Method for approaching of moving object at self-guidance as per information on fact of target localisation
FIELD: measurement equipment.
SUBSTANCE: method is based on use of information on fact of target localisation with a locator, the sensitivity axis of which coincides with direction of speed vector of the object. Trajectory of the object is formed in the form of cycles that begin and end by the fact of target localisation. Inside each cycle an arc-like movement is performed at maximum possible angular speed that is constant in the cycle, the sign of which is changed after achievement of the value of the average angle of advance of the object trajectory relative to a line of sighting, which is calculated for the current cycles as a product of difference of the value of this angle in the previous cycle and increase rate of the inclination angle of the object trajectory in the current cycle relative to the previous one multiplied by a coefficient depending on approach conditions, and a fraction, in the numerator of which there is difference of values of the average angle of advance in the previous cycle and rate of increase of the inclination angle of the object trajectory in the current cycle relative to the previous one, and in the denominator there is a sum of the specified values.
EFFECT: possible approach at opposite self-guidance when linear speed of the target exceeds speed of the object.
The invention relates to the field of automatic control during the approach of a moving object (hereinafter "facility") with another moving object (hereinafter "purpose") in the case of homing using minimal information about the purpose, namely: the fact of coincidence of the linear velocity vector of the object with the line of sight of the target.
A method of homing object using the specified information is the "chase method, which allows control of when homing, using the information from the permanent sight of the goal, i.e. the velocity vector of the object when it is closer to the goal aimed at the target at (V. A. Revkin, "radio-Electronic control systems of rockets and shells", Goskomstat, 1996, p. 1, section 2.3, page 27).
When homing on the "chase method", depending on the conditions of convergence may exist areas on the trajectory of convergence of objects, especially with a head homing, where there are invalid values of misses. Fig.1 shows an example of the oncoming convergence of the object and purpose of the method of the chase, when the speed exceeds the target speed of the object: the target's speed - 35 conventional units (I.(e.), the speed of an object compared with 26.4 in.e.
The target trajectory is the line 1, the trajectory of the object is line 2. Mistake in "chase" in this case greatly exceeds the allowable value, as m�minimum radius of the object in the example is $ 15.e., a slip - 65.e.
The objective of the proposed method is the implementation of a homing object using information about the purpose of the method of the chase, even with a possibly smaller than the target, the linear velocity at the opposite homing.
To solve this problem is proposed to move the object along the trajectory, consisting of arcuate segments for which the object is moving with the greatest possible constant angular velocity ω0. Two arcuate cut together in a loop that begins and ends upon sighting the target, Fig. 2 where:
OA1BCDEF ... - the trajectory of the object when homing;
O1NM - the trajectory of the target;
OO1, DN, FM line-of-sight targets at the moments of "i-1", "i", "i+1", respectively, which are parallel to the lines: OO1|| DD1|| E1E2DN || MM2;
the axis of x0- the reference axis angles of the inertial coordinate system;
the x axis is the sensitive axis of the locator target, it same axis associated with the object coordinate system;
V - linear velocity of the object coincident with the axis of sensitivity of the locator;
V1- the linear velocity of the target;
where R is the radius of the object
∠O1Ox0=∠E2E1x0, ∠NE1x0=∠N1NE1- the angles of inclination of the trajectory volun�the axis relative to the inertial system of coordinates x 0in moments of sight goals;,the values of these angles at the moments of "i-1", "i", respectively;
∠E2E1N=|∠NE1x0-∠E2E1x0|=∠N1NE1wherethe value of ∠M2MF:since DN is parallel to M2M;
,- quantitative increment of the values of the angles of inclination of the trajectory relative to the axis of the inertial system of coordinates x0in current relative to previous cycles at the moment of sighting the target.
The sign of the valuefrom point D, or E1has a positive value iffixed counter-clockwise relative to the line of sight DN (x direction in the associated coordinate system), negative if clockwise. Relative to N - on the contrary.
