Guided projectile and the steering machine for him

 

(57) Abstract:

The invention relates to the field of managed artillery ammunition. Guided projectile includes a housing, a cruciform located aerodynamic surfaces, the frame communicated with the channels of the gas pipeline gas accumulator pressure, gas gearbox and four steering machines, kinematically connected with drive shafts rudders. The projectile is equipped with actuators return rudder to zero relative to its longitudinal axis position, kinematically connected with drive shafts rudders. Steering of the machine is made in the form of gas engines unilateral actions and pairs are located on two sides with respect to the axes of the drive shafts, which are mounted in radial holes of the frame and the axles, in the end grooves which for folding into the housing pivotally mounted handlebars. Each steering gear connected to the drive shaft steering shaft one end of which is rigidly connected with the side lever of the drive shaft, and the other pivotally mounted in the stem of the steering engine. In the gas line between the gas accumulator pressure and gas gearbox mounted gas gearbox accurate reduction. Tarnovo electromagnet. Gas engine made in the form of the power of the single-action cylinder and provided with a drive return the piston to its original position. This drive is placed in the cylinder from the piston rod and is made in the form attached in the cylinder glass restrictive washer, placed in a glass of spring and cooperating with the ledge of a piston rod movable washer located between the spring and the bounding puck. Ball lock made of sequentially installed in the power cylinder from the side of the working end of the piston and the fixed housing of the electromagnet thrust washer, input inductor, the guide sleeve slotted hole, which features a ball and output inductor. The input inductor is made in the form of a washer with a mounting seat for a ball, formed by a hollow axial bore that communicates through a diametrical hole with the input of the radial holes of the power cylinder, and end-to-end parallel to the axis of the input throttle openings. The output inductor is made in the form of a washer with a mounting seat for a ball formed through an axial bore in which is located a plunger armature of an electromagnet, and an output cavity formed end depressed outside the RA. The input choke, guide Bush and the output choke sealed in the power cylinder sealing sleeves. The gap between the outside end of the piston and limiting washer is made is not a large gap between its working face and thrust washer. The invention allows to reduce the dimensions and weight of the control compartment of the projectile due to the implementation of the three-position control law. 2 S. p. f-crystals, 5 Il.

The invention relates to the field of rocketry and can be used in managed shells (CA), mostly artillery CONDITION, with large (up to several tens of kilometers) range.

A device of the flight control [1] missiles with crosswise arranged aerodynamic rudders, which are mounted on the axes of folding in the frame of the rocket body. In this device, each wheel is driven by its steering machine, so the area of rational use of the device is stabilized in roll rockets and shells.

The steering machine controller flight [1] includes a motor, an output shaft which is connected with the driving bevel gear and Cam mechanism. However, from the point of view eseistika. For rotating projectiles necessary steering actuators with higher performance, and therefore, more power. The duration of the control surface actuators US with a flight range of up to several tens of kilometers is calculated by the minute. Under these conditions, the advantage of the gas actuator, due to the smaller volume and weight (taking into account the size and weight of on-Board power source drive), per unit of power, is particularly significant factor.

Closest to the claimed CONDITION on essential features guided missile realizing the control method [2]. The missile includes a housing, a cruciform located aerodynamic surfaces, the frame placed on it the gas the steering actuator. Steering linkage consists of reported channels gas pipeline gas accumulator pressure, gas gearbox and four actuators, each of which is made in the form of a gas engine is double-acting and kinematically connected with the axis of one of the aerodynamic control surfaces.

The missile has a relay control law, in which each wheel makes continuous oscillatory rotation from lock to lock with the frequency upravlinna at zero team these times are equal. Therefore, the lack relay control law and the implementing steering - presence of a constant flow rate of the working fluid from the gas supply source that the operation of steering US in a few minutes necessitates a corresponding increase in the size and weight of the gas accumulator pressure. While the working fluid in the steering actuator is spent and at zero management team. It is irrational compared with three position control law, when the null command control rudders installed in the middle position, and the flow rate of the working fluid in the steering drive is missing. In addition, rudders missiles when relay control law almost always are in the deflected position, which increases the drag of the rocket.

