JPH0285296U - - Google Patents

Info

Publication number
JPH0285296U
JPH0285296U JP16198088U JP16198088U JPH0285296U JP H0285296 U JPH0285296 U JP H0285296U JP 16198088 U JP16198088 U JP 16198088U JP 16198088 U JP16198088 U JP 16198088U JP H0285296 U JPH0285296 U JP H0285296U
Authority
JP
Japan
Prior art keywords
missile
section
guidance
propulsion section
propulsion
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
Application number
JP16198088U
Other languages
Japanese (ja)
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed filed Critical
Priority to JP16198088U priority Critical patent/JPH0285296U/ja
Publication of JPH0285296U publication Critical patent/JPH0285296U/ja
Pending legal-status Critical Current

Links

Landscapes

  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Description

【図面の簡単な説明】[Brief explanation of drawings]

第1図はこの考案によるミサイルの構成図、第
2図は従来のミサイルの構成図である。 図において、1は誘導部、2は弾頭部、3は制
御部、4は推進部、5は前翼、6は後翼、7はミ
サイルを示す。なお、各図中同一符号は同一又は
相当部分を示す。
FIG. 1 is a block diagram of a missile according to this invention, and FIG. 2 is a block diagram of a conventional missile. In the figure, 1 is a guidance section, 2 is a warhead, 3 is a control section, 4 is a propulsion section, 5 is a front wing, 6 is a rear wing, and 7 is a missile. Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims (1)

【実用新案登録請求の範囲】[Scope of utility model registration request] 後翼操舵方式のミサイルにおいて、機首に設け
た誘導部と弾頭部の間に推進部を設け、ミサイル
飛行時における前記推進部の推薬燃焼による重量
軽減に伴つてミサイル重心が後方に移動する事に
より、ミサイル終末誘導時の運動性をミサイル発
射時点よりも増加させた事を特徴とするミサイル
In a rear-wing steering missile, a propulsion section is provided between the guidance section installed in the nose and the warhead, and the center of gravity of the missile moves rearward as the weight is reduced by propellant combustion in the propulsion section during missile flight. This missile is characterized by having increased maneuverability during final guidance compared to when the missile was launched.
JP16198088U 1988-12-14 1988-12-14 Pending JPH0285296U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP16198088U JPH0285296U (en) 1988-12-14 1988-12-14

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP16198088U JPH0285296U (en) 1988-12-14 1988-12-14

Publications (1)

Publication Number Publication Date
JPH0285296U true JPH0285296U (en) 1990-07-04

Family

ID=31445394

Family Applications (1)

Application Number Title Priority Date Filing Date
JP16198088U Pending JPH0285296U (en) 1988-12-14 1988-12-14

Country Status (1)

Country Link
JP (1) JPH0285296U (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9963482B2 (en) 2011-09-30 2018-05-08 Tohoku University Phosphatidylinositol-3-kinase inhibitor and pharmaceutical composition

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9963482B2 (en) 2011-09-30 2018-05-08 Tohoku University Phosphatidylinositol-3-kinase inhibitor and pharmaceutical composition

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