Method of controlling rocket flight during flight tests
FIELD: physics; control.
SUBSTANCE: invention relates to rocket engineering and can be used to control rocket flight during flight tests. The method includes constantly inspecting, during the entire period of time from mounting the rocket on the launching pad until launching the rocket, using an on-board radar system for remote probing the Earth, the standard and predicted destruction sites of the rocket as a result of possible accidental change in the flight trajectory; detecting, at both sites, the appearance of unauthorised objects whose existence is endangered during self-destruction of the rocket; detecting and identifying the unauthorised objects; simultaneously entering into the programmed flight control system a command to delay the self-destruction; transmitting a command to delay self-destruction of the rocket or guiding the rocket to a safe place if, at the time of launching the rocket, the unauthorised objects are still located at one of the rocket destruction sites; launching the rocket; determining current coordinates and motion parameters of the rocket; calculating the probable trajectory; generating and transmitting to the rocket commands to change the flight trajectory; constantly transmitting to the command centre data on the state of the environment on the route of test flights; predicting possible accidental changes in the flight trajectory which lead to contamination of the Earth's surface, water bodies and air; transmitting to the rocket commands to either continue flight towards the target or deviate from the trajectory and destroy the rocket in an area with minimal damage to the environment.
EFFECT: invention ensures safety for unauthorised objects located at a predicted rocket destruction site.
The invention relates to methods of control of the spatial position of an object, and more specifically, to methods for flight control of the aircraft (LA), especially when testing, and can be used in flight tests of objects such as missiles of all types and several other LA.
Known methods [EP 432902, CL F41G 7/00,1991 and EP 435589, CL F41G 7/20, 1991], in which flight control produce missiles on launchers (PU), using the system, on which you enter information about the destination, and depending on its condition correlated flight path. However, these methods do not take into account the condition of the route of flight that could significantly affect the change in flight path, and therefore these methods are not appropriate to use when testing missiles.
Known methods [US 5071087, CL F41G 7/22, 1991 and DE 3402190, CL F41G 7/22, 1985], in which the launch and flight control is made in accordance with the program of tactical software generated ground-based computing system, which is connected with the block of program memory located in the rocket.
However, in these methods, the flight control is carried out according to the predetermined program, and the system does not have the option of changing the flight situation in case of an abnormal deviation from a predetermined path, and therefore this method is not to�sufficiently effective for use in missile tests.
The closest in technical essence is a method of controlling the flight of missiles in flight tests [RU 2114374, CL F41G 7/30,1996], which includes the determination of the current coordinates and motion parameters of the rocket, calculate the likely trajectory, formation and transfer of missile command for changing the flight trajectory and a constant transmission to the command post of data about the state of the environment on the route of flight tests, the prediction of possible abnormal changes in flight paths resulting in the pollution of the earth's surface, water and air, the transfer of missile command or the continuation of the flight to the target, or deviation from the trajectory and the destruction of missiles in the area with minimal damage to the environment
This method allows to some extent to ensure environmental safety during test flights of missiles, but only under the condition that the projected elimination of the missiles will not be any unauthorized objects, such as people or a herd of animals, happened to be in this place.
The objective of the claimed solution is the security of unauthorized objects in the projected elimination of the rocket.
The problem is solved in that in the known method of controlling the flight of missiles in flight tests, including the definition of current to�of coordinates and motion parameters of the rocket, the calculation of the probable trajectory generation and transfer for the rocket teams to change trajectory and a constant transmission to the command post of data about the state of the environment on the route of flight tests, the prediction of possible abnormal changes in flight paths resulting in the pollution of the earth's surface, water and air, the transfer of missile command or the continuation of the flight to the target, or the deviation from the trajectory and the destruction of missiles in the area with minimal damage to the environment, with the on-Board radar remote sensing(RS) regular and predictable places the destruction of the rocket due to potential abnormal changes in the trajectory of constantly examined during the entire period of time from the placement of the missiles in the launcher before its start, register in both places, the appearance of objects whose existence is in danger if the self-destruction of the rocket, fix them, identify and identify those objects, register them, simultaneously injected into a programmable system flight command delay self-destruct the moment, and further, if by the time of the launch of unauthorized objects will still be in one of the places the elimination of missiles, include command delay self-destruct the missiles or drain it in a secure� place.
The comparison with the known method of the claimed solution showed that the technology for flight control rocket is supplemented by observations of complex remote sensing for the projected elimination of the rocket, and programmable system flight team entered the elimination of deferred missiles, that allows to judge about the criterion of "novelty."
The method is industrially applicable and developed technical equipment meets the criterion of inventive step, since they do not explicitly follow from the prior art.
