KR970705001A

KR970705001A - Gyroscope stabilized launch system for use in underwater objects

Info

Publication number: KR970705001A
Application number: KR1019970700836A
Authority: KR
Inventors: 에이 브라운 제프리; 리드 콥세이; 마샬 툴린; 로이 클라인
Original assignee: 완다케이. 델슨-로우; 에이치이 홀딩스, 인크., 두잉 비지니스 애즈 휴우즈 일렉트로닉스
Priority date: 1995-06-07
Filing date: 1996-06-04
Publication date: 1997-09-06
Also published as: NO970554D0; AU685027B2; NO970554L; CA2196970A1; EP0774104B1; WO1996041114A1; IL120160A0; EP0774104A1; DE69610968D1; DE69610968T2; AU6044796A; JPH10501881A

Abstract

발사체(50)는 공기 중의 한 위치로부터, 공기/물 경계면을 통해, 그리고 수중물체(24)를 향해 추진된다. 발사체(50)는 발사체(50) 주위에 캐비테이션 공간(30)을 형성하는 전방 단부(52)를 포함하여, 발사체 주위의 물 견인을 피한다. 발사체(50)는 발사체가 물을 통과할 때 캐비테이션 공간(30)의 벽 속으로 발사체가 요잉하는 경우에 캐비테이션 공간의 측면과 접촉하여 발사체(50)가 전도시키는 것을 방지하는 복귀력을 발생시키는 측방향 안정화기(90)을 더 포함한다.The projectile 50 is propelled from one position in the air, through the air / water interface, and toward the underwater object 24. Projectile 50 includes a forward end 52 that forms a cavitation space 30 around projectile 50 to avoid water traction around the projectile. The projectile 50 is a side that generates a return force to prevent the projectile 50 from conducting when it contacts the side surface of the cavitation space when the projectile jets into the wall of the cavitation space 30 when the projectile passes water And further includes a direction stabilizer (90).

Description

Gyroscope stabilized launch system for use in underwater objects

본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음Since this is a trivial issue, I did not include the contents of the text.

제1도는 본 발명는 수중에 잠수되어 있는 목표물을 향해서 공중으로부터 발사되는 일련의 발사체에 대한 개략도이다.FIG. 1 is a schematic view of a series of projectiles launched from the air toward a target submerged in water; FIG.

제2도는 발사체의 일 실시예에 대한 측면도이다.Figure 2 is a side view of one embodiment of the projectile.

제3도는 저2도의 발사체의 전방 단부 정면도이다.3 is a front view of the front end of the projectile of the second degree.

제4도는 제3도의 선 4-4를 따라서 취하여 도시한 것으로 제2도 및 제3도의 발사체에 대한 단면도이다.4 is a cross-sectional view of the projectile of FIGS. 2 and 3, taken along line 4-4 of FIG.

제5도는 제2도에 대한 개략적 상세도로서 발사체의 후방부를 나타내는 도면이다.FIG. 5 is a schematic view of the rear portion of the projectile as a schematic detail of FIG. 2.

제6도는 제2도에 대한 상세도로서 스팅어 헤드를 나타내는 도면이다.FIG. 6 is a view showing the stinger head as a detail of FIG. 2.

Claims

CLAIMS What is claimed is: 1. A launch vehicle system having a generally cylindrical symmetrical projectile with a projectile front end and a projectile rear end, the projectile system comprising a stinger head at a forward end of the launcher, a generally cylindrical symmetrical projectile body connected to the stinger head, Wherein the stinger head has a stinger nose having a maximum diameter of a nose and a stinger body having a stenter body front end connected to a rear end of the stinger nose, Wherein the flow separation groove has a diameter smaller than a maximum diameter of the nose, and the projectile body has a diameter larger than the maximum diameter of the nose, and the flow separation groove has a diameter smaller than the maximum diameter of the nose, and the stinger nose support portion has a stator nose support portion having a nose- With a large projectile rear diameter Projectile and the rear part, the front end is Stinger nose support and the launch vehicle system, characterized in that the rear end portion has a front projectile connected to a launch vehicle rear portion.

The launch vehicle system of claim 1, wherein the stinger nose comprises a blunt forward or conical front face.

The stinging nose according to claim 1, characterized in that the stinger nose has a stinger nose forward region having a maximum diameter of the stinger nose forward region and a stinger nose rear region having a maximum diameter of the stinger nose rear region smaller than the maximum diameter of the stinger nose forward region .

The launch vehicle system according to claim 1, wherein the flow separation groove has a forwardly facing separation groove between the stinger nose and the stinger nose support.

The launch vehicle system according to claim 1, wherein said projectile rear portion comprises a cylindrical central region and a plurality of grooves in said central region.

The launch vehicle system according to claim 1, wherein said projectile rear portion comprises a warhead cavity and a warhead embedded in said warhead cavity.

2. The launch vehicle system of claim 1, wherein the stabilizing means comprises a forward stabilizing shoulder located between the rear portion of the projectile and the forward portion of the projectile.

8. The launch vehicle system of claim 7, wherein the stabilizing means further comprises a flattened extension in the radial direction on the rear portion of the launch vehicle at the rear end of the launch vehicle.

The launch vehicle system of claim 1, wherein the stinger nose has a surface finish of about 16 microinches.

The launch vehicle system of claim 1, wherein the stinger head is made from a material selected from the group consisting of steel and tungsten carbide.

The launch vehicle system of claim 1, further comprising a disposable anvil plate attached around the launch vehicle.

A method of destroying an underwater target, comprising: a generally cylindrical symmetrical projectile body having a projectile body front end portion and a projectile body rear end portion; Providing a projectile system having means for forming a cavitation space and stabilizing means for stabilizing the projectile with respect to lateral stability connected to the projectile body; And propelling the projectile towards the underwater target into the water.