The method of controlling the rocket

 

(57) Abstract:

The invention relates to rocket technology, particularly to a method of missile guidance in the event of an emergency in flight to improve the safety of objects on the ground within the area of potential fall of emergency rocket or its fragments. Technical and economic results of the present invention is the elimination or reduction of additional material and economic losses or victims in the event of a missile in flight emergency. The method of controlling the rocket is that in the case that the controlled parameters of the rocket alarm values or when the missile emergency produce emergency undermining missiles or emergency shutdown of the rocket engines. In-Board computer system management system rocket in advance impose the values of the functionals speed or "timestamp" critical points" of the trajectory, when the accident in which the system control block the execution of disaster timeline on the time required for turning point fall of emergency rockets in the "danger zone", and then produce emergency shutdown of engine or emergency is Oh when the emergency situation in flight to improve the safety of objects on the ground within the area of potential fall of emergency rocket or its fragments.

Known way to control the missile in flight, namely, that in the case of achieving controlled by the values of the parameters of the emergency or the occurrence of non-explosive rocket emergency, produce emergency shutdown of engine (AWD) or emergency undermining missiles (APR) (see, for example, CT, N22, 1967, pages 12 and 13. On the security service of the Eastern polygon USA, producing emergency shutdown of the engine in flight or undermining of the rocket when the rocket emergency. CT N39, 1966 , page 1 and CT # 46, 1966, page 1. The undermining of emergency missiles Minuteman" system of self-destruction or by command from the Earth).

The disadvantage of this method of missile guidance in an emergency situation is the risk of causing additional damage emergency rocket terrestrial objects. As in case of emergency failure of the rocket when it is being in a "Critical point" of the trajectory, i.e. at the point when the termination of a flight in which the command "AWD" or "APR" emergency rocket or its fragments may fall into the "danger zone" (e.g., town, the military-industrial object, foreign territory or friend who is creating a method of missile guidance, at which eliminates or at least reduces the disadvantages of the known method, i.e., the possibility of achieving positive technical and economic results due to the elimination or reduction of additional material and economic losses or victims in the event of a missile in flight emergency.

The solution is achieved in that in the method of controlling the missile control system with on-Board computing system, wherein in the case that the controlled parameters of the rocket alarm values or when the missile emergency make emergency off rocket engines or emergency undermining missiles, in-Board computer system management system rocket in advance impose the values of the functionals speed or timestamp critical points in the flight path of the rocket, when the accident in which the system control block the execution of disaster timeline on the time required for withdrawal of the proposed point of falling rockets in the danger zone, then using the emergency cyclogram produce emergency shutdown of engine or emergency undermining missiles.

That is, when the receiving system is EMA control rocket introduces a delay command performance "AWD" or "APR" at the time, necessary to move the point of fall of the emergency rocket out of the "danger zone".

The proposed method can be organized in the following way. In-Board computer system management system rocket in advance impose the values of the functionals speed or timestamp "critical points" of the trajectory. The control system in case of emergency failure of the rocket blocks the execution of the emergency program to the time required for migration emergency rocket "danger zone". I.e., performs a delayed execution of the command "AWD" or "APR" on the time required for turning point fall of emergency rocket or its fragments from the "danger zone", and the emergency shutdown of engine or emergency undermining missiles produced after the release of "danger zone".

Implementation of the proposed control method is possible, because after the occurrence of non-explosive emergency (AU) in the majority of accidents (more than 90% of all speakers) rocket continues to set the speed in the course of time, even up to tens of seconds. Naturally, when the explosive nature of the failure, which according to statistics is less than 10% of all accidents missiles, the implementation of the present invention to improve safety is unacceptable.

FPIC is possible controllable parameters of the rocket alarm values or when the missile emergency make emergency off rocket engines or emergency undermining missiles, characterized in that in-Board computer system management system rocket in advance impose the values of the functionals speed or timestamp critical points in the flight path of the rocket, when the accident in which the system control block the execution of disaster timeline on the time required for withdrawal of the proposed point of falling rockets in the danger zone, then use the emergency cyclogram produce emergency shutdown of engine or emergency undermining missiles.

 

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Guided missile // 2244897

FIELD: armament, in particular, guided missiles.

SUBSTANCE: the guided missile has a body with on-board systems, frame with drive shafts made with journals, with air vanes hinge-installed in their end face grooves for folding in the body and fixation in the unfolded position. The guided missile is provided with control-surface deflection transducers and a printed circuit board secured through an insulator on the front end face of the frame and connected by means of a bundled conductor to the on-board systems of the guided missile.

EFFECT: reduced spread in the value of the sweep angle of the air vanes in the process of manufacture.

2 dwg

FIELD: guided missiles, in particular, their control actuators.

SUBSTANCE: the control surfaces are connected by means of a half-axle, in which a central hole is made along the missile longitudinal axis, alkane holes are made perpendicularly to the longitudinal axis for installation of the axles of the control surfaces. The half-axle has components for coupling to the actuation cylinders.

