RU154723U1 - GUIDED MISSILE - Google Patents

Abstract

Guided missile containing a housing, a turbojet engine, wings, aerodynamic executive controls, consisting of rudders and ailerons, and an actuator drive, characterized in that the rudders are installed in front of the center of mass of the rocket at a distance of a = (5 ... 8) d, where d is the caliber of the rocket, and made in the form of two trapezoidal plates mounted on a horizontally located shaft mechanically connected to the steering gear, and the ailerons are located behind the center of mass of the rocket, made in the form of four trapezoidal plates, the area of each of which is 0.3 ... 0.5 of the area of the steering wheel, and mounted on shafts, which in turn are mechanically connected, for example, using a parallelogram mechanism, with a single aileron drive, while the wings on the rocket body are mounted at a distance from the center of mass no more than b = 4d with the displacement of the bearing planes relative to each other by c = (0.03 ... 0.15) d in antiphase to the direction of installation of the turbine blades of the turbojet engine.

Description

Technical field

The utility model relates to the field of weapons, namely to guided missiles, and can be used in their development.

State of the art

The claimed utility model is a guided missile with increased flight range and combat effectiveness.

The use of guided missiles equipped with aerodynamic bearing surfaces and control elements allows us to solve the problem of increasing firing accuracy and target range by optimizing their aerodynamic characteristics.

Various technical solutions for guided missiles are known in the art.

So, for example, an aircraft-guided missile is known according to the invention patent RU No. 2259536, published on 08.27.2005, consisting of a body, a propulsion system, wings, rudders and steering gears, adopted by the authors as an analogue.

Among the disadvantages of this technical solution can be noted such as the insufficient use of the aerodynamic capabilities of the rocket to achieve maximum flight range in view of the lack of optimization of its aerodynamic characteristics.

The closest set of essential features to the claimed utility model is a cruise missile according to the utility model certificate RU No. 25931, published on 10.27.2002, which includes a body, a turbojet engine, wings and aerodynamic executive controls.

The disadvantages of this technical solution are the unregulated relative location of the controls on the rocket body, which does not allow for optimal aerodynamic characteristics, and the presence of torque relative to the longitudinal axis of the rocket transmitted by high-speed rotation of the turbine of a turbojet rocket engine, requiring constant compensation by deflecting the controls in the roll channel and leading to an increase in aerodynamic drag. Both of these circumstances lead to a decrease in flight range.

Utility Model Disclosure

The task to which the claimed utility model is directed is to create a guided missile with an increased flight range and increased combat effectiveness.

The technical result obtained by the implementation of the claimed utility model is the optimization of aerodynamic characteristics, achieved by increasing lift while reducing drag, and increasing the mass of the delivered payload.

The specified technical result is achieved due to the fact that in a guided missile, consisting of a body, a turbojet engine, wings, aerodynamic executive controls, including rudders and ailerons, and actuator actuators, the rudders are installed in front of the center of mass of the rocket at a distance a = ( 5 ... 8) d, where d is the caliber of the rocket, and made in the form of two trapezoidal plates mounted on a horizontally located shaft mechanically connected to the steering gear, and the ailerons are located behind the center of mass of the rockets s, made in the form of four trapezoidal plates, the area of each of which is 0.3 ... 0.5 of the steering wheel area, and mounted on shafts, which in turn are mechanically connected, for example using a parallelogram mechanism, with a single aileron drive, while the wings on the rocket body are installed at a distance from the center of mass of no more than b = 4d with the displacement of the bearing planes relative to each other by c = (0.03 ... 0.15) d in antiphase to the direction of installation of the turbine blades of the turbojet engine.

The execution of the rudders in the form of two trapezoidal plates mounted in front of the center of mass of the rocket at a distance of a = (5 ... 8) d makes it possible to increase the flight range due to flight at optimal balancing angles of attack. The use of trapezoidal plates as rudders allows for their smooth flow around, which leads to a decrease in aerodynamic drag. The installation of the rudders in front of the center of mass of the rocket at a distance of a = (5 ... 8) d allows you to create an aerodynamic moment leading to the rocket reaching the maximum effective angle of attack, thereby allowing for the highest possible lifting force. The execution of rudders of a less streamlined shape, as well as their installation at a distance less than a = 5d from the center of mass of the rocket, leads to a deterioration in the aerodynamic characteristics of the rocket either due to an increase in drag or due to a decrease in the balancing angle of attack and a decrease in lift. Installing more rudders on a -8d distance from the center of mass causes the missile to the output of the rocket at too high angles of attack, which increase the aerodynamic resistance becomes more intense than the increase in lift. In addition, when reaching large angles of attack, flow disruptions may occur, which leads to unsteady flow and a deterioration in aerodynamic characteristics, and, consequently, to a decrease in flight range.