Each steering machine missiles that implements the control method [2], made in the form of a power cylinder double-acting, controlled gas distribution device, in which a ball check valve communicates with the plunger armature retractable electromagnet. The piston of the power cylinder during the filling of the working fluid, a working cavity occupies the corresponding end position, and at nab, the left actuator. Thus regulation of the flow of the working fluid is ball valve in only one working cavity (larger volume), and the second working cavity (less) constantly filled. The movement of the piston in the direction of adjustable working cavity is carried out when emptying due to the difference of the squares of the working ends of the piston. The need to overcome the resistance forces are constantly filled with the working cavity of a smaller amount makes about three times the difference of the squares of the working ends of the piston, as created when this steering machine force counteracts a force from the side of the filled cavity and the load of aerodynamic wheel. Consequently, a greater volume of the working cavity, through which the flow of the working fluid, also about three times more than required. Therefore, this steering machine with the power cylinder double-acting, relay implements the control law, requires a large flow rate of the working fluid, which increases the dimensions of the source power steering.

Solved by the claimed devices task is the improvement of the overall mass of the performance CONDITION, namely the reduction of the size and weight of the control compartment through the realization of the implemented CONDITION, comprising a housing, a cruciform located aerodynamic surfaces, the frame communicated with the channels of the gas pipeline gas accumulator pressure, gas gearbox and four steering machines, kinematically connected with drive shafts rudders fitted with actuators return rudder to zero relative to its longitudinal axis position, kinematically connected with drive shafts rudders. This steering of the machine is made in the form of gas engines unilateral actions and pairs are located on two sides with respect to the axes of the drive shafts, which are mounted in radial holes of the frame are rigidly connected in pairs by axles and pins, in the end grooves which for folding into the housing pivotally mounted rudders, and side levers, located on the pins. Each steering machine is kinematically connected to the drive shaft steering shaft one end of which is rigidly connected with the side lever, and the other is pivotally mounted in the stem of the steering engine. In the gas line between the gas accumulator pressure and gas gearbox mounted gas gearbox accurate reducing.

In addition, the solution of this problem is achieved in that in which the needle is retractable anchors electromagnet, gas engine made in the form of the power of the single-action cylinder and provided with a drive return the piston to its original position. This drive is placed in the power cylinder from the piston rod and in the form stipulated in the power cylinder glass restrictive washer, placed in a glass of spring and cooperating with the ledge of a piston rod movable washer located between the spring and the bounding puck. Ball lock made of sequentially installed in the power cylinder from the side of the working end of the piston and the fixed housing of the electromagnet thrust washer, input inductor, the guide sleeve slotted hole, which features a ball and output inductor. The input inductor is made in the form of a washer with a mounting seat for a ball, formed by a hollow axial bore that communicates through a diametrical hole with the input of the radial holes of the power cylinder, and end-to-end parallel to the axis of the input throttle openings. The output inductor is made in the form of a washer with a mounting seat for a ball formed through an axial bore in which is located a plunger armature of an electromagnet, and an output cavity formed end podno the power cylinder. The input choke, guide Bush and the output choke sealed in the power cylinder sealing sleeves. The gap between the outside face of the piston and limiting washer is made is not a large gap between its working face and thrust washer.

The design of the inventive device illustrated by drawings, where Fig.1 shows a longitudinal section of the CONDITION; Fig.2 is a view of the frame body from head CONDITION; Fig.3 is a partial section view of the frame along the axis of the drive shafts rudders; Fig.4 is a view of the frame body from the tail CONDITION; Fig.5 is a longitudinal axial section of the steering machine.

In case 1, the claimed CONDITION is fixed (for example, radial screws) frame 2, in the radial holes of which there are four driving shaft 3, is rigidly connected in pairs by the axis 4 by means of pins 5. In the grooves of the pins drive shafts 3 axes 6 folding set of aerodynamic control surfaces 7, drop down through the slots in the housing 1. Axle drive shaft 3 provided with side arms 8.

The front end face of the ring nut 9 is fixed four steering of the machine 10 are located in pairs on two sides relative to the associated drive shafts 3. Each steering machine 10 kinetic and 13 in the side hole of the lever 8, and the other pivotally mounted on the axis 14 in the piston rod 15 of the steering of the machine 10. Thus, steering of the machine 10 kinematically connected in pairs via the drive shaft 3 and axis 4, each steering gear 10 to rotate a pair of aerodynamic rudders 7 only in one direction from zero (middle) position, in which the chord rudders 7 coincides with the longitudinal axis of the MUSTACHE. Moving each pair of wheels 7 in the zero position, actuator return rudders, which in the inventive devices made in the form of springs 16 and is combined with the steering of the machine 10.

