FIELD: weapons and ammunition.
SUBSTANCE: tested guided missile (GM) is rotated relative to an external axis, and the moment of centrifugal force in respect to the axis of the bearing surface folding is used as the aerodynamic load at opening bearing surfaces of GM. GM rotation is carried out up to the speed, when the value of the specified moment of the centrifugal force matches the value of the aerodynamic load moment. Afterwards the mechanism of the bearing surfaces opening is actuated. The value of the mentioned speed of GM rotation relative to the external axis may be calculated using a certain function.
EFFECT: reduced material and time expenditures when doing tests.
2 cl, 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| BENCH FOR MODELING AERODYNAMIC LOAD ON OPENING AIRCRAFT ELEMENTS | 2016 |
|
RU2633089C1 |
| STAND FOR MODELLING IMPACT OF AERODYNAMIC LOAD ON OPENING ELEMENTS OF AIRCRAFTS | 2014 |
|
RU2559396C1 |
| METHOD FOR CONTROL OF SPIN-STABILIZED MISSILE AND GUIDED MISSILE | 2000 |
|
RU2166727C1 |
| GUIDED MISSILE | 2003 |
|
RU2244897C1 |
| METHOD FOR CONTROL OF SPIN-STABILIZED MISSILE AND GUIDED MISSILE | 2004 |
|
RU2275584C2 |
| GUIDED PROJECTILE | 2001 |
|
RU2196295C1 |
| GUIDED ARTILLERY PROJECTILE | 2000 |
|
RU2177601C1 |
| GUIDED MISSILE AND METHOD OF ITS ASSEMBLY | 2007 |
|
RU2336490C1 |
| AERODYNAMIC CONTROL SURFACE (VERSIONS) | 2000 |
|
RU2184342C2 |
| FOLDING AERODYNAMIC CONTROL | 2005 |
|
RU2284450C1 |
