Method of control over aircraft flight

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.

 

The invention relates to military technology, and more particularly to a method of traffic control aircraft (LA), in particular, are installed in the complexes UAV, remote controlled objects (meteorological, agricultural, geological, robotic and other), guided weapons as stationary (on the surface, mining, surface, submarine launchers)and mobile (on various objects, such as tanks, infantry fighting vehicles, self-propelled launchers, helicopters and other).

Control the movement of aircraft during their flight allows to significantly improve the accuracy characteristics of appropriate systems, including weapons that are installed on the ground and on various mobile carriers. The firepower of these machines increases significantly, and by complementing conventional weapons (artillery or infantry) managed aircraft (unmanned aerial vehicles (UAVs), missiles (UR) and others).

Currently, there are various ways to control the movement of aircraft (UAVs, guided missiles, shells and other). The effectiveness of ways to control their movement depends on the efficiency of the complexes as a whole.

A known method of controlling the movement of missiles (protistan the new, anti-hail and other) of the first generation, which consists in putting the gunner (the operator) on the object of sight (goal) line of sight, eye the measurement of the variations of the aircraft (guided missile), the impact on the management bodies of the missile in accordance with these deviations to combine guided missile with the target (see, for example, Antitoxin "Anti-tank weapon), Voenizdat, 1974, P.á192-236). The first generation are managed (anti-tank and other) missiles with manual guidance systems. ATGM first generation and the methods of their generation have obvious disadvantages: low speed missiles, implemented them, and hence a very large time of flight (20-25 ░ C), does not strike zone before firing position depth of 300-600 m, low rate of fire compared to other anti-tank means and other Education personnel rules firing and practical skills is very expensive and difficult, as manual control requires strict selection and thorough training of operators. Low speed flight requires continuous visual tracking missile and the target, and the missile guidance throughout the trajectory. Therefore navodchikom (operators) ATGM must meet strict requirements. For training and periodic drills gunners who problemih missiles with manual guidance system requires complex electro-optical equipment. In addition, with this method of control is almost impossible to eliminate one of the main disadvantages: low speed flight of the guided missile, as by increasing the speed of its movement work gunner is much more complicated, because the control is usually done by using commands, based on the relative position of the missile and the target. The gunner is not physically have time to respond to changes in direction of flight speed missiles (LA). He also experiences significant difficulties in the derivation of the rocket on the line of sight. Avoid levka missiles in the ground near the launcher (firing object) last give a significant elevation angle. The result is formed (see above) Neustrashimy area size in 600-700 m in Addition, under these conditions, virtually eliminated shooting with mobile carriers, especially when they are maneuvering, as well as the possibility of transfer line of sight the next object of sight when you miss the previous (especially when limiting the maximum flight range of the aircraft).

There is also known a method of controlling the movement of the aircraft (missiles) guided missile weapons C-1 "Cobra" (see, for example, "the armament of the tank T - 80B". Tank T-80B. And IE. M, Voenizdat, 1984, P.95-127), which is the most Liskin the technical nature of the claimed and received for his prototype. At the same time it is a basic object of the proposed method.

This method of control aircraft movement is the formation of a stable line of sight and combining it with the object of sight, the launch of the aircraft, its capture by the control system, measurement system control deviation of the aircraft from the line of sight during its flight, the automatic creation and transfer it to the control commands corresponding to this deviation, automatic generation and submission to the authorities drone control signal corresponding to this command.

This method differs from the previous by the fact that continuous monitoring of the object of sight, combining with it the line of sight, leading the gunner (the operator), and tracking of AIRCRAFT (missile), measurements of the deviations from the line of sight, the development and transfer of command aboard a flying AIRCRAFT (missiles), and then on his (her) controls are performed by the control system automatically. This method is compared with the previous provides (see there):

the increasing speed of aircraft (missiles); the reduction of the time of flight of missiles at maximum range; reducing the "dead zone" of up to 75 m or less from the firing position; higher efficiency and stability of the results of firing the variety of situations antitank combat; simplifying operator (its functions are limited to the combination of line of sight with the object of sight, and the control commands are generated and transmitted automatically on LA), which improves accuracy and minimizes the impact on the results of the individual operator data.