∠x0B1B, ∠x0E1E - given the angles of inclination of the trajectory of the object relative to the axis of the inertial system of coordinates x0determining the change of sign of the reversal of the object;,- the values of these angular values in cycles and "i";
∠O1OB=∠OO2A1, ∠EDN - average angles of pre-emption, defined�represent the change of sign of the reversal of the object, that is, the average angles of inclination of the trajectory of the object relative to the line of sight after the "i-1"th and "i"-th time instant, respectively, qi-1, qi- -the values of these angles;
- the value of the angle ∠CC1D;since ∠CC1D=∠N1NE1;is positive if C1C the fixed angle clockwise if clockwise - negative value. It should be noted that;
φ is the angle of the velocity vector of the target relative to the line of sight.
The process of controlling the movement of the object when the homing is as follows.
After viewing the target at a point On the object impart motion through an arc segment S with an angular velocity ωo. To achieve the object given value of qi-1at the point In the sign of ωo.change to the opposite, and the object moving in an arc BD, again replaced by a sign reversal after sight of the goal at point D.
Each time, at the moment of sighting targets (for example in "i"-th, the D point of the trajectory of the object) make measurements of the current value of the anglethe slope of the trajectory of the object relative to the inertial coordinate system and compare it with the previous value of in "i-1"-the point of sight:
and taking into account the obtained values ofset computed by the control law of the "i"oe the average lead angles qi.
The essence of the invention consists in the fact that it is proposed to form the current value of the average lead angles q in the cycle according to the control law in the form of rational functions:
where k=1, 0 ... depending on the conditions of convergence.
Thus, the process of approximation of the object aimed by the proposed method homing procedure is as follows, Fig. 1:
1. The object is located at point O, endorses the goal (point O1), the time point "i-1"; at the same time remember the value of.
2. The object moves during the time T1before reaching the setpointthe magnitude of the angle of inclination of the trajectory of the object relative to the axis of the inertial system of coordinates x0with angular velocity ωo, while the average lead angles will be the value of qi-1up to the point In where changing the sign of the reversal of the object. remember.
3. After change of sign of ωothe object is moved until the "i" fact-of-sight targets at point D of the trajectory of an object that ends with "i-1"-you� cycle convergence and begins a new, "i"-th cycle.
At this point:
b/ are compared,and define its name: in this case the value of
in/ calculate the average lead angles qiin "i"-th cycle, using the control law (3);
g/ produces a change of sign reversal on the opposite;
4. Implement the movement of an object along a trajectory DE with the specified in claim 3 in average lead angles qiby:
a/ move the object within a given value of T1that in the "i"that cycle is equal to:
true, as, Fig. 2, or:
b/ reaches the setpoint on the trajectory of the object sizethat in the "i"that cycle is equal to:
true, since ∠EE1x0=∠EE1N+∠NE1x0the value of ∠EE1N = 2qithe value of ∠NE1x0is equal to;
5. After change of sign of ωoat point E the trajectory of the object peremeshayte point "i+1" - fact sight of the goal at point F of the trajectory, which ends with "i"-th cycle of convergence and a new "i+1"-St cycle.
Further, the homing process is carried out in a similar method according to the paragraphs 3, 4, 5 to approach the minimum distance h, the value of which is in the range from 0 to values:
Fig. 1, 3 and 4 show specific examples of the convergence of the object and purpose of the law (3) for k=1, when V<V1Fig. 1, V1<V for k=1 in Fig. 3 and for k=0 in Fig. 4.
Management of the facility when the hardware implementation of the proposed method is carried out using the functional diagram shown in Fig. 5, where the following notation is used:
4 - the Object with its own stabilization system;
5 - management System object carries a homing;
6 - Steering - implements the control action on the object;
7 Unit performs control with steering wheel commands CBM;
8 - Specialized computing machine SVM - manages the process of guidance based algorithms.
9 - sharing Device of EE - translates incoming information into language CBM;
10 - Meter values of angular velocity ω;
11 - Command unit - implements the inertial coordinate system, the axes of which are the origin of ug�s tilt of the trajectory of the object. As command and control device can be applied gyro-, Astro -, or other devices;
12 Locator goals - record the sighting target, when the velocity vector of the object is directed at the target;
13 - Goal.
