JPH07215299A - Loading apparatus installing method and structure in space navigating object - Google Patents
Loading apparatus installing method and structure in space navigating objectInfo
- Publication number
- JPH07215299A JPH07215299A JP753394A JP753394A JPH07215299A JP H07215299 A JPH07215299 A JP H07215299A JP 753394 A JP753394 A JP 753394A JP 753394 A JP753394 A JP 753394A JP H07215299 A JPH07215299 A JP H07215299A
- Authority
- JP
- Japan
- Prior art keywords
- mounting
- loading apparatus
- conical fitting
- equipment
- installing method
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、宇宙航行体への搭載機
器取付方法及び構造に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method and structure for mounting equipment mounted on a spacecraft.
【０００２】[0002]
【従来の技術】従来、宇宙航行体への機器取付位置は設
計結果によって一義的に固定されてしまい、宇宙航行体
のマスアンバランス量に対し上限値が規定され、かつ現
状がそれを超えている場合には、“バランスウェイト”
と呼ばれる重りを衛星各部に取付けることで対処してい
た。2. Description of the Related Art Conventionally, the equipment mounting position on a spacecraft is uniquely fixed according to the design result, and an upper limit value is specified for the mass unbalance amount of the spacecraft, and the current situation exceeds that. If there is, "balance weight"
The problem was dealt with by attaching a weight called a to each part of the satellite.
【０００３】[0003]
【発明が解決しようとする課題】この従来の機器取付方
法では、機器重量の製造によるばらつき、構造体製造後
に生じた機器の設計重量変更等、あらかじめ予測し得な
い、または構造体製造に反映できないマスアンバランス
原因に対しては、バランスウェイトという新たな重量を
擁して対処せざるを得なく、一般的に衛星全体重量上限
に対して厳しい要求を課せられる宇宙航行体のシステム
成立性に大きな影響を与えるという問題点があった。With this conventional method for mounting equipment, it is not possible to predict in advance such as variations in the weight of equipment due to manufacturing, changes in the design weight of equipment that have occurred after manufacturing the structure, or it is not possible to reflect this in manufacturing the structure. For the cause of mass unbalance, we have no choice but to deal with a new weight called balance weight, which has a great impact on the system viability of spacecraft, which generally imposes severe requirements on the upper limit of the total weight of satellites. There was a problem of giving.
【０００４】[0004]
【課題を解決するための手段】前記課題を解決する為、
本発明の機器取付方法は、偏心したコニカルフィッティ
ングを取付けに用い、かつコニカルフィッティングは偏
心量の異なる数種類を用意しておくことを特徴とするも
のである。[Means for Solving the Problems] In order to solve the above problems,
The device mounting method of the present invention is characterized in that an eccentric conical fitting is used for mounting, and several kinds of conical fittings having different eccentric amounts are prepared.
【０００５】[0005]
【実施例】以下、本発明の実施例を図面を参照して説明
する。図１は本発明の一実施例の外観図であり、搭載機
器１の取付足部分２が、構造体３に、コニカルフィッテ
ィング４を介して取付用ボルト５によって取付けられい
る。所用数のコニカルフィッティングの偏心量、偏心方
向を揃えることにより、機器取付位置を取付面内方向に
移動されることができる。Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is an external view of an embodiment of the present invention, in which a mounting foot portion 2 of a mounted device 1 is mounted on a structure 3 via a conical fitting 4 by mounting bolts 5. By aligning the eccentric amount and the eccentric direction of the required number of conical fittings, the device mounting position can be moved in the mounting surface inward direction.