However, this method also has disadvantages. The need for long holding time line of sight on the object of sight leads to the risk of loss when in sight of the gunner light or miladinovich interference. The presence on Board AIRCRAFT (missiles) powerful light source is required to generate the light of feedback and closed loop control, making it difficult for the gunner tracking purpose, exacerbating the effect of light interference. All this leads to a significant increase in error tracking of the target (the object of sight) because of the difficulties compensation gunner deviations of the line of sight (target brand) from the target caused by maneuvering the rolling carrier. This is because the stabilization system line of sight in the prototype measures and compensates only the angular deviation of the line of sight from a given gyroscopic sensor angular direction at the target and does not respond to linear movement of the guidelines together with the carrier (tank). Operas is Thor not able to compensate for them, especially in terms of noise and interruptions in the visibility of the target.

In addition, the maneuvering of the carrier during the flight LA (guided missile) leads to a violation of the compliance with the provisions of LA (guided missile) on the trajectory in the longitudinal direction and information zone (the plane perpendicular to the flight path of aircraft (missiles) control.

In the above-mentioned shortcomings remain significant errors of alignment of the line of sight with the object of sight (in order) from interference, especially unexpected noise, appearing in the process guidance more dangerous objects of sight (goals), requiring the transfer line of sight (retargeting) and the operational decision leads to penalty or loss of AIRCRAFT (missiles), constant tension of the operator and reduce the effectiveness of fire.

The aim of the present invention is to improve the efficiency of traffic control aircraft (guided missile) by providing the ability to retarget to another, more dangerous target (the object of sight) or in the case of a miss on the first goal (the object of sight), the increased robustness of the visual channel, precision-guided missile (aircraft) and the introduction of additional information about the parameters of the process control.

Goal of d is attained, however, in the method of controlling the movement of aircraft, consisting in formation of a stable line of sight and combining it with the object of sight, the launch of the aircraft, its capture by the control system, measurement system control deviation of the aircraft from the line of sight during its flight, the automatic creation and transfer it to the control commands corresponding to this deviation, automatic generation and submission to the authorities drone control signal corresponding to this command, if the field of view of the sighting device several suspected objects of sight, the combination of a stable line of sight produce successively with each of them, identify and remember their range and angular coordinates relative to the target device, after the launch of the aircraft in the direction of the middle (first) range of the object of sight and capture its control system measures the time of its motion on the trajectory, determine and served in the field of view of the sighting device to hit the aircraft in the specified zone object of sight or penalty, in case of a miss in the middle (first) on the distance to the object of sight and the conditions (1) and (2)

Ψ2,1{[(D22-2D1D2cosΨ2,1+D12)/Vland]-tp}ωng,(1)

φ2,1{[(D22-2D1D2cosφ2,1+D12)/Vland]-tp}ωnin,(2)

where D1- distance to the middle (first) range of the object of sight,

D2- distance to the next (second) in the range of the object of sight,

VLa- cruise speed of the aircraft,

tp- loss of time and, define the total inertia of the control system and operator when the line of sight from one object of sight to another,

ωng, ωNV- rational (disposable) angular velocity guidance of the aircraft, respectively, in horizontal and vertical planes,

Ψ2,1φ2,1- angular misalignment between the direction to the middle and the next (first and second) the objects of sight, respectively, in horizontal and vertical planes when you slip on the middle (first) object of sight,

served on aircraft command in excess of its flight above the sight line, transfer line of sight the next (second) range the object of sight and when approaching him off the team for the excess and gently bring the aircraft to the line of sight, in case of further failures on aircraft continue to apply the command to the excess of the translation line of sight for the next objects of sight, definition, and presentation of information in the field of view of the sighting device about the appropriate penalties, and in case of loss of capture for a time exceeding the time required to re-capture the return line of sight to its original position, when this command on the excess to the aircraft serves Ave is every miss in the time span they another object of sight, and removing commands excess produce through time

tpp{[(D22-2D1D2cosΨ2,1+D12)/Vland]-(tp+ty),

wheretCRthe time of flight of the aircraft with the excess over the line of sight,

ty- the lead time for removing commands excess and smooth the output of the aircraft on the line of sight.