After receiving the signal Δ of the fact sight of goal 13, the fixed locator 12, which is perceived CBM 8 after conversion of EE 9, RAS recorded by the program organizes the oscillatory motion of the object 4 by issuing commands via the Converter device 7 on the steering actuator 6, which, in turn, produces a control action δ to rotate the object 1 with a given angular velocity ω0- registered by the device 10. Simultaneously, the signal Δ RAS remembers the current value ofreceived from the command device 8, of course, after the transformation of EE.
After time T1or when the object value of the angleRAS will return the pivot of an object with angular velocity-ω0that ends the sight of the goal (getting the signal Δ from the locator). Then SVM reads through EE from the command device 8, the value of the current angle, compares it with the value in the previous cycle, receiving the value of(positive or�negative), and using this value and the value of the average value of the angle of lead of the previous cycle generates the new control law current values of lead angles and time T1or angle of trajectory, Θ1.
This method of homing can be used when approaching objects in outer space and in other cases, for example, in combination with the method of the chase or in other ways homing.
Explanation of the drawings given in the description.
Shows graphical plots are reduced copies of drawings, executed on graph paper A3. The misses h was defined as the minimum distance between the trajectories of the object and purpose when you split them in the critical region into small segments of time.
The drawing shows the counter-example of the convergence objective, which moves with velocity V1than the speed of the object V, sweep 1, and:
- homing of the object by the method of chase (trajectory 2);
- homing on this method (trajectory 3, calculated according to the algorithm (3) with K=1).
Graphically determined the misses h: for trajectory 2 is "AB", for trajectory 3 is "SV".
The drawing outlines the parameters of the object and purpose for consideration of the angular correlations and the formation of a trajectory of convergence; p�the following analysis the control law selected object as a trend of decreasing values in the preliminary areas of convergence.
The drawing shows an arbitrary example of the convergence of the object and purpose when homing in accordance with the algorithm (3) with K=1.
The drawing shows an arbitrary example of the convergence of the object and purpose when homing in accordance with the algorithm (3) with K=0.
The drawing shows a functional diagram of the hardware implementation of this method.
Method of convergence of a moving object when homing on information about the sighting target locator, the sensitive axis of which coincides with the direction of the velocity vector of the object, characterized in that the trajectory of the object shape in the form of a cyclically repeating arcuate segments, each two segments are combined in a loop that starts and ends with a fact-of-sight of the goal, and the end point of sight of the previous cycle is the starting point of the current, and inside each loop arcuate movement is produced with the best possible constant in a loop angular velocity, the sign of which is changed according to the value of the average lead angle of the trajectory of the object relative to the line of sight, calculated according to the control law for the current cycle as the product of the difference of the values of this angle in the previous cycle and increment, positive Il� negative, the angle of inclination of the trajectory of the object in the current cycle relative to the previous one multiplied by a coefficient that depends on the circumstances of convergence, and a fraction, the numerator of which is the difference between the average values of lead angles in the previous cycle and increment, positive or negative, the angle of inclination of the trajectory of the object in the current cycle relative to the previous one, and the denominator the sum of the specified values.
FIELD: physics, navigation.
SUBSTANCE: disclosed is a method of guiding aircraft to ground facilities. In the method, guidance to ground facilities is controlled simultaneously in an inclined plane whose position is determined by the flight path direction of the aircraft, and in a vertical plane, based on a condition for providing and stabilising the required resolution of radar images of ground facilities, using a proportional navigation technique with offset of the line of sight rate of the ground facility in both aircraft control planes. Offset values are generated such that the direction of the velocity vector of the aircraft in the vertical plane at moment in time matches the direction towards the point of intersection of the perpendicular to the projection of the line of sight of the ground facility on the horizontal plane, which coincides with the ground surface, passing through the ground facility and belonging to said horizontal plane, with the vertical plane in which the velocity vector of the aircraft is located.
EFFECT: high accuracy of guiding aircraft to ground facilities.
FIELD: physics, navigation.
