Multi-stage rocket motors
US5419118A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jan 19, 1994 |
| Grant date | May 30, 1995 |
| Priority date | — |
| Expiry date | Jan 19, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A motor for impelling a missile or projectile has a housing and a plurality of spaced walls defining progressive compartments in the housing. A nozzle in one of the compartments produces a thrust for the missile or projectile when pressurized gases flow through it. Igniters extending into the individual compartments ignite propellants in such compartments. The igniter in an individual one of the compartments is energized initially and the igniters progressively displaced from such individual compartment are thereafter energized sequentially. Each wall separating an individual pair of adjacent compartments has a normally closed valve. Each valve has a first orifice of relatively great area in the compartment closer to the nozzle and a second orifice of limited area in the compartment further from the nozzle. A membrane between the orifices prevents the valve from being opened by a pressure from the closer compartment until this pressure becomes relatively great (e.g. 6500 psi). When a comparatively low pressure (e.g. 1500 psi) is applied in the second orifice by propellant combusting in the further compartment, the membrane ruptures. The rupture is facilitated by dimpling the membra…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.