In the screw holes of the rear end of the frame 2 fixed gas accumulator pressure 17, gas regulators prior 18 and accurate 19 reduction. Channels gas pipeline: gas accumulator pressure 17 - reducer preliminary reduction 18 - gearbox exact reduction 19 - steering of the machine 10 made in the form of holes 20 in the frame 2, located at different levels on its thickness (Fig.4 holes 20 are conventionally shown as dotted lines). The tightness of the gas pipeline provide threaded plugs 21 of the hole 20. Gas accumulator pressure 17 is actuated pyrotechnic mechanisms the second item which serves as a housing 23, made in the form of a power cylinder gas engine single-acting with the piston 15. From outside of the end face of the piston 15 (from its stem) in the housing 23 posted by actuator return the piston to its original position, consisting of a restrictive washer 24, the movable washer 25, interacting with the ledge of the piston rod 15, the spring 16 and the Cup 26, which restrictive washer 24 and the spring 16 is fixed in the housing 23.

From the opposite end of the body 23 has a gas distribution device in the form of a ball valve, actuated retractable electromagnet 27, the armature 28 which is provided with a plunger 29, interacting with the ball 30. Ball lock consists of a series set thrust washer 31, the input inductor 32, the guide sleeve 33 for the ball 30 and the output inductor 34, a fixed magnet 27 in the housing 23.

The input inductor 32, made in the form of washers, has a seat for the ball 30 formed by a hollow Central bore 35 that communicates through a diametrical hole 36 with inlet holes 37 of the power cylinder, made in the housing 23. In addition, the input inductor 32 has through its parallel to the axis of the holes 38 (Fig.5 while the RA with the working cavity 40 of the power cylinder through the hole in the thrust washer 31.

Guide sleeve 33 is made in the form of a washer with a Central slotted hole, which features a ball 30, and guides which are the edges of the slots.

The output inductor 34 is made in the form of a washer with a Central hole in which is located a plunger 29 of the armature 28 of the electromagnet 27, and an output cavity 41 ball valve, two radial holes 42 with the output apertures 43 of the power cylinder in the housing 23.

The installation location of the input inductor 32, the guide sleeve 33 and the output inductor 34 in the housing 23 is sealed sleeves 44, 45, and 46.

The anchor 28 is preloaded by a spring 47 relative to the pole 48 of the electromagnet 27.

Managed the trajectory of the flight CONDITION begins with the revelation of the aerodynamic control surfaces 7 at the command of the control system. After disclosure of the aerodynamic control surfaces 7 on the signal system control CONDITION is triggered pyrotechnic mechanism start 22 gas accumulator pressure 17 and the gas channels, the gas line enters the gas reducer preliminary reduction of 18, and then into the gas reducer exact reduction 19, the output of which the gas pressure is reduced to the operating pressure of steering gears 10. The three-evanie commands in the control system takes into account the rotation CONDITION: depending on its position along the channel roll steering of the machine 10 in turn trained the team through the course and pitch, thus to rotate the pair of rigidly connected to the steering wheel 7 at the maximum angle +morm(m- the maximum deflection angle of the steering wheel) control command is only served on one of the kinematically connected drive shafts 3 and axis 4 actuators 10. The feed sequence and duration of teams is determined by the control system MOUSTACHE and, in General, is random. When applying the zero team, having single wheels 7 are returned to zero position under the action of one of the drives back wheels to the zero position.

It should be noted that the aerodynamic control surfaces 7 operates normally spring aerodynamic hinge moment, under which the wheels 7 in the position of the aerodynamic equilibrium (in the absence of a steering torque generated by steering machines 10 and springs 16). Therefore, given the same direction of action of the aerodynamic hinge moment and torque generated by the actuator return of the steering wheel 7 in the zero position, the required power of the latter is significantly less required power steering gears 10.

