FIELD: machine building.
SUBSTANCE: rocket part of a jet projectile contains a solid-propellant rocket engine with a nozzle, a block of stabilizers consisting of a base and blades fixed on it. Difference between the outer (R) and inner (Ra) radii of the jet projectile in the section passing through the nozzle section is selected by formula (R-Ra)=(0.02…0.812)L, where L is the distance from the rear edge of the blade to the nozzle outlet section.
EFFECT: design of the rocket part in accordance with the invention ensures stability of the jet projectile in the process of movement along the trajectory at supersonic flight speeds, as well as increases the reliability of operation of the aerodynamic stabilization elements during operation.
1 cl, 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ROCKET PROJECTILE WITH A GAS-DYNAMIC STABILIZATION SYSTEM | 2020 |
|
RU2756195C1 |
| MISSILE | 2023 |
|
RU2814640C1 |
| ROCKET PROJECTILE STABILIZER | 2022 |
|
RU2790655C1 |
| ROTATING MISSILE | 2020 |
|
RU2732370C1 |
| HYPERSONIC MISSILE | 2023 |
|
RU2806859C1 |
| MISSILE WITH AIR-JET ENGINE | 2015 |
|
RU2585211C1 |
| MISSILE STABILIZER | 2023 |
|
RU2814624C1 |
| TAIL UNIT OF SPIN-STABILIZED MISSILE | 2001 |
|
RU2182309C1 |
| MISSILE PART WITH STABILISER OF ROCKET PROJECTILE | 2014 |
|
RU2540291C1 |
| SUPERSONIC PROJECTILE | 2016 |
|
RU2642693C2 |