In this latter does not identify any transformations, characterized by distinctive essential features that are known to achieve the specified technical result.
The invention is illustrated by drawings, where Fig. 1 - algorithm of the flight control of the rocket during emergency situations during the flight of the missile or where the elimination of missiles, and Fig. 2 - scheme of the method in predicting abnormal situation, change the trajectory and prognosis of possible changes of a place of elimination of the missile of Fig. 3-scheme of the method when the area of the elimination of missiles unauthorized objects.
The invention consists in the following.
When testing in case of abnormal deviations from the flight path of the missile detachable part of the drive (from�open with the remnants of toxic components of rocket fuels jettison fairings can get to that area, and their fall may cause irreparable ecological damage to the environment. Meteorological conditions at the site of the explosion can stay like that toxic substances released during flight of the missile, will be distributed in areas that are vulnerable from an ecological point of view. In the known methods of control of flight, intended for flight control of missiles, to take into account such a situation is not necessary, but when testing is necessary, as in cases of various non-standard deviations from the trajectory may be a significant pollution that could be reduced significantly, if the test flight will be carried out taking into account the environmental condition of the flight path and at the destination. Introduction data on the state of the environment on the flight path and at the destination of the missiles to the command post flight control and continuous forecasting of the situation on the trajectory and destination allow you to change the trajectory of the rocket, thus ensuring environmental safety test flights by destroying missiles in the area with minimal damage to the environment.
However, if the location of the destruction of the missiles there may be unauthorized objects, nab�emer people animals, etc. the possibility of the existence of such objects in the place of destruction of the rocket imposes quite severe restrictions on the choice of routes run.
Almost any emergency situation develops for some time, when the rocket is partially preserves controllability, and means Board control system if necessary to get the point of dropping objects from unauthorized. As control actions in the event of an emergency can be taken depending on the current position of the rocket unauthorized location of objects and the prediction results of the health authorities, the value of traction control, the angles of spatial orientation of the thrust control relative to the associated coordinate system of the rocket and the time of an emergency stop control.
To detect unauthorized objects it is necessary to launch the missile. Information about the status of the elimination of the rocket can be obtained with the on-Board radar remote sensing of the Earth from an aircraft during the entire period of time from the installation of the missiles in the launcher before its start.
The coordinates of unauthorized objects in the field of liquidation of the rocket is recorded in both places the emergence of unauthorized objects, the existence of Coto�'s in danger when you self-destruct the missiles fix them, identify and identify these objects.
To ensure safety during testing of missiles available in the emergency circuit to include a forecast of the situation on the route of flight and in the place where the missile and/or its steps, the coordinates of unauthorized objects, the coordinates of unauthorized moving of objects and prognosis of unauthorized coordinates of moving objects
To implement this can be further highlighted in the flight control loop delays the elimination of the missile to change the trajectory of its flight and the place of liquidation.
The method is as follows.
Prior to testing with the aircraft 1 (Fig. 1) throughout the period from the placement of the missiles in the launcher to start by remote sensing 8 detect unauthorized objects projected in the place where the missile 2 in the case of its abnormal behavior or regular place of liquidation, upon detection of unauthorized objects are projected coordinates their movements 9.
During this period, it is predicted the function of the body of the flight management system 3 and predicts the further impact of abnormal behaviour management systems on the flight path 4 and the change from a fall of emergency items 5. When tested in the case of non-standard�Togo deviations from the flight path of the missile detachable parts carrier (stage with the remnants of toxic components of rocket fuels jettison fairings can get into an area where a fall may cause irreparable ecological damage to the environment 6. The forecast of meteorological conditions and input data on the state of the environment on the flight path and in the place of destruction of the rocket 7 allows to predict the situation on the route of flight and in the place where the missile and/or its steps 10 and to determine the control interface, for example, introduction to programmable flight control system command delay self-destruct the moment 11, the duration of which can be calculated by one of the methods proposed by Gevarter [Gevarter. Analytical evaluation strategy pre-launch. "The issues of missile technology" 4 (184) 1970. Publishing house "WORLD"].
If at the time of the launch of unauthorized objects will still be in one of the places the elimination of missiles, include the command delay self-destruct the rocket 2 or divert it to a safe place.
Examples of specific use.
An example in the event of an emergency.
Happened launch point O in Fig. 2. By means of Earth remote sensing (ERS) satellite watching the entire track 13 of the missile and in the exclusion zone 14 and zone 15 for the elimination of the appearance of unauthorized objects.
On 10-th second of the flight of the rocket p�Ozola is an emergency situation at the point 13, which led to the deviation of the missile 1° to the North. This led to the change of a trajectory of the missiles.
