JPH04362499A - Satellite fairing of rocket - Google Patents

Abstract

PURPOSE:To prevent the transmission of an outer sound such as an engine jet which is critical to a satellite loaded in a satellite fairing of a rocket, to the inside of the fairing so as to generate an excitation phenomenon. CONSTITUTION:In a main structure 1 of a satellite fairing of a rocket in which a satellite is housed, a vacuum part 10 is provided, and the transmission of a sound in the outside 3 of the fairing into the inside 4 of the fairing is prevented by this vacuum part 10.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket satellite fairing designed to prevent acoustic vibrations.

0002

[Prior art] The satellite fairing of a conventional rocket is
As shown in FIG. 3, the satellite 2 is placed inside the satellite fairing main structure 1, but when a rocket is launched, a loud sound is generated outside the rocket 3 by the engine jet. The sound excites the satellite fairing main structure 1, the satellite fairing becomes a new vibration source, the sound propagates inside the fairing 4, and this internal sound excites the onboard satellite 2. . Since this internal sound is critical to the satellite, conventionally, the following method has generally been used to reduce the internal sound.

That is, as shown in FIGS. 4 and 5, by pasting a soundproof blanket (sound absorbing material) 5 such as glass wool on the inside of the satellite fairing main structure 1, the echoes of sound inside the satellite fairing 4 can be reduced. The fairing is made smaller in order to reduce the sound inside the fairing.

[0004] As the material for the main structure of the satellite fairing, aluminum alloy, which has a high specific strength (material strength/density), is generally used in order to reduce the weight of the structure. Also,
Structural styles include semi-monocoque structure, monocoque structure (FIG. 5), and honeycomb structure using honeycomb core material 6 (FIG. 4).

Note that 7 in FIG. 4 is a honeycomb face sheet.

[0006]

SUMMARY OF THE INVENTION The conventional method using a soundproof blanket for the satellite fairing of a rocket has the following problems.

That is, this method aims to reduce internal sound by reducing the echo of sound inside the satellite fairing using a soundproof blanket, and prevents the propagation of sound from the outside of the satellite fairing to the inside. It's not a thing. For the above reasons, the sound reduction effect is small, and the fairing internal sound still has a large influence on the satellite.

The present invention aims to provide a rocket satellite fairing that can solve the above problems.

[0009]

SUMMARY OF THE INVENTION The rocket satellite fairing of the present invention provides a vacuum section within the main structure housing the satellite.

0010

[Operation] Sound is a wave that travels through a medium (gas, liquid, solid). In the present invention, by providing a vacuum section within the fairing main structure that accommodates the satellite, sound propagation from the outside to the inside of the satellite fairing is blocked. This results in
Satellite fairing internal sound is reduced.

[0011]

Embodiment A first embodiment of the present invention will be explained with reference to FIG. In this embodiment, a honeycomb structure is used as the main structure 1 of a rocket satellite fairing of the type shown in FIG.

As shown, the satellite fairing main structure 1
A plurality of air vents 8 are provided in the honeycomb core material 6 attached to the outer honeycomb facesheet 7 and the inner honeycomb facesheet 7', and the outer honeycomb facesheet 7 communicates with the fairing exterior 3. An escape port 9 was provided.

[0013] As the honeycomb core material 6, a material with excellent vibration damping properties is used. In addition, by sandwiching a vibration isolating material between the honeycomb face sheets 7, 7' and the honeycomb core material 6, the vibration is transmitted from the outer honeycomb face sheet 7 through the honeycomb core material 6 to the inner honeycomb face sheet 7'. It may also be possible to prevent solid-state sound from propagating to the ground.

In this embodiment, when the speed of the rocket increases during launch, etc., the static pressure of the air decreases due to the speed of the air flowing outside the fairing 3.
As a result, the air inside the honeycomb core material 6 is sucked out to the outside of the fairing 3 through the air outlet 8 and the air port 9, and the inside of the honeycomb core material 6 becomes a vacuum section 10.

The vacuum section 10 within the honeycomb core material 6 prevents the propagation of sound from the outside 3 of the fairing to the inside 4 of the fairing, reducing the sound inside the fairing 4. This can prevent vibration of the satellite.

A second embodiment of the present invention will be explained with reference to FIG. In this embodiment, a monocoque structure is used as the main structure 1 of the fairing for a rocket satellite of the type shown in FIG.

As shown in the figure, a corrugated plate or dimple plate 11 is installed inside the satellite fairing main structure 1 having a monocoque structure.
is attached, and a space is provided between it and the main structure 1. Further, the main structure 1 is provided with an air escape port 9 communicating with the fairing interior 3 from which air in the space is sucked out.

Furthermore, a vibration isolating material is sandwiched between the satellite fairing main structure 1 and the corrugated plate or dimple plate 11 to prevent solid-borne sound from reaching the satellite fairing main structure 1 to the corrugated plate or dimple plate 11. Make it.

In this embodiment, as in the first embodiment, air in the space between the corrugated or dimpled plate 11 and the satellite fairing main structure 1 passes through the air outlet 9 to the outside of the fairing 3. A vacuum section 10 is formed in the space. With this vacuum section 10, similarly to the first embodiment, from the outside 3 of the fairing to the inside 4 of the fairing.
This prevents sound from propagating to the fairing and prevents vibration of the satellite mounted inside the fairing 4.

[0020]

[Effects of the Invention] By providing a vacuum section within the main structure of the satellite fairing, the present invention prevents the sound outside the fairing from propagating inside, and significantly reduces the sound inside the fairing compared to the conventional structure. This can prevent vibration of the satellite mounted inside the fairing.

[Brief explanation of drawings]

1 is a detailed diagram of a first embodiment of the invention; FIG.

FIG. 2 is a detailed view of a second embodiment of the invention.

FIG. 3 is a schematic cross-sectional view of a satellite fairing of a conventional rocket.

FIG. 4 is a detailed view of a conventional honeycomb structure satellite fairing main structure.

FIG. 5 is a detailed view of a conventional monocoque satellite fairing main structure.

[Explanation of symbols]

1 Main structure of satellite fairing 2 Satellite ３　　　External fairing 4 Inside the fairing 5. Soundproof blanket 6 Honeycomb core material 7,7′ honeycomb face sheet 8 Air escape hole 9 Escape port 10 Vacuum section 11　Corrugated plate or dimple plate

Claims (1)

[Claims] 1. A satellite fairing for a rocket, characterized in that a vacuum section is provided within the main structure of the satellite fairing for accommodating a satellite.