DESIGN AND MANUFACTURING OF A SINGLE PIECE ROCKET ENGINE
关于老挝专利「DESIGN AND MANUFACTURING OF A SINGLE PIECE ROCKET ENGINE」,老商通整理了如下公开信息,由 AGNIKUL COSMOS PRIVATE LIMITED 于 2010-10-23 提交申请,当前状态为等待形式审查。标识字段包括:申请号 P/895;DIP 编号 LAP895;主管局代码 LA;保护类型 Patent - PCT National Phase。时间线要点:公开/公告日 2026-04-03。技术或外观分类记载为 B33Y 50/00。发明人 / 设计人包括 RAVICHANDRAN, Srinath、SHAH KHADRI, Syed Peer Mohamed。代理机构 / 代理人记载为 ACTIP (LAO) IP CO., LTD.。公开摘要提示:Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an…。
P/895
图样
基础信息
- 类型
- 专利
- 申请号
P/895- 状态
- 等待形式审查
- 申请人
- AGNIKUL COSMOS PRIVATE LIMITED
- 代理机构
- ACTIP (LAO) IP CO., LTD.
- 申请日期
- 2010-10-23
- 公开 / 公告日
- 2026-04-03
- 保护类型
- Patent - PCT National Phase
- 优先权
- IN · 202041046382 · 2020-10-23
- 申请人地址
- AGNIKUL COSMOS PRIVATE LIMITED · 910, Syndicate Bank Colony, Anna Nagar West Extension, Chennai, Tamil Nadu 600101, India · IN
- 代理地址
- ACTIP (LAO) IP CO., LTD. · Sisavath Village, Chanthabouly District, Vientiane, Lao PDR · LA
- 国际分类
- B33Y 50/00
- 商品 / 服务
- —
办理流程
根据当前状态动态标注-
提交申请
-
形式审查 进行中
-
实质审查
-
公开
-
授权
关联分析
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摘要
Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an integrated engine that comprises a combustion chamber to burn the fuel, an injector plate (504) to inject the fuel to the combustion chamber, an igniter (502) to ignite the fuel mixture, anozzle (506) to pass hot gas to produce thrust and cooling channels (508) for regenerative cooling, where all these components are fused to form a single piece integrated engine. The engine of the present invention eliminates the need of assembling the individual components. Further, the engine is additively manufactured with high grade aerospace materials. Thus, the cost and mass of the engine is reduced when compared to traditionally manufactured engines, which leads to frequent missions.
Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an integrated engine that comprises a combustion chamber to burn the fuel, an injector plate (504) to inject the fuel to the combustion chamber, an igniter (502) to ignite the fuel mixture, anozzle (506) to pass hot gas to produce thrust and cooling channels (508) for regenerative cooling, where all these components are fused to form a single piece integrated engine. The engine of the present invention eliminates the need of assembling the individual components. Further, the engine is additively manufactured with high grade aerospace materials. Thus, the cost and mass of the engine is reduced when compared to traditionally manufactured engines, which leads to frequent missions.
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