FIELD: armament.
SUBSTANCE: the control actuator unit of the guided missile has a fairing with slots for the sealing flaps made in the area of the slots for outlet of the control surfaces. The contour of the fairing is made curvilinear. The flaps are made in radius. The radius of the flaps is selected from the condition of coincidence of the extreme points and the mid-point of the flap profile with the respective points of the profile of the slot for the flaps. The width and the length of the flaps equals the width and the length of the fairing slots. The relation of the area of sticking of the flaps and the area of the slots for outlet of the control surfaces is made according to a definite dependence.
EFFECT: simplified construction, as well as enhanced reliability of operation of the guided missile control actuator unit.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GUIDED PROJECTILE STEERING DRIVE UNIT | 2009 |
|
RU2399866C1 |
| GUIDED MISSILE AND METHOD OF ITS ASSEMBLY | 2007 |
|
RU2336490C1 |
| CONTROL ACTUATOR UNIT OF GUIDED PROJECTILE | 2004 |
|
RU2280231C1 |
| GUIDED MISSILE ACTUATOR ASSEMBLY | 1996 |
|
RU2101666C1 |
| AIR-DYNAMIC UNIT OF GUIDED MISSILE CONTROL ACTUATOR | 1996 |
|
RU2092782C1 |
| METHOD OF OPENING CONTROL SURFACES OF GUIDED PROJECTILE ACTUATOR UNIT AND ACTUATOR UNIT FOR REALIZATION OF THIS METHOD | 2002 |
|
RU2237598C2 |
| GUIDED MISSILE | 2005 |
|
RU2295698C1 |
| GUIDED MISSILE CONTROL ACTUATOR UNIT | 1995 |
|
RU2087841C1 |
| GUIDED MISSILE | 2003 |
|
RU2248517C2 |
| CONTROLLED PROJECTILE, STEERING DRIVE GROUP OF CONTROLLED PROJECTILE, PNEUMATIC DISTRIBUTION DEVICE OF STEERING DRIVE OF CONTROLLED PROJECTILE, MECHANISM OF INITIATION OF STEERING DRIVE OF CONTROLLED PROJECTILE | 2017 |
|
RU2669979C1 |