SUBSTANCE: invention relates to autonomous aircraft navigation systems, particularly aircraft navigation systems comprising on-board radar equipment which guides the aircraft to ground objects. Guiding an aircraft to a ground object includes measuring the viewing angle of the ground object in the horizontal plane relative to the direction of the ground velocity of the aircraft, the angular velocity of the line of vision of the ground object in the horizontal plane, the distance from the aircraft to the ground object, the flight velocity of the aircraft and acceleration thereof in the horizontal plane. The method also includes measuring the current value of the deviation angle of the line of vision of the ground object from the direction of the velocity vector of the aircraft, the current value of the viewing angle of the ground object in the vertical plane, the current value of the inclination angle of the velocity vector of the aircraft in the vertical plane, the current value of the angular velocity of the line of vision of the ground object in the vertical plane and the current value of acceleration of the aircraft in the vertical plane. The method includes calculating the current value of the deviation angle of the projection of the line of vision of the ground object on the horizontal plane from the projection of the direction of the velocity vector of the aircraft on the same plane. The obtained results are used to control flight in the horizontal and vertical planes to enable stabilisation of the linear azimuthal resolution of the radar image of the ground object generated by on-board synthetic aperture radar, stabilisation of resolution of said radar image on the horizontal range, and such that the direction of the velocity vector of the aircraft in the vertical plane at each moment in time matches the direction towards the point of intersection of the perpendicular to the horizontal projection of the line of vision of the ground object, passing through said object and belonging to the horizontal plane, with the vertical plane to which the velocity vector of the aircraft belongs. The value of deviations (discrepancies) of current angle measurements, as well as the current inclination angle of the line of vision of the ground object from the required values is estimated and trajectory control signals for the aircraft in the horizontal and vertical planes, which enable to eliminate said deviations, are generated.
EFFECT: high accuracy of guiding an aircraft to given ground objects using on-board synthetic aperture radar.
FIELD: instrument engineering.
SUBSTANCE: during the final preparation for launch mobile carrier, the signals are defined and set proportional to the initial coordinates on the slant range, on the angle of slope, on the azimuth of mutual position of the mobile carrier and originally specified object of viewing (OV) relative to the base of the integrated antenna device in the coordinate system connected to the center of mass of the mobile carrier. At that the operational signals are made in the form of a package of consecutive words that are proportional to the parameters of initial setting of the inertial measurement of parameters of viewing vector of the set OV in the local horizontal coordinate system. These signals convert the parallel form and the signals are formed according to them, proportional to the initial conditions of the setting of inertial direction finding of the set OV in the base antenna coordinate system.
EFFECT: increased accuracy.
2 cl, 8 dwg
FIELD: aircraft engineering.
SUBSTANCE: stabilised sight line is consecutively aligned with every viewing object. Distance to objects and their angular coordinates relative to finder system are defined and memorised. After launching the aircraft toward short-range viewing object and its interception by control system, time of flight abeam flight path is measured. Data on aircraft hitting the preset viewing zone or miss is defined and fed to finder system field of vision. In the case of miss and possibility of re-aiming, instruction for flight above sight line is sent to aircraft. Sight line is switched to the next range viewing object and, at approach thereto, aforesaid instruction is cancelled to move the aircraft to sight line. In further misses, elevation instruction is fed with changing sight line to the nest viewing objects. Said elevation instruction is fed to aircraft when it flies over immediate object.
EFFECT: higher accuracy of control.
FIELD: weapons and ammunition.
SUBSTANCE: engineering anti-aircraft mine comprises a contactless target sensor and a directional fragmentation warhead. The method to damage low-flying targets consists in the fact that the mine warhead is actuated using a bistatic radar target sensor. The device for damage of low-flying targets is made in the form of a bistatic radar system made of a spaced radar transmitter and an autonomous Doppler radar receiver. The radar transmitter is installed on the secured object. The autonomous Doppler radar receiver is installed on the area surrounding the object, together with the fragmentation warhead. In another version of design the device warhead is made in the form of an electromagnetic missile. The electromagnetic missile comprises ready fragments of a ferromagnetic material. The area of fragmentation warhead damage is matched with the zone of detection of the autonomous Doppler radar receiver.
EFFECT: higher reliability of damage of various air targets under any meteorological conditions.
4 cl, 1 dwg
FIELD: weapons and ammunition.
