JPH05310196A - Vibration control device of spacecraft onboard - Google Patents

Abstract

PURPOSE:To surely prevent resonance of onboard equipment by providing a weight supported by a buffer means which vibrates at the same frequency as and in opposite phase to the resonance frequency of the onboard equipment and a guide rail for guiding the weight in the direction of vibration, and providing a bearing means between the guide rail and the weight. CONSTITUTION:In a vibration control device for preventing resonance of a spacecraft 1 and onboard equipment 3, a weight 5 supported on a coil spring 4 is guided in the direction of resonance of the onboard equipment 3 by a direct driven rolling bearing 6 and a guide rail 7. The mathematical model of the vibration system comprises a mass m1 corresponding to the onboard equipment 3, a spring constant K1 of the equipment structure system, the mass m2 of the vibration control device and a spring constant K2 of the vibration control device structure system. When the mass m1 is acted upon by an excitation of PCosomegat, the mass m2 of the weight is set such that the characteristic frequency omega2= K21/2/m2 of the m2K2 system equals the excitation frequency omegaand then the steady displacement X1, X2 of m1, m2 becomes X1=0 and X2=-P/K2 and the exciting force P balances the spring forces X2, K2, whereby resonance of the onboard equipment 3 can be prevented.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a vibration isolator for a space environment experimental equipment mainly mounted on a spacecraft.

[0002]

2. Description of the Related Art Conventional anti-vibration devices for spacecraft-equipped devices mainly use anti-vibration rubber, and by attaching a rubber-like substance to the resonance part, the vibration energy of the device is converted into stress and strain energy of the rubber. However, a method of absorbing this by internal friction of rubber has been widely adopted.

In recent years, in the field of space development, space environment utilization experiments using weightless high vacuum environment in outer space have been widely carried out. Experimental equipment for this purpose must prevent disturbance of the zero-gravity environment due to movement of humans in spacecraft or vibration of equipment such as pumps, and the development of highly reliable anti-vibration equipment was desired. ..

[0004]

The conventional vibration isolator of this type has a drawback that it is heavy and the effect of suppressing resonance is not so great. In addition, since the anti-vibration effect of rubber is subtly changed depending on the parameters such as the shape of the equipment and the thickness of attachment, the vibration-proof design should be performed by attaching the rubber while conducting the vibration test and confirming the damping effect. Need to go,
There were many trial and error suitable factors, and there was a problem that work efficiency was poor.

[0005]

A vibration isolator for equipment mounted on a spacecraft according to the present invention comprises a weight supported by a buffering means that vibrates at the same frequency as the resonance frequency of the equipment on board and in an opposite phase, and the weight. A guide rail for guiding in the vibration direction of the mounted device and a bearing means provided between the guide rail and the weight are provided.

[0006]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Next, the present invention will be described with reference to the drawings. 1A and 1B show an embodiment of the present invention, FIG. 1A is a front view showing the configuration, and FIG. 1B is an explanatory view using a numerical model.

In FIG. 1 (a), an onboard device 3 is mounted on a spacecraft 1 via a mounting bracket 2, and in order to prevent resonance of the onboard device 3 due to vibration of the spacecraft 1, a vibration isolation device is provided. Is mounted on top. In this vibration isolator, the weight 5 supported by the coil spring 4 is guided by the linear motion rolling bearing 6 and the guide rail 7 in the resonance direction of the mounted device 3.

The mathematical model of this vibration system is, as shown in FIG. 1 (b), a mass m1 corresponding to the mounted device 3, a spring constant k ₁ of the device structure system, a mass m ₂ of the vibration isolator, and a vibration isolator structure system. The spring constant k ₂ including the coil spring 4 of FIG. When the excitation of PCosωt due to the vibration of the spacecraft ₁ acts on the mass m ₁ , the mass m _{2 of the} weight 5 is changed to m ₂ · k ₂
If the natural frequency ω ₂ = √k ₂ / m _{2 of the system} is set to be equal to the excitation vibration ω, the stationary displacements X ₁ and X of m ₁ and m ₂ are set.
₂ becomes X ₁ = 0, X ₂ = -P / k ₂ , and in the m ₁ · k ₁ system, the excitation force P and the spring force X ₂ k ₂ are balanced, and the resonance of the mounted device 3 is realized. Can be prevented.

In the present embodiment, the resonance of the onboard equipment 3 due to the vibration from the spacecraft 1 is assumed, but the present invention can be applied to the case where the onboard equipment 3 itself serves as a vibration source. Within the range.

[0010]

As described above, the anti-vibration device for equipment mounted on a spacecraft of the present invention can not only reliably prevent the resonance of the on-board equipment, but also has a clear anti-vibration theory, which facilitates design work. There is an advantage.

[Brief description of drawings]

FIG. 1 shows an embodiment of the present invention, (a) is a front view showing the configuration, and (b) is an explanatory view using a mathematical model.

[Explanation of symbols]

 1 Spacecraft 2 Mounting bracket 3 Onboard equipment 4 Coil spring 5 Weight 6 Linear motion rolling bearing 7 Guide rail

Claims (3)

[Claims] 1. A weight supported by a buffer means that vibrates at the same frequency as the resonance frequency of the mounted device and in an opposite phase, a guide rail that guides the weight in the vibration direction of the mounted device, the guide rail, and the guide rail. A vibration isolator for a spacecraft-equipped device, comprising: a bearing means provided between weights. 2. The vibration isolator for a spacecraft-equipped device according to claim 1, wherein the buffering means is a coil spring. 3. The vibration isolator for a spacecraft-equipped device according to claim 1, wherein the bearing means is a linear motion rolling bearing.