FIELD: engines and pumps.
SUBSTANCE: proposed method comprises fitting the charge in solid-propellant rocket engine combustion chamber and thermostatting said charged engine at the temperature of accelerated climatic tests. Period of thermostatting is determined with due allowance for solar radiation effects by relationships protected by this invention. Then, solid-propellant rocket engine is disassembled to check the charge for integrity. Thereafter, charge is fitted again in the engine to perform firing trial for compliance with technical requirements.
EFFECT: higher accuracy of estimating serviceability in accelerated climatic tests of slid-propellant charge.
3 dwg, 2 tbl
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF SOLID PROPELLANT CHARGE CHANNEL ARMOURING | 2006 |
|
RU2337088C2 |
| SOLID PROPELLANT ROCKET ENGINE (VERSIONS) | 2009 |
|
RU2412369C1 |
| THERMOPLASTIC LOW-SMOKE ACETYLCELLULOSE-BASED ARMORING COMPOSITION WITH ELEVATED HEAT RESISTANCE | 2005 |
|
RU2276174C1 |
| PROPELLANT CHARGE FOR ROCKET ENGINE | 2010 |
|
RU2451816C1 |
| METHOD FOR MEASURING ADHESIVE STRENGTH BETWEEN ROCKET ARMOUR COATING AND THE SURFACE OF SOLID ROCKET FUEL GRAIN | 2010 |
|
RU2442138C1 |
| SOLID-FUEL CHARGE FOR ROCKET ENGINE | 2011 |
|
RU2464440C1 |
| METHOD OF ARMORING OF THE SOLID PROPELLANT CHARGES (VERSIONS) | 2006 |
|
RU2317199C1 |
| ARMOURING COMPOSITION FOR COATING SOLID PROPELLANT CHARGE | 2009 |
|
RU2412969C1 |
| SOLID PROPELLANT ROCKET ENGINE | 2008 |
|
RU2383764C1 |
| ARMOURING METHOD OF INSERTABLE SOLID-PROPELLANT CHARGE WITH EPOXY ARMOUR COMPOUND ALONG SIDE SURFACE, AND METHOD FOR DETERMINING EPOXY ARMOUR COMPOUND VISCOSITY | 2011 |
|
RU2458243C1 |