SUBSTANCE: complex homing head comprises an optical and infrared digital photo cameras, a passive or an active radiolocator, an automatic pilot, a unit of threshold passage of a signal of an optical photo camera, a unit of switching off of infrared pixels, an electronic key, a delay line and a night vision device. The signal from the night vision device or from the infrared camera arrives to a specialised computer of a control system, where with the specified extent of validity it is compared with all-aspect images of all known airplanes available in the computer memory. After identification of the airplane type the computer determines the predetermined resolution or prohibition for target damage. A pre-programmed most vulnerable area is selected on the target, and further homing is carried out to the same area by readings from the night vision device or infrared camera.
EFFECT: improved accuracy.
9 cl, 1 dwg
FIELD: weapons and ammunition.
SUBSTANCE: method of generation of a signal of control of a shell rotating by list angle consists in detection of an amplitude modulated signal with a tracking gyroscopic head of homing, proportional to angular speed of a target sighting line, conversion of a signal into a width-modulated signal that arrives to an inlet of a steering drive of the shell. At the same time the sum of the amplitude-modulated signal and the signal of the sensor of angular speed of the shell filtered with a filter of noise components and a filter of a permanent component is converted into the width-modulated signal.
EFFECT: provision of possibility to increase probability of shell hitting a target.
1 cl, 6 dwg
SUBSTANCE: method of striking a target producing coherent interference by launching and guiding missiles fitted with an active radar seeker involves emitting a probe signal and receiving the signal reflected by the target, wherein two missiles are simultaneously directed onto the target, and emission of the probe signal and reception of the signal reflected by the target are reassigned between the missiles alternately; before launching missiles, the intervals for emitting probe signals and receiving reflected signals are synchronised such that intervals for emitting the signal of one missile match intervals for receiving the signal reflected from the target of the other missile. Switching intervals for emitting the signal and receiving the reflected signal is carried out with frequency higher than the bandwidth of the guidance system, and the frequency of switching emission and reception intervals is set primarily alternating. The missiles are guided into the target on "pliers" type maximally divergent trajectories.
EFFECT: improved method.
4 cl, 2 dwg
FIELD: weapons and ammunition.
SUBSTANCE: topographical lock-on of launcher is effected with the help of satellite navigation system prior to setting the fire parameters. Fire control board with digital radio communication means is located 50-100 metres from launcher. Lock-on errors may not exceed 50 metres. Fire control parameters are transmitted in binary code to launcher ACS and, further, to missile. Launcher is turned to azimuth and elevation to launch the missile by command from control board.
EFFECT: increased range of fire, higher safety.
SUBSTANCE: optoelectronic system for an air defence missile system has an pointing head (5) mounted on a precision two-coordinate turning device (8), as well as a computing unit (13), a monitor (15) and a control unit (16). The pointing head (5) has a double-channel design with wide (6) and narrow (7) field of vision television channels. The optoelectronic system is fitted with a unit for superimposing wide and narrow field of vision images (14). The lens of the narrow field of vision channel has a mirror-lens design with central screening and includes a main concave mirror (19) and a convergent mirror (20) arranged in series, as well as annular first (21) and second (22) optical wedges placed in front of the convergent mirror (20) with possibility of independent rotation relative each other around the optical axis of the lens. The outer diameter of the optical wedges is equal to the diameter of the main concave mirror (19), and the inner diameter is equal to the diameter of the convergent mirror (20). The wide field of vision (6) channel is placed in front of the narrow field of vision (7) channel having a common optical axis with it. The diameter of each of the components wide field of vision (6) channel does not exceed the diameter of the convergent mirror (20).
EFFECT: possibility of battery launch of a missile with one air defence missile system at several targets at once.
FIELD: armament, in particular, artillery guided missiles with a laser semi-active homing head locking on n illuminated target in the terminal trajectory leg; the invention is designed for control of fire of mortars and barrel artillery of calibers, types 120, 122, 152, 155 mm, at firing of guided ammunition, as well as of guided missiles with a homing head.
