Ignition system used in testing solid propellant compositions for smokelessness
US4068591A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Mar 10, 1976 |
| Grant date | Jan 17, 1978 |
| Priority date | — |
| Expiry date | Mar 10, 1996 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF42C19/0819
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
This invention is an igniter for solid rocket propellants that is used when testing propellant compositions for smokiness. The igniter has a charge of solid propellant in the form of small, generally spherical particles or thin sheets so as to have a large total burning surface and thin web. The composition of the igniter propellant is same or similar to that of the propellant being tested so that true smokiness of the test propellant can be ascertained. Upon ignition, the igniter propellant charge burns rapidly in an igniter combustion chamber and produces a high internal pressure. The hot gases produced by this combustion of the igniter propellant discharge through an orifice in an igniter chamber wall and flow onto the surface of the main propellant being ignited.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.