Forecast the impact of system management (SU) on the trajectory of the rocket indicates that the change trajectory means SU is not possible.
The point forecast of a fall of emergency products showed the new trajectory of the rocket 17, which lies outside the zones of alienation 14.
The decision on liquidation of rockets with minimal environmental risk.
Projected coordinates unauthorized objects on the new track of the missile and determines the location on the new route of flight in which the destruction of the missiles will result in minimal environmental losses, taking into account static and driving the coordinates of unauthorized objects.
The operator, having predicted the situation, gives the command to eliminate the missiles.
The Outlook for the elimination of missiles at point 15 revealed the possibility of damage to unauthorized objects in the zone 16. Is determined by the length of the delay the elimination of the rockets with 15 needed for missile out of range unauthorized objects on the new route 17 and change of place the elimination of 18. After this command is given to the withdrawal of the degrees of protection of the controller and is undermining the rockets.>
Example in case of occurrence in the elimination of missiles unauthorized objects.
Happened launch point O (Fig. 3). By means of Earth remote sensing (ERS) satellite watching the entire route 19 missile on the subject of unauthorized objects.
On 15-th second of the flight of the rocket RS showed the presence of unauthorized moving of the object 22 in the kill zone 21.
The forecast of the impact of SU on the trajectory of the rocket indicates that the change of trajectory is possible by means of an emergency stop of the engine (AWD).
The forecast of the point of impact of the product showed a possible new damage area of the object outside of the exclusion zone 21.
The decision to change the trajectory of the rocket using the AED.
Projected coordinates unauthorized objects on the new highway 23 missile and the determined new location of the rocket with minimal environmental losses, taking into account static and driving the coordinates of unauthorized objects.
The operator, having predicted the situation, gives the command to the AWD.
Is formed with a delay of 10 issuing commands AWD rocket. After this command is given to the withdrawal of the degrees of protection of the controller and is AWD.
The above examples show that the claimed solution of the corresponding�match the criterion of "industrial applicability".
A method of controlling a missile in flight tests, including determination of the current coordinates and motion parameters of the rocket, calculate the likely trajectory, formation and transfer of missile command for changing the flight trajectory and a constant transmission to the command post of data about the state of the environment on the route of flight tests, the prediction of possible abnormal changes in flight paths resulting in the pollution of the earth's surface, water and air, the transfer of missile command or the continuation of the flight to the target, or the deviation from the trajectory and the destruction of missiles in the area with minimal damage to the environment, wherein what with the on-Board radar remote sensing of regular and predictable places the destruction of the rocket due to potential abnormal changes in the trajectory of constantly examined during the entire period of time from the installation of the missiles in the launcher before its start, register in both places, the emergence of unauthorized objects whose existence is in danger if the self-destruction of the rocket, fix them, detect and identify unauthorized objects simultaneously injected into a software system for the flight control team for the postponement of time of self-destruction and further, if to moments�at the launch of unauthorized objects will still be in one of the places the elimination of missiles, include command delay self-destruct the missiles or divert it to a safe place.
SUBSTANCE: in the method of linearised signal shaping, the rotation period of missile is divided into time intervals on the missile rotating by bank angle, their durations are measured and stored in a certain way. Signal lineariser comprises digital integrator, calculator, tilt signal shaper, step-signal shaper, register and clock-pulse driver. Switchable signal lineariser comprises digital integrator, two calculators, tilt signal shaper, step-signal shaper, tilt sensor, register, control unit, switchboard, clock-pulse driver. In the process of integration, the amplitude of clock pulses is integrated on the missile rotating by bank angle in order to shape the linearised signal, bit-by-bit summing of bitwise binary parallel numbers for each rising edge of clock pulses is carried out. Duration of integration interval is set of corresponding duration of angular spacing of 90 degrees. Then, the integration process is repeated, by changing the discrete quantity in a certain way before starting. Digital integrator comprises series-connected single-bit digital cells. Cell contains D-flip-flop and adder connected in a certain way.
EFFECT: high precision of control command shaping by missile.
11 cl, 7 dwg
FIELD: radio engineering, communication.
SUBSTANCE: adjustment shield simulates forward radio signals and radio signals specularly reflected from the earth, propagating from a missile and a target to a final homing area. The adjustment shield is located in the far zone of a radio direction-finding antenna and comprises laser and infrared emitters. To simulate signals from a missile transponder and signals reflected from a target, the shield is provided with a radio pulse generator with a frequency synthesiser.
EFFECT: high accuracy of adjustment.
FIELD: weapons and ammunition.