The introduction of significant new features allows you to extend the capabilities of known methods, improves the efficiency of targeting LA (guided missile) by redirect (transfer line of sight) for other purposes (objects of sight) in the case of a miss on the nearest (first) range of the target (the object of sight), improving the noise immunity of the visual channel and precision-guided LA (guided missile) by introducing additional information about the possibility of redirect (transfer line is sight) and temporal parameters of the process aiming LA (guided missile).

Implementation of the proposed method is as follows. Form a stable line of sight by analogy with the prototype and combine it consistently with the objects of sight (goals)that appeared in the field of view of the sighting device of sight (gunner) and selected for viewing (lesions). Define and automatically memorize their range and angular coordinates relative to the sighting device. In determining the coordinates of the joint operation of the laser rangefinder, encoders, storage and computing devices, and other elements of the apparatus can be arranged so that in moments of measurement of distance to targets at the same time could be measured and remember their angular coordinates relative to the given direction, which can be used in the direction from visirule device on one of the objects of sight, usually the middle. The presence of coordinate objects of sight (goals) allows comparison between them and calculate the angular sizes of the zones of probable hits (lesions) in the vertical and horizontal planes for later after a miss purposes of determining the optimal sequence of translation (retargeting) line of sight when possible mistakes largest Ψ2,1,φ2,1with what ispolzovaniem conditions of expressions (1) and (2).

On the basis of the calculated values enter into the field of view of the sighting device of sight and form the visual information that facilitates decision-making on possible upcoming redirect (transfer line of sight), if the second target (the second object of sight), for example, is in the zone of probable hits (lesions). Run LA (guided missile) and its capture by the guidance system, and then start to measure the time of his (her) motion on the trajectory before the withdrawal to the line of sight. The capture of LA (guided missile) in the prototype is carried out by installing a missile source of light radiation, and beam guidance systems capture is provided by the capture device located onboard a guided missile. The conclusion of the guided missile on the line of aim, as a rule, are performed autonomously, according to a certain program, and to develop additional commands on this site no practical need.

The value of the altitude of LA (guided missile) maintain a constant by reducing the formation of light and miladinovich interference, as well as the persistence of transients maneuvering LA (guided missile) relative to the line of sight. At the sight of the middle object of sight (target) movement of aircraft (missiles) may going on the th as at the height of the line of sight, and with the excess over it (if the height of the uneven terrain creates the danger of entries LA (missiles). If the sight is one (one) of the following objects of sight (goals, after a miss on the first), then, because of the difficulty of estimating the height of the irregularities, the command in excess of aircraft flight (guided missile) above the line of sight is served with every miss, translate the sight line to the next (second) range target (object) and when approaching it (to him) remove command on the excess and gently bring LA (guided missile) to the line of sight. Removing commands excess produce through time

tpp{[(D22-2D1D2cosΨ2,1+D12)/Vland]-(tp+ty),

where tCRthe time of flight of the aircraft with the excess over the line of sight, ty- the lead time for removing commands excess and smooth the output of the aircraft is of Parata (guided missile) to the line of sight.

When loss of capture of LA (guided missile), associated with the termination of the management process, return line of sight to its original position or combine it with another object-of-sight (purpose) and repeat the operations to start and control the movement of the second LA (guided missile).

When loss of capture of LA (guided missile), involving a loss of visibility of the object of sight (target) or LA (missiles), take a pause equal to the time to re-grip (for prototype - 0,3-0,7), and only after that return line of sight to its original position.

