FIELD: rocketry.
SUBSTANCE: blade front and rear edges represent a combination of a flat 0.1 to 0.3-wide blunting of the blade mean thickness along the span and a wedge on the blade convex side with the angle of 7° to 12° in the plane perpendicular to the edges. The width of the flat blunting is constant along the blade span. The blade front and rear edge parts adjoining the blade end chord are rounded off with a radius of 2 to 7 thicknesses of the blade at its end part. The relation of the blade root chord to its height defined from the expression h=(H-do)/2 is selected in the limits of 1,5 to 3,0 where h is the blade height, H is the fin span, do is the fairing diameter. It results in smaller scatter of the fin drag characteristics and shell aeroballistic characteristics, reduction of geometrical parameters of blades.
EFFECT: increased shell range, higher accuracy of hits and reliability.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ROCKET PROJECTILE STABILIZER | 2022 |
|
RU2790655C1 |
| MISSILE STABILIZER | 2023 |
|
RU2814624C1 |
| SUPERSONIC CONTROLLED PROJECTILE | 2011 |
|
RU2459177C1 |
| TAIL PLANE STABILIZER OF SUPERSONIC JET PROJECTILE | 2001 |
|
RU2176066C1 |
| SUPERSONIC SPIN-STABILIZED MISSILE | 2023 |
|
RU2809446C1 |
| ROCKET STABILIZER | 2022 |
|
RU2790653C1 |
| ROTARY JET PROJECTILE | 2011 |
|
RU2451902C1 |
| MISSILE | 2023 |
|
RU2814640C1 |
| MISSILE PART WITH STABILISER OF ROCKET PROJECTILE | 2014 |
|
RU2540291C1 |
| SUPERSONIC PROJECTILE | 2016 |
|
RU2642693C2 |