The location of the ailerons, made in the form of four trapezoidal plates, the area of each of which is 0.3 ... 0.5 from the rudder area, behind the rocket's center of mass, allows the rocket to be controllable in the roll channel and at the same time ensure stable rocket movement along the trajectory. The implementation of ailerons in the form of trapezoidal plates allows, as in the case of rudders, to reduce the value of aerodynamic drag. The installation of rudders in front of the center of mass of the rocket leads to the creation of a destabilizing moment (even with non-deviated rudders), which tends to overturn it. To compensate for this moment, ailerons are installed behind the center of mass, which, in addition to the control function in the roll channel, perform the stabilization function in the transverse channels. Performing ailerons with an area of less than 0.3 rudder area will not allow for a stable rocket flight and for effective control in the roll channel will require a larger angle of rudder deflection, which will lead to increased resistance and reduced range. The implementation of ailerons with an area of more than 0.5 rudder is undesirable, as it will make the rocket overly stable, and therefore poorly controlled.

The execution of the rudders fixed on a horizontally located shaft mechanically connected with the steering gear, and the ailerons mounted on the shafts, which in turn are mechanically connected, for example, using a parallelogram mechanism, with a single aileron drive, allows to increase the payload mass (while maintaining the total rocket weight) by reducing the number of drives used in the rocket. Traditionally, for the simultaneous control of a rocket in several channels, four rudders are required, each of which has a separate drive. This is due to the fact that with simultaneous control in different channels, each of the rudders has an individual deviation angle, which may not coincide with the neighboring rudders either in magnitude or direction. The separation of control in the pitch channel to the rudders in front of the center of mass of the rocket, and in the roll channel to the ailerons behind the center of mass of the rocket, allowed reducing the number of drives to two, and releasing the released mass to increase the payload, and, consequently, to increase the combat effectiveness.

The implementation of the wings on the rocket body, installed at a distance from the center of mass no more than b = 4d, allows for a stable flight of the rocket to the maximum range. The installation of wings on a rocket is most effective in the region of the center of mass, but this is not always possible, either due to any layout limitations or due to the fact that due to fuel burn-out during movement along the trajectory of the rocket, the position of the center of mass is constantly changing. The displacement of the wings relative to the center of mass leads to the occurrence of a tilting or stabilizing moment. The location of the wings at a distance from the center of mass of more than b = 4d is unacceptable, since it leads to the fact that the rocket becomes either substantially statically unstable, or vice versa is excessively stable. In both cases, it is necessary either to increase the size of the controls, or to increase the angle of deviation of the rudders during the flight, which invariably leads to an increase in aerodynamic drag and a decrease in the flight range.

The implementation of the bearing planes of the wings with an offset of c = (0.03 ... 0.15) d in antiphase to the direction of installation of the turbine blades of the turbojet engine allows to compensate for the torque from the turbine of the turbojet engine, thereby reducing the required aileron deflection angles in the roll channel. When installing wings without a relative displacement of their bearing planes on a rocket with a turbojet engine, there is a need to constantly fend off the torque transmitted to the rocket from a turbine rotating at high speed. For this, it is necessary to command the ailerons during the entire flight of the rocket, which leads to increased energy consumption on board the rocket and increased load on the steering gear, as well as an increase in aerodynamic drag. The installation of wings with a relative displacement of their bearing planes leads to the creation of an aerodynamic moment of heel, which tends to bring the rocket into a plane of symmetry passing through the end chords of the wings and the longitudinal axis of the rocket. The offset of the bearing planes of the wings in antiphase to the direction of installation of the turbine blades of the turbojet engine allows you to generate a moment directed opposite to the moment from the rotation of the turbine. A decrease in the relative displacement of the wings by less than 0.03 d will not create any significant stabilizing moment in the roll channel, and, therefore, does not compensate for the moment from the turbine. An increase in the relative displacement of the wings by more than 0.15d, on the contrary, will form a very large aerodynamic moment, which will exceed the moment from the turbine and which will need to be compensated by the deviation of the ailerons, as a result of which the achieved effect is lost.

