Abstract

The invention relates to rocket technology, and more particularly to a folding aerodynamic rocket fin. The present folding aerodynamic rocket fin comprises a rotatable part and a root part, a cylindrical torsion bar, and a locking mechanism comprising compression springs and locking members. The root part of the folding aerodynamic rocket fin consists of a pylon and a pivot pin. Configured in both the rotatable part and the pylon of the root part are two mutually parallel axially aligned apertures. Mounted in the upper aperture is a fixed pivot pin of the rotatable part of the folding aerodynamic rocket fin, said pin being fastened to the pylon by a screw. The cylindrical torsion bar is fastened by a hexagonal end part thereof in the fixed pin, and the other end of the torsion bar is pretwisted in the direction of folding of the folding aerodynamic rocket fin and is secured on the rotatable part by a tap wrench. The lower aperture on the rotatable part is configured to allow activation of the mechanism for locking the rotatable part. The mechanism for locking the rotatable part is disposed in an aperture provided in the pylon of the root part and includes locking members, locking member stopping bushings, compression springs, and a tie rod consisting of a cylindrical rod, a threaded cylindrical shear nut and a bushing mountable on an adhesive. The lead-in part of a locking member and the aperture in the pylon are configured to be conical. The technical result consists in providing reliable locking of the folding aerodynamic rocket fin.

IPC Classes  ?

• F42B 10/14 - Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Abstract

The invention relates to the field of aircraft, and more particularly to foldable airfoils and to mechanisms for unfolding and locking same. A mechanism for unfolding and locking an aerodynamic rudder having two fold axes comprises a pylon and a pivotable root panel which are connected by half-shafts, said root panel being lockable, and a source of high-pressure gas disposed inside the pylon for use as an actuator. During the unfolding of a tip panel, a connector mounted on a rod performs an additional translational movement once the root panel has assumed an unfolded working position, said connector acting on a pusher which, in the course of a linear movement, transmits unfolding moment to a shaft disposed in the root panel and connecting the unfolding mechanism via a tensioning member to the tip panel, allowing the latter to unfold. The technical result is the possibility of accommodating an aircraft inside the confined space of a launch canister.

IPC Classes  ?

• F42B 10/14 - Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Abstract

The invention relates to the field of military technology, and more particularly to a system for controlling a missile using aerodynamic fins, and can be used in the development of guided missiles, interceptor missiles and ballistic missiles. The technical result is greater missile guidance accuracy, a simpler missile structure and control system, reduced mass, and less labour-intensive manufacture. A missile is configured for control by four aerodynamic fins. Said fins are arranged symmetrically on the airframe such as to be coplanar on a plane perpendicular to the reference axis of the missile. The missile is further configured to be capable of rolling freely about its longitudinal axis in response to random disturbances, and is designed to allow control using only the pitch and yaw channels. This is provided by the four aerodynamic fins, kinematically interconnected in pairs and having two axes of rotation. For the calculation of control signals for pitch and yaw channel control, the current position of the roll angle of the missile is determined in a reference fixed coordinate system. Said coordinate system is fixed relative to a ground-based coordinate system during flight by means of an inertial system.

IPC Classes  ?

• F42B 10/62 - Steering by movement of flight surfaces
• F42B 15/01 - Arrangements thereon for guidance or control

Abstract

The invention relates to missiles having an aerodynamic control system, and can be used in guided missiles, interceptor missiles and ballistic missiles. Missile control efficiency is increased by reducing the effect of downwash on the missile, i.e. reversal of the control rolling moment. The present missile is based on an aerodynamic canard configuration and comprises an airframe. Disposed in the airframe are a propulsion system, a power supply system, a payload, and control system apparatus. Said apparatus contains four aerodynamic fins. Four wings are arranged on the airframe, symmetrically about the longitudinal axis thereof. To reduce the effect of downwash occurring behind the aerodynamic fins and the airframe of the missile during flight at a non-zero angle of attack on the reversal of the control rolling moment and the aerodynamic resistance of the missile as a whole, a unitized wing assembly is used. The latter structurally unites the four wings of the missile into a single assembly. Said assembly is mounted on a ring bearing for movement relative to the airframe of the missile. During flight, the assembly is capable of rotating freely about the reference axis of the missile and allows the wings to self-adjust by virtue of a feathering effect in accordance with the downwash of air behind the aerodynamic fins and the airframe of the missile.

IPC Classes  ?

• F42B 10/62 - Steering by movement of flight surfaces
• F42B 15/01 - Arrangements thereon for guidance or control