JPS61135199U

JPS61135199U -

Info

Publication number: JPS61135199U
Application number: JP5886U
Authority: JP
Priority date: 1986-01-06
Filing date: 1986-01-06
Publication date: 1986-08-22

Description

[Brief explanation of the drawing]

第１図は本考案にしたがつた特定の配列の立面
図、第２図は本考案にしたがつた他の特定の配列
の立面図、第３図はロケツト発射筒の詳細部を示
した本考案にしたがつた配列の平面図、第４図は
本考案にしたがつたさらに他の配列の平面図であ
る。１０……本考案にしたがつた装置、１２……密
閉高圧室、１４，１６……ロケツト発射筒、１８
……ロケツト、２０……キヤツプ、２２……シー
ル、２４……ロケツト、２６，２８……直立排気
ダクト、３０，３２……エルボ。 1 is an elevational view of a particular arrangement according to the invention, FIG. 2 is an elevational view of another particular arrangement according to the invention, and FIG. 3 shows details of a rocket launcher. FIG. 4 is a plan view of yet another arrangement according to the present invention. 10... Device according to the present invention, 12... Sealed high pressure chamber, 14, 16... Rocket launcher, 18
... Rocket, 20 ... Cap, 22 ... Seal, 24 ... Rocket, 26, 28 ... Upright exhaust duct, 30, 32 ... Elbow.

Claims

[Claims for Utility Model Registration] (1) A rocket-enclosed high-pressure chamber exhaust structure for suppressing undesirable combustion of raw exhaust gas in a manifold, comprising a plurality of rocket-enclosed high-pressure chamber exhaust structures positioned in a line adjacent to each other. a rocket launcher; a continuous closed high-pressure chamber extending generally horizontally along a linear row of launchers and having means for connecting to each launcher at its base; A device for releasably sealing a launcher near its base from communication with the sealed high-pressure chamber, and for introducing exhaust gas from the rocket into the sealed high-pressure chamber at the time of launch. a sealing device adapted to open upon firing of the rocket within the cylinder and close to sealingly shut off said launcher under all other circumstances; each connected to each end of said sealed hyperbaric chamber; an exhaust structure having an exhaust duct 26, 28 extending from the high pressure chamber 12 at right angles thereto via a pair of smoothly continuous elbows, one for each exhaust duct; extending generally upwardly, said elbows 30, 32 having a generally constant radius connecting the associated exhaust duct to the corresponding end of the enclosed hyperbaric chamber, and said exhaust ducts 26, 28 extending generally upwardly. The cross-sectional area is approximately equal to the cross-sectional area of the high-pressure chamber 12, and the exhaust gas flow rate is approximately 0.5 mm in a steady state during firing of the rockets 18, 24 from the associated launch tubes 14, 16. A structure that is designed to generate a . (2) A structure according to claim 1 of the utility model registration, in which each duct 26, 28 has a substantially constant cross-sectional area over its entire length. (3) Utility Model Registration In the structure described in claim 1, at least one exhaust duct 42, 44 extends from an inlet end adjacent to the closed high pressure chamber 12 to an outlet remote from the closed high pressure chamber. A structure having a cross-sectional area that increases proportionally with the distance to the end. (4) In the structure according to claim 3 of the utility model registration, both of the exhaust ducts 42 and 44 have a similar shape, and the cross-sectional area gradually increases from the inlet end to the outlet end. Structure. (5) In the structure described in any one of claims 1 to 4 of the claims for registration of a utility model, the exhaust duct (26, 28 or 42, 44
) has a cross-sectional area over its entire length that is at least not smaller than the minimum cross-sectional area of the closed high-pressure chamber 12. (6) Utility model registration Claims In the structure described in any one of claims 1 to 5, the launch tubes 14, 16, the sealed high pressure chamber 12 and the exhaust duct (26, 28 or 42) , 44) is mounted well below the ship's deck 34, and the launch tube and exhaust duct have an opening extending upwardly through the deck.