JPS6364897A - Dynamic balancing regulator for space missile - Google Patents

Abstract

(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a dynamic balance adjustment device for a spacecraft, such as an artificial satellite, that adjusts the dynamic balance of the spacecraft during flight.

[Conventional technology]

FIG. 2 shows a conventional dynamic balance adjustment device. This conventional dynamic balance adjustment device has a fixed shaft 10 and a fixed plate 11 fixed to the satellite main body, and a fixed plate 11 arranged parallel to the fixed shaft 10. A fixed screw 12, a dynamic balance adjusting weight 15 guided by the fixed shaft 10, a rotating screw 14 rotatably held by the dynamic balancing adjusting weight 15 and screwed into the fixing screw 12, and a rotating screw. 14 is rotated through a gear or the like to adjust the dynamic balance adjustment weight 15.
It is composed of an electromagnetic motor 13 provided at

In this configuration, the rotating screw 14 is rotated by the motor 13, and the adjusting weight 15 is moved to a predetermined position on the fixing screw 12, thereby adjusting the dynamic balance of the artificial satellite in flight.

[Problem that the invention seeks to solve]

The above-described conventional dynamic balance adjustment device for a spacecraft uses a motor, so it has the disadvantage of being large and heavy.

Furthermore, since an electromagnetic motor is used, it has the disadvantage that it must be kept away from observation equipment for measuring magnetic fields, which dislikes the generation of electric fields, which restricts the placement of equipment within space vehicles such as artificial satellites.

There are also problems with the reliability and durability of the motor used in the environment during satellite launch and in the environment of outer space.

[Means for solving problems]

The spacecraft circumferential motion adjustment device of the present invention includes a fixed shaft fixed to the main body of the spacecraft, a drive section in which the fixed shaft is inserted through a through hole, and an adjustment weight attached to the drive section. , first and second piezoelectric elements attached to the fixed shaft, third and fourth piezoelectric elements attached to the drive section, and the first and second piezoelectric elements or the third and fourth piezoelectric elements. The fourth piezoelectric element is excited or the first piezoelectric element is excited.
Either the fourth piezoelectric element is excited to generate an elastic wave that becomes a traveling wave on the surface of the fixed shaft or the inner surface of the through hole, or the elastic wave is generated as a traveling wave on the surface of the fixed shaft or the inner surface of the through hole. and a high frequency power source that generates an elastic wave as a traveling wave to move the adjustment weight along the fixed axis.

〔Example〕

Next, embodiments of the present invention will be described with reference to the drawings.

FIG. 1 is a sectional view of an embodiment of the present invention. In the figure, reference numeral 1 denotes a fixed shaft fixed to the satellite body, which is made of an elastic body that can be excited by a piezoelectric element. 3 is a piezoelectric element wound around one end of the fixed shaft 1; 4 is a piezoelectric element wound around the other end of the fixed shaft 1; The piezoelectric elements 3 and 4 are slightly vibrated by supplying a voltage while shifting the , and a traveling surface acoustic wave is generated on the surface of the fixed shaft 1 . 9 is a drive unit that moves the attached dynamic balance adjustment weight 2 along the fixed shaft 1;
It is made of an elastic body that can be excited by a piezoelectric element. 5 is a piezoelectric element wound around the inner diameter of one end of the drive unit 9; 6 is a piezoelectric element wound around the inner diameter of the other end of the drive unit 9; A phase-shifted voltage is supplied from the power supply 8 to cause the piezoelectric elements 5 and 6 to vibrate minutely, thereby generating a traveling surface acoustic wave on the inner diameter surface of the drive section 9 .

Next, the principle of operation of the drive section 9 will be explained. First, piezoelectric element 3
A phase-shifted high-frequency voltage is supplied from the high-frequency power source 8 to the piezoelectric elements 3 and 4 through the wire 7 to the fixed shaft 1, which excites the fixed shaft 1, and generates a traveling surface acoustic wave on the surface of the fixed shaft 1. to occur. The driving portion 9 receives a force in the opposite direction to the traveling wave due to this traveling wave. Further, a high frequency voltage with a phase shift is supplied to the piezoelectric elements 5 and 6 from a high frequency power source 8 via a wire 7 to cause the piezoelectric elements 5 and 6 to vibrate minutely, to excite the drive unit 9, and to A surface acoustic wave is generated which is a traveling wave in the opposite direction to the traveling wave of the fixed shaft 1 described above. Due to this traveling wave, the driving section 9 applies a force in the opposite direction to the traveling wave to the fixed shaft 1, but since the fixed shaft 1 is fixed to the satellite body, the driving section 9 receives a reaction force from the fixed shaft 1. Due to the resultant force of this reaction force and the force applied to the drive section 9 by the traveling wave of the fixed shaft 1 described above, the drive section 9 to which the adjustment weight 2 is attached can move on the fixed shaft 1.

In addition, when moving the drive part 9 by a small amount, the high frequency voltage supplied to the piezoelectric elements 3 and 4 is cut off, and the drive part 9 is moved only by the reaction force that the drive part 9 receives from the traveling waves generated by the piezoelectric elements 5 and 6.
move.

〔Effect of the invention〕

As explained above, the present invention does not use an electromagnetic motor in a dynamic balance adjustment device for a spacecraft, but uses a piezoelectric element to reduce size and weight, and suppress electromagnetic interference with other equipment. and reliable.

This has the effect of improving durability.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a sectional view of an embodiment of the present invention, and FIG. 2 is a sectional view of a conventional dynamic balance adjustment device for a spacecraft. 1.10...Fixed shaft, 2,15...Dynamic balance adjustment weight, 3-6...Piezoelectric element, 7...Wire, 8...High frequency power supply, 9...Drive unit , 11... fixed plate, 12...
...fixing screw, 13...motor, 14...rotating screw.

Claims (1)

[Claims] A fixed shaft fixed to the main body of the spacecraft, a drive section in which the fixed shaft is inserted into a through hole, an adjustment weight attached to the drive section, and a first adjustment weight attached to the fixed shaft.
and a second piezoelectric element, third and fourth piezoelectric elements attached to the drive section, and exciting the first and second piezoelectric elements or the third and fourth piezoelectric elements; Either the first to fourth piezoelectric elements are excited to generate an elastic wave that becomes a traveling wave on the surface of the fixed shaft or the inner surface of the through hole, or the surface of the fixed shaft or the inner surface of the through hole A dynamic balance adjustment device for a spacecraft, comprising: a high frequency power source that generates an elastic wave that becomes a traveling wave to move the adjustment weight along the fixed axis.