SUBSTANCE: the method consists in the following: the target is detected by a target indicator, then the distances between the target indicator and the target and the firing position and the target are measured with a topographical survey of the target, target indicator and the firing position, computation and realization of the firing settings according to the target and firing position coordinates. Then, missile guidance to the target is performed, it includes a successive gun setting and turn of the missile on target illuminated after the shot by laser radiation of the target indicator, the topographical target survey and conversion of its coordinates to a sequence of binary codes is accomplished with the aid of a reconnaissance panel, and the computation of gun settings is performed with the id of a gun control panel. A common computer time is organized in the reconnaissance panel and in the gun control panel, and after the shot up to the actuation of the target indicator transmission of the value of the time of switching of target indicator laser radiation is performed from the gun control panel to the reconnaissance panel by means of digital radio communication, and the signal of switching of target illuminance is automatically transmitted from the reconnaissance panel to the target indicator at achievement of the time of switching.
EFFECT: enhanced accuracy of fire by a guided missile at a target illuminated by a laser beam due to reduced quantity of "hand" operations and enhanced accuracy of synchronization of the moment of target illumination with the time of the shot; the last property is especially important for destruction of moving targets.
FIELD: homing systems of flight vehicles.
SUBSTANCE: the method consists in the fact that the distance from the flight vehicle to the target by the moment of beginning of homing, the current rate of closure with it, angular velocities of the sight line and the lateral accelerations of the target and guided flight vehicle in the horizontal and vertical planes are measured. After measurements the signals of flight vehicle control in the horizontal and vertical planes are formed according to the relations using the mentioned coordinates of the target and flight vehicle. The high sensitivity of the flight vehicle to the target maneuver is based on the estimation of its lateral accelerations, and the adaptation to the range of the beginning of homing is based on estimation in the procedure of suspension of its navigation parameter.
EFFECT: provided reaction to the maneuver of far located targets and adaptation to the range of the beginning of homing predetermining a more active maneuver of the guided object on a near located target.
FIELD: high-accuracy armament systems, in particular, guidance systems of tactical ballistic missiles.
SUBSTANCE: the method includes the lunching of the missile and its flight on the trajectory having a ballistic leg, on which the moment of separation of the correctable war module is determined, and the correctable war module is separated, and a homing leg. In addition the flight trajectory has a leg of intermediate correction. Prior to the missile launch, the initial conditions for computation of the predicted flight trajectory of the correctable war module are set into the on-board computer via the antenna of the communication radio set and the on-board receiver. After the launch the kinematic parameters of the missile motion are additionally determined on the ballistic leg, and after separation of the correctable war module the predicted miss of the correctable war module is computed on the leg of intermediate correction, and the impulse correction engine is started for reduction of the miss to the minimum value. Before the homing leg the correctable war head is decorated to the operating linear and angular velocity, and the beginning of the homing leg is determined by transmitting a signal from the correctable war module via the radio channel to the target indicator-range finder. At intermediate correction and homing the impulse correction engines are started when the current miss exceeds the allowable value.
EFFECT: enhanced accuracy of guidance.
FIELD: radio engineering, in particular, methods for guidance of self-moving guided projectiles to reflected laser beam, applicable in military equipment.
SUBSTANCE: use is made of several sources of illumination of the optoelectronic device located on the object of destruction. These sources operate at different frequencies, as a result of which an information field of projectile flight control is produced with a multispectral homing head, which makes it possible to reduce the requirements to the accuracy of projectile guidance to the target at the initial leg o guidance to the optoelectronic instrument, located in the most vulnerable point of the armored object.
EFFECT: enhanced accuracy of guidance of guided projectile to the most vulnerable points of position of the optoelectronic instrument, and efficiency of destruction of the armored object.
FIELD: aircraft guidance systems.
SUBSTANCE: method comprises measuring transverse acceleration of the aircraft to be guided in the horizontal plane, measuring the angle between the vector of aircraft velocity and line of sighting on the ground object, distance between the aircraft and ground object, velocity of the aircraft, and generating the control signal in the horizontal plane as the difference between the required angular velocity of the conventional sighting point multiplied by the adaptive navigation parameter and transverse acceleration of the aircraft in the horizontal plane. The adaptive navigation parameter is generated depending on the difference between the current value of the angle between the vector of the aircraft velocity and line of sighting on the ground object in the horizontal plane and required angular shift of the conventional sighting point in the horizontal plane with respect to the line of sighting on the ground object.
EFFECT: improved stabilizing of linear resolution of the guidance.
FIELD: air defense.