【０００６】図２は、図１のＡ−Ａ断面の拡大図であ
り、機器取付足をコニカルフィッティング外形に即した
形状に設計することにより、コニカルフィッティングの
外形が変わらない限り、機器設計に影響を与えることな
くコニカルフィッティング偏心量、偏心方向を選択でき
る。また図３はコニカルフィッティングの単体図であ
り、偏心量Ｓの異なるものを用意しておくことで、必要
な機器取付位置移動を実現することができる。FIG. 2 is an enlarged view of the AA cross section of FIG. 1, and by designing the equipment mounting feet in a shape conforming to the contour of the conical fitting, the equipment design is affected unless the contour of the conical fitting changes. The conical fitting eccentricity amount and eccentric direction can be selected without giving. Further, FIG. 3 is a unitary view of the conical fitting, and by preparing those having different eccentric amounts S, it is possible to realize the required equipment mounting position movement.
【０００７】[0007]
【発明の効果】以上説明したように、本発明の機器取付
方法は機器取付時に機器取付位置の調整が可能な為、ノ
ミナルの取付位置で生じてしまうマスアンバランスに対
し、ある程度までバランスウェイトなしでの対応が可能
となる為、不測のマスアンバランスが生じた場合のシス
テム成立性への影響を最小限に抑えることが出来る。As described above, according to the device mounting method of the present invention, since the device mounting position can be adjusted when mounting the device, there is no balance weight to some extent against the mass imbalance that occurs at the nominal mounting position. Therefore, it is possible to minimize the influence on the system viability when an unexpected mass imbalance occurs.
【図１】本発明の一実施例の外観図。FIG. 1 is an external view of an embodiment of the present invention.
【図２】図１のＡ−Ａ断面の拡大図。FIG. 2 is an enlarged view of an AA cross section of FIG.
【図３】本発明のコニカルフィッティング単体図。FIG. 3 is a conical fitting unit diagram of the present invention.
１ 搭載機器 ２ 搭載機器取付足部分 ３ 構造体 ４ コニカルフィッティング ５ 取付用ボルト、Ｓ 偏心量 1 On-board equipment 2 On-board equipment mounting foot part 3 Structure 4 Conical fitting 5 Mounting bolt, S Eccentricity
Claims (3)
ィングを使用することを特徴とする宇宙航行体への搭載
機器取付方法。1. A method of mounting on-board equipment to a spacecraft, which comprises using a conical fitting having an eccentric mounting hole.
ィッティングと、コニカルフィッティングを受け入れる
穴をもつ搭載機器の取付足部分と、コニカルフィッティ
ングの取付穴を介して搭載機器を宇宙航行体に取付ける
宇宙航行体への搭載機器取付構造。2. A space navigation system in which a conical fitting having a mounting hole at an eccentric position, a mounting foot portion of a mounted device having a hole for receiving the conical fitting, and a mounting device mounted on a spacecraft through the mounting hole of the conical fitting. Mounting structure for equipment mounted on the body.
とするコニカルフィッティング。3. A conical fitting having a mounting hole at an eccentric position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP753394A JPH07215299A (en) | 1994-01-27 | 1994-01-27 | Loading apparatus installing method and structure in space navigating object |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP753394A JPH07215299A (en) | 1994-01-27 | 1994-01-27 | Loading apparatus installing method and structure in space navigating object |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH07215299A true JPH07215299A (en) | 1995-08-15 |
Family
ID=11668430
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP753394A Pending JPH07215299A (en) | 1994-01-27 | 1994-01-27 | Loading apparatus installing method and structure in space navigating object |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH07215299A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016528095A (en) * | 2013-07-24 | 2016-09-15 | ロッキード マーティン コーポレイションＬｏｃｋｈｅｅｄ Ｍａｒｔｉｎ Ｃｏｒｐｏｒａｔｉｏｎ | Parallel dual launch mechanism |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5066649A (en) * | 1973-10-20 | 1975-06-05 |
-
1994
- 1994-01-27 JP JP753394A patent/JPH07215299A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5066649A (en) * | 1973-10-20 | 1975-06-05 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016528095A (en) * | 2013-07-24 | 2016-09-15 | ロッキード マーティン コーポレイションＬｏｃｋｈｅｅｄ Ｍａｒｔｉｎ Ｃｏｒｐｏｒａｔｉｏｎ | Parallel dual launch mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 19980210 |