In the General case, the actuators return rudders can be mechanical, gas or electric and have active combined with steering machines 10 and is made on the basis of force of the spring 16. A slight complication of the design of the steering of the machine 10, it helps to improve overall mass MUSTACHE.

When developing a steering drive command if the relay control law implemented in the known device [2], aerodynamic wheel double-moves between stops +mand -m. Associated with the flow of the working fluid mechanical steering of the machine is equal to the product pwpwhere p is the working pressure of the steering engine, a wp- greater volume of the working cavity of the steering engine, in which the control of the flow of the working fluid.

In the present US with three position control when developing equivalent commands aerodynamic control surfaces move the steering of the machine 10 only from the zero position to the +mor tom. Given that the working volume of the gas engine steering of the machine 10 in this case 2 times less have 2 times less mechanical work done by the steering of the machine 10. Respectively 2 times reduces the required mass flow rate of the working fluid of the steering actuator, and hence the required volume of the gas accumulator pressure.

In the kinematic diagram of the inventive MUSTACHE connection of the piston 15 each the si 14 in the piston rod 15 and is rigidly connected with the side lever nuts 12 and 13, provides translational movement of the piston 15 during rotation of the lateral arm 8. In addition, when assembling the MUSTACHE nuts 12 and 13 is set to zero and the extreme angular position of the steering wheel 7. When the zero position of the control pistons 7 15 kinematically connected actuators 10 interact ledges rods with movable washers 25, tucked springs 16 to the bounding washers 24.

The need to introduce an intermediate gas reducer exact reduction 19 in the case of the three-position control due to the higher degree of discretization of the process of consumption of steering gear of the working fluid from the gas accumulator pressure 17, as at zero commands on the steering of the machine 10, the gas flow in the steering actuator is virtually absent (the flow rate of the working fluid through technological gaps by several orders of magnitude less than the flow through the steering of the machine 10). Therefore, sequential stepwise lowering of the gas pressure of the accumulator pressure 17 to the operating pressure of steering gears via two series-connected gas regulators 18 and 19 provides a more accurate reduction, helping to reduce the level of unproductive consumption of the working fluid caused by AZ on channel 20 gas main frame 2 arrives (see Fig.5) in the inlet 37 of the housing 23, diametrically holes 36 and the cavity of the deaf Central hole 35 of the input inductors 32 each steering of the machine 10. In the initial position of the ball 30 ball shutter is pressed on its seat to the input orifice 32 of the plunger 29 of the armature 28 by the force of the preload spring 47 of the electromagnet 27, overlapping the deaf Central hole 35 of the input inductor 32. Thus ball valves seal gas pipeline steering at zero command control steering of the machine 10.

When applying to the electromagnet 27 electrical signal that corresponds to a single command control CONDITION, the armature 28 and its associated plunger 29 is moved to the pole 48, overcoming the spring 47. Under the action of gas pressure in the cavity deaf center hole 35 of the input inductor 32 of the ball 30 is released by the plunger 29 is moved to the landing place of the output inductor 34, blocking its Central hole. For the deaf Central hole in the input inductor 32, the gas enters into the cavity 39 of the ball valve, and out through the channels 38 and through the hole in the thrust washer 31 in the working cavity 40 of the gas engine. Under the action of gas pressure, the piston 15 through concentration Upon termination of the electrical pulse to the electromagnet 27 under the action of the spring 47, the armature 28 and the plunger 29 to move the ball 30 on its seat input inductor 32, again sealing gas pipeline steering at the place of installation of the steering engine. The force of the spring 16, the piston 15 is moved to the stop of the movable washer 25 in the guide washer 24, i.e., returns to its original position. When the gas from the working cavity 40 of the gas engine is discharged into the atmosphere (or built-in with the atmosphere of the cavity compartment control CONDITION) through the hole in the thrust washer 31, the holes 38 of the input inductor 32, the cavity of the ball valve 39, the splined hole of the guide sleeve 33, the gap between the plunger 29 and the surface of the Central hole of the output inductor 34, the output cavity 41 ball valve, radial holes 42 of the output inductor 34, the output of the radial holes 43 of the housing 23 and further through the output channels of the gas pipeline.

