JPH04297400A - Collision detecting method of meteoroid/debris against spacecraft - Google Patents

Abstract

PURPOSE:To provide such a collision detecting method of meteoroid/debris against a space navigator, capable of detecting a collision position of the meteoroid (meteorite)/debris (fragments) against the space navigator. CONSTITUTION:A lot of sensors 2 detecting a vibration in an airframe 1a in a matrix manner are installed in the airframe 1a of a space station 1, and an impulse wave being produced by a collision of meteoroid/debris against the airframe 1a is detected, while detected data of these sensors 2 are analyzed, through which a collision position of the meteoroid/debris and its impact strength are detected.

Description

Detailed Description of the Invention [0001] [Industrial Application Field] The present invention relates to a method for detecting collisions of meteoroids/debris (space debris) with respect to spacecraft, and relates to a method for detecting collisions of meteoroids/debris (space debris) with spacecraft such as space stations and artificial satellites. It is useful when applied to [0002] With recent space development, many artificial satellites have been launched, and the installation of future space stations is also being considered. Many of these spacecraft such as artificial satellites and space stations are manned, and sufficient safety measures must be taken for people inside these spacecraft. [0003] Problems to be Solved by the Invention [0003] Although there is still no established method for determining the collision position and degree of damage to a spacecraft due to meteoroids/debris colliding with a spacecraft at ultra-high speed, For the safety of the crew, it is necessary for spacecrafts to quickly determine the location of meteoroid/debris collisions and the extent of damage caused by the collision. SUMMARY OF THE INVENTION In view of the above-mentioned prior art, an object of the present invention is to provide a method for detecting a collision of meteoroids/debris with a spacecraft, which is capable of detecting the collision position of the meteoroid/debris with the spacecraft and the impact of the collision. shall be. [Means for Solving the Problems] The structure of the present invention that achieves the above object is as follows: [0006] Vibrations are applied to the outer peripheral surface of a spacecraft such as a space station or an artificial satellite in a line or matrix pattern. A large number of sensors are installed to detect the meteoroid/debris, and each sensor detects the vibrations that occur when the meteoroid/debris collides with the spacecraft. It is characterized by detecting the location of the collision and the strength of the impact. [Operation] According to the present invention having the above-mentioned structure, vibrations generated due to meteoroid/debris collision are detected by a large number of sensors arranged in a line or matrix. Therefore, by comprehensively determining the vibrations detected by each sensor, the location of the collision and the strength of the impact can be determined. [Embodiments] Hereinafter, embodiments of the present invention will be explained in detail based on the drawings. As shown in FIG. 1, a large number of sensors 2 are attached to the outer peripheral surface of the body 1a of the space station 1, arranged in a matrix at predetermined intervals. Each of these sensors 2 detects vibrations of the aircraft body 1a caused by meteoroid/debris collision with the aircraft body 1a,
The detected vibration data is sent to the DIU via a transmission line 3 such as a coaxial cable, twisted cable, or optical fiber.
The signals are collected in a sampling unit 4 and supplied to a computer 5 via this DIU sampling unit 4. The computer 5 detects the collision position and the degree of impact based on the data sent by each sensor 2. More specifically, as shown in FIG. 2, the No. 1~No. 16
When considering the sensor 2 of , meteoroid/
Assuming that debris collides, the shock wave detection time at each sensor 2 is T1 to T16 (subscripts are the number of sensor 2).
) represents when sampling is performed continuously,
T6 <T10<T7 <T11<T5 <T9
<......<T6. Of these, No. 1 was the first to detect a shock wave. No. 6 detected fourth from sensor 2. 4 sensors 2 up to 11 sensors 2
(No. 6, No. 7, No. 10, No. 1
Focusing on the detection times T6, T7, T10, and T11 in 1). [0011] If the time of meteoroid/debris collision is T0, (T11-T0)2 + (T6-T0)2 = (
T10-T0)2 + (T7-T0)2 0012
] Therefore, T0 = (T112 +T62-T10
2 -T72)/2(T11+T6 -T10-T7
), and T0 is calculated using only the data of T6, T7, T10, and T11. [0013] Also, if the propagation velocity of the shock wave = v, then No.
．． Coordinates (x,
y) is determined by the following calculation. That is, the propagation velocity v is a structural characteristic of the space station 1 and is known, and if l is the interval of the matrix formed by the sensor 2, then x=(l112 -l72+l2)/2ly=(l1
12 -l102 +l2)/2l At this time, l11=v×(T11-T0), l7=v×(
T7 - T0 ), l10 = v x (T10 - T0 ) [
Therefore, the collision position 6 is located at the above coordinates (x, y
). On the other hand, the degree of collision is No. 6, No.
7.No. 10, No. It is determined by detecting the amplitude and energy amount of the shock waves passing through each of the 11 sensors 2 and comparing them with manufacturing characteristics stored as a database in the computer 5. [0018] As described above in detail with the embodiments, according to the present invention, it is possible to quickly grasp the collision position of meteoroid/debris and the degree of impact.

[Brief explanation of drawings]

FIG. 1(a) is a front view showing a part of a space station to which an embodiment of the present invention is applied, and FIG. 1(b) is a view taken along the line A--A in FIG.

FIG. 2 is an explanatory diagram showing the principle of the present invention.

[Explanation of symbols]

1 Space station 2 Sensor

Claims (1)

[Claims] [Claim 1] On the outer peripheral surface of a spacecraft such as a space station or an artificial satellite, in the form of a line or matrix,
A large number of sensors are installed to detect vibrations, and each sensor detects the vibrations generated when the meteoroid/debris collides with the spacecraft. / A method for detecting a collision of meteoroid/debris with respect to a spacecraft, characterized in that the collision position of the debris and the strength of the impact are detected.