SUBSTANCE: tank-type container of warhead includes fairing, thin-walled tank body, front and rear bottoms, filler dispersion and ignition device. Buffer cavity where container weight compensators is made between the fairing and front bottom. Container fairing is designed as reinforced flat bottom with rounded edges attached to the container shell by screw connection. Front bottom of the container has a conical deflector shape. Deflector cone angle is 120-140°. Tank body features centring bulge at a distance of 3.6-3.8 of the calibre from the fairing. Filler dispersion and ignition device is positioned along longitudinal axis of the container and shifted inside the buffer cavity by 0.010-0.015 of its length and attached to a cross-shaped support.
EFFECT: enhanced efficiency of missile or ammunition with such container.
FIELD: weapons and ammunition.
SUBSTANCE: rolling missile is accelerated to cruising speed by means of a detachable solid-fuel launching accelerator, cruising speed is maintained with thrust of a small-size disposable turbo-jet engine, twisted and a mode of rotation about the roll axis is maintained by means of aft stabilisers that are slanted relative to the longitudinal axis and/or a gas-dynamic nozzle on the turbo-jet engine, aerodynamic lifting force is formed in the rotation mode by means of n pairs of small-size foldable wings.
EFFECT: invention allows increasing flight distance of a cruise missile.
FIELD: weapons and ammunition.
SUBSTANCE: shell with gas hanger includes a smooth cylindrical part, in which there is a feed cavity connected to the outer cylindrical surface through feed devices. The feed cavity is intended to create pressure in a carrying gas layer. The feed cavity is filled with substance having high combustion speed. The feed cavity is connected to the rear part of the shell through a thermite wick. The latter is made in the form of a gasket arranged on the inner wall of the feed cavity and pressed to this wall with a spring-loaded shoe.
EFFECT: reduction of the shell size and increase of firing distance.
FIELD: weapons and ammunition.
SUBSTANCE: guided missile is made based on canard configuration. The missile with a single-channel control system and rotating in roll direction. The missile contains a main propulsion system, a steering wheel in one plane and a stabiliser with the location of fixed bearing surfaces by X-shaped pattern relating to the plane of the steering wheel console. At the head part of the housing of the guided missile in a plane perpendicular to the plane of the steering wheel console, the pylons are mounted. The fixed consoles of the pylons in a transverse plane are located at an angle of 45-60 degrees relative the consoles of the stabiliser. The consoles of the pylon on the geometric shape in the plan are made like consoles of the steering wheel with the ratio of areas of the pylon and the steering wheel as 0.5-1.0. The ratio of areas of the console of the pylon and the console of the stabiliser are made as 0.05-0.1.
EFFECT: improved control efficiency, improved ballistic and dynamic properties of the missile.
FIELD: weapons and ammunition.
SUBSTANCE: unit of control system of rocket projectile comprises a housing with ogive part, aerodynamic controllers folding-out in flight with actuators and a control unit, mounted on the ogive part. Each controller is equipped with abutment. The abutment is located in front of the front edge of the controller coaxially with the axis of folding-out. The profile of the front part of the abutment is congruent to the profile of the ogive part of the housing. The diameter of the maximum circumscribed circle of the abutments of all the controllers does not exceed the unit gauge. Folding-out axes of the controllers are biased to the axis of the unit relative to its gauge by an amount at least 0.5 of the maximum thickness of the controller at the root chord of its folding-out part.
EFFECT: improvement of accuracy of projectile shooting.
4 cl, 2 dwg
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
FIELD: weapons and ammunition.
SUBSTANCE: performed is topographic control of target indicator and launching facility to the terrain by ground satellite receiver, determined are coordinates of launching facility and location and ephemeris for each space vehicle of satellite positioning system, detected and measured are target coordinates, the coordinates are transmitted to artillery position control station, set is universal computer time in reconnaissanceman's console and artillery position control station, calculated and transmitted are shooting settings to launching facility automatic control unit, performed is missile launching procedure, the missile is launched from transporter-launcher container along the preset ballistic course, the missile is oriented by on-board navigation satellite receiver, when the missile approaches the target it is oriented by laser emitter.
EFFECT: providing higher probability of guided missile hitting the target.
FIELD: weapons and ammunition.
SUBSTANCE: shell is made based on the canard configuration. The shell comprises an air-dynamic steering gear in the front section of the shell housing and aerodynamic control elements - steering wheels with pylons mounted in front of them. The air-intake devices of the air-dynamic steering gear are incorporated in the pylons and made in the form of bi-plane U-shaped plates with converting into the monoplane along the rear edge. In the front edge of the pylon the U-shaped hole is made and the hole in the shell housing is made.
EFFECT: increase in efficiency of the shell operation.
2 cl, 6 dwg
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.
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
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
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.
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.
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