If at the time of passage of the object of sight (target) loss of capture has not occurred, determine and present information in the field of view of the sighting device about the flight of AIRCRAFT (missile) this goal with a penalty on it, after which transferred in accordance with the conditions (1) and (2) the line of sight on the second(left) and, in the case of a miss for him (her), similarly for subsequent objects of sight (target) with the definition and presentation of information in the field of view of the sighting device about the span of the corresponding objects of sight (targets) with a penalty, after what if it hits, and in the event of a loss of capture and the time required to re-capture the return line of sight to its original position. On subsequent launches of LA implementation of the method is the same.

Application of p is izlagaemogo way traffic control LA allows almost no significant changes in its characteristics to implement (through the transfer line of sight (retargeting) a chance to improve the efficiency of aircraft control (missiles). So, for example, getting the second goal (the object of sight) allows for a 10-15% increase overall likelihood that LA (guided missile).

The method of controlling the movement of aircraft, consisting in formation of a stable line of sight and combining it with the object of sight, the launch of the aircraft, its capture by the control system, measurement system control deviation of the aircraft from the line of sight during its flight, the automatic creation and transfer it to the control commands corresponding to this deviation, automatic generation and submission to the authorities drone control signal corresponding to the command, wherein if the field of view of the sighting device several suspected objects of sight, the combination of a stable line of sight produce successively with each of them, identify and remember them the distance and angular coordinates relative to the target device, after the launch of the aircraft in the direction of the middle - the first range of object sighting and capture its control system measures the time of its motion on the trajectory, determine and served in the field of view of the sighting device to pop the years of aircraft in a given area of the object of sight or miss, in the case of a miss on the middle - the first range to the object of sight and the conditions (1) and (2)
Ψ2,1{[(D22-2D1D2cosΨ2,1+D12)/Vland]-tp}ωng,(1)
φ2,1{[(D22-2D1D2cosφ2,1+D12)/Vland]-tp}ωnin,(2)
where D1- distance to the middle - the first range of the object of sight,
D2- distance to the next - the second paragraph is the distance of the object of sight,
VLa- cruise speed of the aircraft,
tp- loss of time, defined by total inertia of the control system and operator when the line of sight from one object of sight to another,
ωng, ωNV- rational (disposable) angular velocity guidance of the aircraft, respectively, in horizontal and vertical planes,
Ψ2,1that & Phi;2,1- angular misalignment between the direction to the middle first and second objects of sight, respectively, in horizontal and vertical planes when you slip on the middle - the first object of sight,
served on aircraft command in excess of its flight above the sight line, transfer line of sight the next second distance, the object of sight and when approaching him off the team for the excess and gently bring the aircraft to the line of sight, in case of further failures on aircraft continue to apply the command to the excess of the translation line of sight for the next objects of sight, definition, and presentation of information in the field of view of the sighting device about the appropriate penalties, and in case of loss of capture for a time exceeding the time required to re-capture the return line of sight to source the e position, when this command on the excess to the aircraft served with every miss in the time span they another object of sight, and removing commands excess produce through time
tpp[(D22-2D1D2cosφ2,1+D12)/Vland]-(tp+ty),
where tCRthe time of flight of the aircraft with the excess over the line of sight,
ty- the lead time for removing commands excess and smooth the output of the aircraft on the line of sight.



 

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2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: proposed system compares signals from optical and IR digital photo cameras and radar signal to differentiate between true and false targets. System generates anticipation trajectory via feedback between rudders with movable homing head, that is, the latter turns in direction opposite the rudder deviation unless the rudders stay in neutral position. System can perform leading anticipation towards airframe via shifting rudders position transducer neutral toward the side coinciding with homing head deviation, or its additional deviation toward the same side.

EFFECT: high probability of heating maneuvering target.

4 cl, 3 dwg

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.

1 dwg

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