RU2539709C1 - Controlled missile - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to missile engineering, namely to controlled missiles. A controlled missile includes a housing with the main control elements symmetrically arranged on it - aerodynamic surfaces and rudders, as well as a wire duct. The latter is arranged along the housing in the incline of rudders. An aerodynamic surface is additionally installed on the housing, on the side opposite to the wire duct.

EFFECT: improvement of aerodynamics of missile flight and improvement of its target guidance accuracy.

2 cl, 1 dwg

Description

The invention relates to the field of rocket technology, in particular to guided missiles, and can be used in various types and classes of missiles, the design of which provides for the presence of gargrot.

This structural element, which is essentially three-dimensional, oriented in the longitudinal direction and placed outside the casing, closes the control wiring, pipelines and electrical wires that extend beyond the main dimensions of the casing, and is widely known in aviation, space and rocketry.

In particular, with regard to aviation technology, from the patent of the Russian Federation No. 2207968, class B64C 30/00, 1999 the construction of a multi-purpose highly maneuverable supersonic aircraft containing garrot is known, and from the application No. 2008115362, class B64D 27/00, 2009 - the presence of garrot in unmanned aerial vehicle.

The presence of gargrot in aerospace engineering is also known from RF patent No. 2072949, class B64D 37/02, 1997.

In the book “I.I. Toropov - Founder and first chief designer of GosMKB Vympel. On the occasion of the centenary of birth ”, Aviamir Publishing House, 2007 shows the appearance of air-to-air missiles R-33 (p. 162), P-73 (p. 161), RVV-AE (p. 164) , the closest analogue), X-29-TE (p. 274), each of which contains a hull, a propulsion system, control system equipment, and combat equipment placed in the hull. At the same time, the main controls - wings and aerodynamic rudders are symmetrically located on the body. Also on the body of the rocket is a garrgot, which protrudes beyond its dimensions and protects electrical communications from external influences.

When flying missiles with angles of attack in an arbitrary plane, the gargrot appears at an angle to the incoming flow and, as a wing of small elongation, creates lift in all control channels, forming a parasitic cross-link between them and at large angles of attack leading to three-channel instability.

The technical result, to which the claimed invention is intended, is to create a guided missile, the design of which would exclude the aforementioned disadvantage introduced by the garrot, i.e. would significantly reduce the effect of this drawback on the aerodynamics of the flight of the rocket and on the accuracy of its guidance on the target.

Obtaining the indicated technical result is ensured by the fact that, in the claimed guided missile, comprising a body with the main controls symmetrically located on it — aerodynamic surfaces and rudders, as well as a garrot, located in their collapse, is additionally installed on the side opposite to the garrot, at least at least one aerodynamic surface to balance the lifting force of the gargrot and the formation of a vortex flow that neutralizes the vortex flow created by the gargrot.

The invention is illustrated by the image of a rocket with a variant containing one aerodynamic surface. Figure 1 shows a view along the axis of the rocket, which shows the rocket casing 1, the main controls symmetrically located on the casing 1, in particular the rudders 2, and the garrot 3 located in their collapse. On the housing 1, opposite to the garrot 3 the side is additionally equipped with an aerodynamic surface 4 for balancing the lifting force of the gargrot and the formation of a vortex flow that neutralizes the vortex flow created by the gargrot.

The configuration of the additional aerodynamic surface is selected in each case, taking into account the obvious technical (structural) limitations and should provide it with load-bearing properties comparable to the load-bearing properties of the garrot.

As a possible embodiment, there can be more than one, for example, two additional aerodynamic surfaces installed on the missile’s body, which will reduce the dimensions and aerodynamic drag of these surfaces. In this case, the aerodynamic surfaces are made in the form of a biplane and are also located in the opposite position of the gargrot part of the rocket, symmetrically with respect to the vertical longitudinal plane of the rocket.

Thus, the aerodynamic surface additionally placed on the body, when the rocket is flying toward the target, especially at large angles of attack, will balance the moment and the vortex flow arising from the gargrot 3, which, in turn, eliminates spurious aerodynamic communication between the control channels and three-channel instability .

Claims (2)

1. Guided missile, comprising a housing with symmetrically placed main controls on it - aerodynamic surfaces and rudders, as well as a garrott, located along the housing in the collapse of the rudders, characterized in that the housing, on the opposite side to the garrot, is additionally installed, at least one aerodynamic surface, to balance the lifting force of the gargrot and its vortex flow. 2. Guided missile according to claim 1, characterized in that with two additionally installed aerodynamic surfaces they are located with the formation of a biplane.