image acquisition device. Adjustments that are outside the frequency range that affect the frequency can be easily performed.

It is a figure which shows the satellite equipment mounting structure of Embodiment 1 which concerns on this invention, and is the back perspective view which looked at the reaction wheel at the time of mounting from diagonally backward. It is a figure which shows the satellite equipment mounting structure of Embodiment 1 which concerns on this invention, and is the cross-sectional view which looked at the reaction wheel at the time of mounting from the side. It is a figure which shows the satellite equipment mounting structure of Embodiment 1 which concerns on this invention, and is the back perspective view which looked at the reaction wheel at the time of mounting from diagonally backward. It is the example of mounting of the reaction wheel of Embodiment 1 which concerns on this invention. It is a figure which shows the conventional satellite equipment mounting structure. It is a figure which shows an example of the wheel structure in the conventional satellite attitude control apparatus.

Explanation of symbols

  1 equipment mounting panel, 2 reaction wheel, 3 notch, 4 equipment interface bracket, 5 center of gravity of reaction wheel 2, 6 offset distance, 7 fixing hole, 112 reaction wheel, 120 equipment mounting panel, 121 support base

Claims (3)

A satellite device mounting structure in which a satellite device is mounted on a satellite device mounting panel included in an artificial satellite,
A panel mounted with satellite equipment in which notches are formed;
A holding member that is fixed to the satellite device mounting panel and holds the satellite device by inserting a part of the satellite device into the notch,
A satellite device mounting structure characterized by comprising: The satellite device is a reaction wheel;
The satellite device mounting structure according to claim 1, wherein the holding member includes an inclined portion inclined by a predetermined angle with respect to a surface of the satellite device mounting panel, and the reaction wheel is held by the inclined portion. The holding member includes a plurality of fixing holes for fixing the device in the inclined portion,
The satellite device mounting structure according to claim 2, wherein the reaction wheel is screwed to the inclined portion in an adjustable manner using any one of the fixing holes.

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