SUBSTANCE: system comprises housing connected with four return springs each of which is connected with the corresponding air vane, propulsion engine, four photomultiplier tubes of the guidance system which are connected in the arms of the electric bridge, four air vanes connected with the electromagnets with movable core through intermediate relay, four infrared devices for photomultiplier tubes, four vision limiters for photomultiplier tubes, four DC amplifiers for photomultiplier tubes, board power source, four tail stabilizing fins, analogue-digital converter, and control unit composed of integrator, tree-link integrating device, and inverter. The photomultiplier tubes are connected with the analogue-pulse converter, intermediate relay, integrator, inverter, and three-link integrating device through the DC amplifier.
EFFECT: accelerated missile aiming.
FIELD: rocket armament, in particular, methods of fire by guided missiles from infantry fighting vehicles and tanks.
SUBSTANCE: after launching of the missile from the bore the sustainer engine is started in the trajectory of its flight by the preset start-up time, and the missile is controlled in the active and passive sections of the trajectory up to the end of the missile flight. The sustainer engine is started by a device with an electronic delay, the delay time is determined from the condition: where: - delay time of sustainer engine starting; - missile flight speed at the instant of sustainer engine starting; V0(m/s) - missile muzzle velocity; m(sq.kgf/m) - missile mass at the instant of sustainer engine starting; cx - missile drag coefficient; Smid(sq.m) - missile maximum cross-section area; - air density.
EFFECT: enhanced efficiency of fire due to the increase of the maximum flying range at a simultaneous reduction of spread and reduction of dispersion in the initial trajectory section.
FIELD: methods for generation of launcher guidance angles by fire control devices.
SUBSTANCE: the probability of pursuit of the underwater target is determined and in addition a correcting of the launcher guidance angles is introduced in the calculation of the lead point coinciding with the center of the target pursuit area by determination of linear deflection of aiming point Δxc by formula: Δxc=l0-ln , where ln - semilength of the target pursuit area; l0 - semilength of the target lock-on area.
EFFECT: enhanced probability of hitting of the underwater target at firing by rockets 90P to the target lead point.
5 dwg, 2 tbl
FIELD: guided missile guidance systems.
SUBSTANCE: before normalization of missile control signals the engine operation time is preset, a priory evaluation of the projections of the missile axial acceleration onto the input axes of the antenna co-ordinate system of the homing head is preset. On completion of engine operation the present flight time is measured, the time before impact with the target is determined, and the evaluation of miss caused by missile axial acceleration is determined. The axial acceleration compensation signal is proportional to the evaluation of miss caused by missile axial acceleration. The obtained compensation signal is summed up with the signal of missile control according to the method of proportional navigation or its modifications.
EFFECT: enhanced accuracy of guidance.
FIELD: armament, in particular, control of artillery guided missiles with a laser semi-active homing head, locking an illuminated target in the terminal trajectory leg, applicable for control of fire of mortars and cannon artillery.
SUBSTANCE: the method consists in topographical survey of the target indicator and firing position to the terrain, target detection by the target indicator, measurement of the distance from the target indicator to the target, azimuth and angle of sight relative to the target indicator under the conditions of successive target location. Topographical co-ordinates, direction and speed of target motion are calculated in the reconnaissance panel, the co-ordinates, speed and direction of target motion are transformed to a series of binary codes and transmitted to the firing position panel by the digital radio communication. On the basis of the obtained data and preliminarily preset meteorological data, ballistic corrections, time of preparation of the gun and missile to fire the predicted point of impact of the missile with the target an the ground surface is calculated, the fire settings according to the co-ordinates of the gun and the co-ordinates of the predicted point of impact of the missile with the target are calculated, the time of the shot for target destruction in the predicted point is calculated, the sole computing time is set in the reconnaissance panel and in the firing position panel, the fire settings are realized. The signal for a shot is given from the firing position panel when the time of the shot is coming. The time of switching-an of the target indicator of laser radiation is transmitted from the firing position panel to the reconnaissance panel via the digital radio communication channel. The signal for switching-on of the laser radiation target indicator is automatically given from the reconnaissance panel when the required time of switching-on is attained, and the missile is guided to the target illuminated by the laser radiation of the target indicator.
EFFECT: enhanced accuracy of fire at movable targets.
4 cl, 2 dwg