The initial position of the piston 15 is movable washer 25, and his stroke - clearance1between restrictive washer 24 and the outside surface of the end face of the piston 15. The possibility of realization of beam switching circuits of the two actuators relative to the axis of the associated drive shafts 3 provides the condition12where2- the gap between the surface of the working end of the piston 15 and the thrust washer 31. While moving the Porsche is Bros gas from the working cavity 40 of the gas engine is the same as that described above.

Thus, the claimed device ensure the implementation of the three-position control CONDITION, in which by reducing the required mass of the working fluid of the steering actuator, and its circuit-design and layout of the control compartment, significantly improved overall mass characteristics MUSTACHE.

Sources of information

1. The control unit flight. French patent 2713330, IPC F 42 B 15/01.

2. The method of controlling the rocket and device for its implementation. U.S. patent 3415466, NCI 244-3.21, 5 IPC F 42 B 15/01.

1. Guided projectile, comprising a housing, a cruciform located aerodynamic surfaces, the frame communicated with the channels of the gas pipeline gas accumulator pressure, gas gearbox and four steering machines, kinematically connected with drive shafts rudders, characterized in that it is equipped with actuators return rudder to zero relative to its longitudinal axis position, kinematically connected with the drive shafts of the steering wheel, with steering of the machine is made in the form of gas engines unilateral actions and pairs are located on two sides with respect to the axes of the drive shafts, which are rigidly connected in pairs by axles, studyware in case pivotally mounted rudders, and side levers, located on the pins, each of the steering machine is kinematically connected to the drive shaft steering shaft one end of which is rigidly connected with the side lever, and the other pivotally mounted in the stock steering the car, and in the gas line between the gas accumulator pressure and gas gearbox mounted gas gearbox accurate reducing.

2. The steering machine, containing a piston gas engine, ball lock, interacting with the plunger armature retractable electromagnet, characterized in that the gas engine is made in the form of a power cylinder single-acting and provided with a drive return the piston to its original position, is placed in the power cylinder from the piston rod and in the form stipulated in the power cylinder glass restrictive washer, placed in a glass of spring and cooperating with the ledge of a piston rod movable washer located between the limiting washer and spring and the ball lock is made of sequentially installed in the power cylinder from the side of the working end of the piston and the fixed housing of the electromagnet thrust washer, input inductor in the form of a washer with a mounting seat for the ball, what tertiary power cylinder, and end-to-end parallel to the axis of the input throttle openings, the guide sleeve slotted hole, which features a ball and output inductor in the form of a washer with a mounting seat for a ball formed through an axial bore in which is placed a plunger armature of an electromagnet, and an output cavity formed end depressed by the electromagnet and reported radial holes with the output of the radial holes of the power cylinder, and the input choke, guide Bush and the output choke sealed in the power cylinder sealing sleeves and the gap between the outside end of the piston and limiting washer is made is not a large gap between its working face and thrust washer.

 

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5 cl

FIELD: armament, in particular, rocketry.

SUBSTANCE: at this method a spatial structure of electromagnetic field is produced at the control station, in which the field parameter is functionally coupled with the coordinates of the respective points of the space. A beam with zero values of the command messages is laid on the target or above the target, and the parameter of the electromagnetic field is measured on the missile, the value of coordinates is determined and the heading and pitch control commands are formed; N devices are positioned in the area of beam propagation, each of the devices transforms the field parameter to the pitch and heading coordinate signals, and then are registered from the missile start, and the position of the missile relative to the target is fixed in the flight trajectory. The process of registration and fixation in time is synchronized according to the value of the registered coordinate signals and fixed missile deviation from the target in heading and pitch, and a conclusion is made on the condition of the beam telecontrol system and its components. The method is realized by the beam telecontrol monitoring system, having a control station, coupled with the missile by electromagnetic radiation, and a telemetering system, use is made of a device for fixation of the missile flight trajectory, and the telemetering system is made in the form of N chains, in each of which connected in series are a receiver and a coordinate separation unit, the heading and pitch outputs of the coordinate separation units from the N chains are connected to a registering device, the receiver from each chain is coupled by an electromagnetic radiation to the control station, and the device fixing the missile flight trajectory is optically coupled with the missile.

EFFECT: a spatial structure of the electromagnetic field is produced at the control station, in which the parameter of the field is functionally coupled with the coordinates of the respective points of the space.

3 cl, 1 dwg

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