Brief Description of the Drawings

The essence of the utility model is illustrated by drawings, where:

in FIG. 1 shows a general view of a guided missile;

in FIG. 2 - steering block;

in FIG. 3 - block ailerons;

in FIG. 4 shows the relative position of the wings;

in FIG. 5 shows a turbine of a turbojet engine.

Utility Model Implementation

Guided missile consists of a housing 1, trapezoidal rudders 2, mounted at a distance " a " from the center of mass 3, ailerons 4, wings 5, mounted at a distance "b" from the center of mass 3 with the offset of the bearing planes relative to each other by a distance of "s" in antiphase to the installation direction of the blades 6 of the turbine 13 of the turbojet engine 7. In this case, the rudders 2 are mounted on a shaft 8, mechanically connected to the drive of the rudders 9, and the ailerons 4 are mounted on shafts 10, mechanically connected to a parallelogram mechanism 11, which in turn is connected with water ailerons 12.

The proposed guided missile operates as follows. After the start, acceleration to the cruise speed and the opening 2 rudders, wings, ailerons 4 and 5 missile enters the flight mode of the turbojet thrust 7. The optimum ratio characteristics of lift and drag rudders realized during installation 2 at a distance "a" from the center of mass 3 rockets. The creation of a lifting force on the rudders and the formation of a balancing angle of attack occurs with the help of the rudder drive 9, which, making translational movements and being mechanically connected with the rudder shaft 8, deflects the rudder 2 by a predetermined angle. The teams formed during the flight are worked out by ailerons 4 located behind the center of mass of 3 missiles and made in the form of four trapezoidal plates. The area of each of the ailerons 4 is 0.3 ... 0.5 of the area of the steering wheel 2, which allows you to provide a margin of stability necessary for the normal flight of the rocket. The ailerons 4 mounted on the shafts 10 are driven by an aileron drive 12, which rotates and mechanically connected to the shafts 10 by a parallelogram mechanism 11 deflects the ailerons 4 by a predetermined angle. The wings 5 mounted on the housing 1 create a lifting force that provides compensation for the weight of the rocket when moving along the trajectory. The removal of the wings 5 from the center of mass 3 does not exceed the value of "b", which allows you not to violate the stability of the rocket. The location of the wings 5 with the offset of the bearing planes relative to each other by a distance of "c" in antiphase to the installation direction of the blades 6 of the turbine 13 of the turbojet engine 7 allows you to compensate for the moment induced by the turbine 13 in the roll channel.

The implementation of the aerodynamic executive controls and wings on the guided missile body according to the indicated ratios make it possible to ensure stable movement along the entire flight path with optimal aerodynamic characteristics. Reducing the required number of steering drives can increase the mass of the payload while maintaining the total weight of the rocket. These circumstances lead to an increase in flight range and increase combat effectiveness.

Based on the proposed utility model, design documentation has been developed.

Claims (1)

Guided missile containing a housing, a turbojet engine, wings, aerodynamic executive controls, consisting of rudders and ailerons, and an actuator drive, characterized in that the rudders are installed in front of the center of mass of the rocket at a distance of a = (5 ... 8) d, where d is the caliber of the rocket, and made in the form of two trapezoidal plates mounted on a horizontally located shaft mechanically connected to the steering gear, and the ailerons are located behind the center of mass of the rocket, made in the form of four trapezoidal plates, the area of each of which is 0.3 ... 0.5 of the area of the steering wheel, and mounted on shafts, which in turn are mechanically connected, for example, using a parallelogram mechanism, with a single aileron drive, while the wings on the rocket body are mounted at a distance from the center of mass no more than b = 4d with the displacement of the bearing planes relative to each other by c = (0.03 ... 0.15) d in antiphase to the direction of installation of the turbine blades of the turbojet engine.

Images