EFFECT: enhanced efficiency of armor-piercing capacity of the missile.

4 cl, 2 dwg

FIELD: defense engineering; production of guided missiles and projectiles.

SUBSTANCE: the invention is pertinent to the field of defense engineering, in particular, to production of guided missiles and projectiles. The technical result of the invention is simplification of testing, increased accuracy, decreased labor input and cost of the testing. The method of testing of a developed torque of an electro-pneumatic steering gear of guided missiles and projectiles is based on a torque measurement of the steering gear with the help of a reference load and an easily removable balance lever put on a rudder. Then the steering gear with a detector of the rudders motion are installed on a customizing table. The detector of the rudders motion is made in the form of a separate contact or non-contact sensor or for the purpose they use an available in the steering gear as a feedback gauge - the gauge of a piston linear motion or a gauge of angular motion of rudders. The rudders turning at a maximum angle in one side is made using application of a torque of the corresponding sign by a reference load with the weight on a definite length of an arm of a placement of the load on the lever in respect to the axis of rotation of the rudders equal to a developed torque of the steering gear at the given pressure of the feeding. Switch on the power of the gauge, measure the voltage on the gauge output by a voltmeter, remove a torque by removal of the reference load, turn the rudders at a maximum angle in other side using application of a torque of an opposite sign equal to a maximum torque of a hinged load on the rudders in respect to the rudders turning angle and an angle of attack of a missile or a projectile. Switch on power supply of the booster of the steering gear and feed onto an input of the steering gear compressed air under pressure of P =1.5Pgvn., feed onto the input of the steering gear a maximum control signal of management corresponding to the motion of the rudders at a maximum angle, measure the voltage on the output of the gauge, which should meet the first given ratio. By a smooth reduction of pressure of the feeding in the pneumo-circuit) of the steering gear and according to reduction of voltage on the output of the gauge determine pressureP

+1
at which the voltage will meet the second given ratio. At that the pressure P+1
should be no more than Pgvn ,remove a pneumatic feeding and the power supply of the booster of the steering gear and switch off the control signal and the power of the gauge. After that using an analogous method they measure voltages and determine the pressure at application of the corresponding torques and a control signal of an opposite sign and determine a developed torque of the steering gear according to the mathematical formula.

EFFECT: the invention ensures simplification of testing, increased accuracy, decreased labor input and cost of the testing.

5 cl, 1 dwg

FIELD: methods for missile radar guidance on air targets in radar guidance systems.

SUBSTANCE: guidance of missiles on an air target moving in the direction to the protected object, including the detection of the air target, evaluation of the parameters of its trajectory, missile launching, missile-to-target approach to the distance of actuation of the missile warhead blasting device, correction of the missile heading in the process of approach, blasting of the charge of the missile warhead at a distance from the protected object not less than the preset one, is accomplished in the trajectory coinciding, in the terminal leg with the predicted missile trajectory. In the terminal leg the speed of the missile is set lower than that of the air target. The result is also attained by the fact that the guidance of the missile on the air target moving in the direction to the protected object, including the detection of the air target, evaluation of the parameters of its trajectory, missile launching, missile-to-target approach to the distance of actuation of the missile warhead blasting device, correction of the missile heading in the process of approach, blasting of the charge of the missile warhead at a distance from the protected object not less than the preset one, is accomplished in the trajectory of the missile displaced in the direction to the protected object. In the terminal leg the speed of the missile is set higher than that of the air target. The result is also attained by the fact that the radar set for guidance of the missile on the air target has a missile control point and an on-board radar equipment. The missile control point includes a detection radar, a guidance radar, a computer, a servo drive, a transmitting device and an antenna device, the missile on-board equipment has a missile antenna, radio-receiving device of the missile guidance channel, actuating device, selector switch, transmitting device, radio-receiving device of the detection channel, computer.

EFFECT: reduced dynamic errors of missile guidance on an air target, and enhanced time of radio contact of the missile warhead fuse: with the air target.

5 cl, 6 dwg

Control actuator // 2254267

FIELD: flying vehicle control systems, mainly small-sized guided projectiles.

SUBSTANCE: proposed control actuator includes adder whose first input is used as actuator input and correcting filter connected to adder output. Actuator includes also relay element, power amplifier and servo unit connected in series. Servo unit output is used as actuator output and is connected with second input of adder through feedback element. Circuit is additionally provided with harmonic signal generator and second adder. First input of adder is connected with correcting filter output and second input is connected with output of harmonic signal generator and output is connected with relay element input. Such arrangement makes it possible to change and to select parameters of correcting filter and gain factor of circuit.

EFFECT: enhanced operational accuracy and noise immunity.

1 dwg

FIELD: aeronautical engineering; control systems of unmanned flying vehicles provided with target coordinator and passive homing system.

SUBSTANCE: proposed method consists in selection of tracking point inside target loop and measurement of parameters of motion of flying vehicle relative to this point. During autonomous flight of flying vehicle, its selective guidance is ensured by forming limited tracking zone around selected tracking point with many threshold magnitudes and respective time intervals. When tracking point gets beyond these thresholds, its position is restored by forced correction. In case tracking within this zone is unstable after several correction cycles, guidance in target loop is performed instead of selective guidance by making several correction cycles of tracking point. In case tracking is unstable again, target is considered to be lost. Homing is replaced by forced motion of flying vehicle in way of reference tracking point over rectilinear trajectory and fixing the axis of target coordinator in direction towards selected tracking point. Attempts are made for locking-on new tracking point inside target loop. In case of successful attempt, homing of flying vehicle to new tracking point is performed. In case of unstable tracking, target lock-on is considered to absent and fixed position of target coordinator axis is restored positively. As target range reduces, approximate linear deviation of tracking point is maintained constant inside target loop.

EFFECT: enhanced efficiency of flying vehicle due to selective guidance and retaining controllability in case of loss of target.

6 cl, 6 dwg

FIELD: defense equipment, in particular, projectiles and missiles.

SUBSTANCE: the preliminarily cooled to the maximum preset negative temperature of the control drive is checked in a thermal vacuum chamber, when it is fed with air of a raised humidity. After the check a technical inspection of the drive (assemblies and parts) is carried out and the quality of coatings and insulation of the current-conducting circuits, strength, stability and serviceability are estimated. According to the results of the comparative estimate of the obtained values of the measured parameters with the preset ones in the selected conditions and technical inspection, a decision is taken on the quality of functioning of the air-dynamic control actuator cooled to the negative temperature at a compressed aid of a raised humidity. The stand for quality control of functioning of the air-dynamic control actuator of guided missile is provided with a thermal vacuum chamber with a vacuum pump, humidity chamber and a pneumatic cock with a connecting hose. The outlet of the humidity chamber is connected to the pneumatic cock and connecting hose to the inlet of the receiver. The base with the unit fastened on it and the receiver with the measuring pressure gauge and the relief valve are installed in the thermal vacuum chamber.

EFFECT: expanded potentialities of use of the stand and enhanced quality of control of functioning of air-dynamic control actuators and autopilots of guided projectiles and missiles.

2 cl, 1 dwg

FIELD: armament, in particularly, rocketry, applicable in development of missile-weapon complexes with beam-rider guidance systems, in which the missile flight trajectory, for example, close to and parallel with the ground surface, or water surface.

SUBSTANCE: from the moment of start a program-changed pitch command is formed on the missile, and at an entry of the missile in the beam area control is effected by the TV guidance system. In the horizontal plane the directions of the missile start line and beam are matched with the zero value of command messages. In the vertical plane the direction of the missile start line is adjusted in angle above the beam direction with the zero values of the command messages, and the beam-rider guidance system is controlled by the guidance system from the moment of getting of the missile to the beam area with zero values of command messages in the vertical plane, the missile is twisted in bank angle. Described are two modifications of the complex of the missile telecontrolled in beam. The first modification has a missile that includes components of missile electromechanical joining, autopilot, and a series-connected receiver and a coordinate separation unit, as well as a control station that includes a sight-guidance instrument and a start control device, which is connected via the device of the electromechanical joining of the launcher to the components of the missile electromechanical joining, the receiver is coupled by electromagnetic radiation to the sight-guidance instrument; installed on the missile are a delay unit and series-connected starting pulse shaper, variable command shaper and an adder, the heading and pitch outputs of the coordinates separation unit are connected, respectively, to the first and second inputs of the delay unit, the heading output of the delay unit is connected to the first input of the autopilot, the pitch output of the delay unit is connected to the second input of the adder, the adder output is connected to the second input of the autopilot, and the third input of the delay unit is connected to the output of the starting pulse shape, whose input is connected to the components of the missile electromechanical joining. The second modification differs from the first one by the fact, that the receiver output is connected to the first input of the delay unit, whose output is connected to the input of the coordinates separation unit, the pitch output of the coordinates separation unit is connected to the output of the starting pulse shaper, whose input is connected to the components of the missile electromechanical joining.

EFFECT: enhanced efficiency.

4 cl, 6 dwg

FIELD: armament, in particular, rocketry spinning in bank angle, applicable in missile guidance systems, in which beam-rider guidance systems are used, for example.

SUBSTANCE: the electromagnetic radiation from the control station is converted on the missile into the components of the command signal, corrected and a command signal is formed from the corrected values. A bank signal is generated on the missile in the form of electric pulses, whose durations are formed to be equal in value to angular intervals, formed at missile bank spinning, the duration of each pulse is transformed into a binary number, whose value corrects the values of the components of the command signal. Introduction in the missile guidance system of a connected-in-series roll-angle pick-off and a "duration-code" converter has enhanced the reliability due to the use of the missile of roll rate for correction of the value of the command signal on the missile.

EFFECT: enhanced reliability due to the use of the missile roll rate as a regulating value, that corrects the command signal on the rolling missile.

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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