The method of controlling the flight of a managed aircraft and managed aircraft

 

(57) Abstract:

The invention relates to techniques for aircraft. The method of controlling the flight of a managed aircraft is in managing a rotary air rudder feed on its outer surface for the center of pressure of the control gas. The aircraft includes a rotary air rudders and the gas source with the missile launcher. In the case of the aircraft behind the center of pressure of the rudder is made through holes connected by channels with a source of working gas. The invention improves the speed of flight of the aircraft without sacrificing manageability. 2 S. and 6 C.p. f-crystals, 3 ill.

The invention relates primarily to the military, in particular, to methods for flight control of piloted aircraft, as well as to managed aircraft that implements these methods.

There is a method of flight control antitank guided missiles (managed aircraft) [1] , which consists in managing air rotary rudder and implemented with mission control, anti-tank guided missile (managed aircraft), th missiles (managed aircraft), what anti-tank guided missile (controlled aircraft during flight experiences aerodynamic resistance, which is a component of the resistance of friction. The large aerodynamic resistance is accompanied by a decrease as airspeed anti-tank guided missile (managed aircraft), and reducing the possible range (the range of its flight), i.e., increase time for target destruction and reduction of potential destruction. Efficiency deteriorates. Especially significant decrease in airspeed anti-tank guided missile (managed aircraft), when the distance between the location of the start and target (opponent) slightly (about 1-1 .5 km). The reduction in speed leads to an increase in flight time to the target, and accordingly, increases (due to the small distance between the location of the start and target probability of detection by enemy places start opening them to respond to fire, which can lead to the defeat of a calculation, and launchers (or artillery) that you are shooting. A delay of even a few tenths of a second lesion with increased time for response will give the opponent the chance to hit as the calculation and the launcher. Effectiveness is reduced. With increasing distance between the location of the start and target (opponent) the probability of detection of the start and, accordingly, the opening of the aimed fire of the enemy is reduced, although the flight time antitank guided missiles (managed aircraft) to the target increases. Increase airspeed to ensure the specified range is possible by increasing the capacity of the firing device, but it is accompanied by the increased weight and size of the firing device, and launchers (artillery), which ultimately increases the weight and dimensions of the complex as a whole, reducing the maneuverability on the battlefield and increasing the likelihood of injury from enemy fire. Increase airspeed to ensure the specified range is possible by increasing the power and time of a jet engine, but this is accompanied by an increase in the weight and size of the jet engine, and hence the whole system with all the negative consequences. Efficiency does not increase. To increase the speed possible and by reducing the caliber antitank API part. For example, the armor penetration cumulative combat units depends on the caliber. Efficiency is not increased.

Closest to the proposed technical solution is the method of controlling the flight of the aircraft [2], which consists in managing the rudders, ailerons, flaps, etc. (rotary air rudders) and applying to the outer surface of the working gas, which is implemented in the flight control of the aircraft, containing the rudders, ailerons, flaps, etc. (rotary air rudders), the intake device (gas source) with a starting device, in the case of the aircraft is a through hole connected to the air intake device (gas source) channel.

The disadvantage of this method and managed aircraft is that supplied to the outer surface of managed aircraft air (working gas) "captures" the center of pressure rotary air rudders, causing the offset. This worsens the working conditions of rotary air rudders, because the offset of the center of pressure causes the deterioration of their management abilities and increase the display area, and accordingly, further increases the hinge point. The increase in hinge moment leads to the necessity of raising the necessary power steering. Increasing power steering accompanied by an increase in the size and weight of the steering actuator and the source of his power, which causes, in the end, increase the size and weight of all managed aircraft with all the ensuing negative consequences. Efficiency deteriorates. The deterioration of the dimensional and weight characteristics most significantly for managed aircraft type guided missiles, especially small.

The task of the invention is to increase efficiency by increasing flight speeds, with improved manageability and overall weight characteristics.

The problem is solved in the method of controlling the flight of a managed aircraft, which consists in managing a rotary air rudders and applying to the outer surface of the working gas, so that during the flight managed aircraft, the supply of the working gas on its outer surface is at the center of pressure swivel which can be produced in a rotary air rudders and razreseno around the perimeter of the cross-section of the hull managed aircraft, and managed aircraft, containing a rotary air rudders and the gas source with the missile launcher, while in the case of managed aircraft is a through hole connected to the gas source by a channel therein through holes in the casing controlled aircraft connected to a source of working gas channel, made for the center of pressure rotary air rudders, these through-openings in the case of managed aircraft, connected with a source of working gas channel can be accomplished in a rotary air rudders and razreseno around the perimeter of the cross-section of the hull managed aircraft. The gas source may be in the form of a cylinder with a working gas, and its starting device in the form of an electromagnetic valve, and the channel connecting the gas source with the hole in the housing of the controlled apparatus can be made in the form of a gap between the internal elements of a managed device.

The positive effect is achieved by reducing the friction force with improved working conditions for rotary air rudders.

This technowledge shell 2 with a rotary air rudders 3 and firing device 4. Firing the device shown in the drawing the case made in the form of a starting jet engine 5, but it may be in the form of a gas generator propellant charge in the cartridge case (when the shot projectile out of the barrel or piston, under the action of compressed gas firing guided projectile, etc., Figures 6 and 7 are denoted by the steering actuator and the axis of the rotary air rudders, respectively. Guided projectile provided with a source 8 of the working gas with a starting device 9 and the body 10 of the controlled projectile razreseno perimeter 11 of its cross section at the center 12 of the pressure rotary air rudders performed through hole 13 connected to a source of working gas channel 14. In the drawing version of the through hole in housing managed projectile located behind the rotary air rudders, but they can be located and directly behind the center of pressure rotary air rudders, which is to reduce hinge moments tend "to have" as close as possible to the axis of the rotary air rudders. The starting device of the gas source, as shown in the drawing, can interact with the sensor starting 15, i.e., to provide automatic activation East of the apparatus, in this case, the managed projectile. The proposed solution can be used in manned managed aircraft, such as airplanes. Then the "inclusion" of the gas source may carry out the pilot of the aircraft or this "inclusion", as in the above embodiment, will be carried out automatically, when starting the engine of the aircraft or when the takeoff. The gas source, as shown in Fig. 1 and 2, may be made in the form of a cylinder 16 with a working gas (compressed or liquefied), for example, nitrogen or air as his starter device is in the form of an electromagnetic valve 17. It can be done in the form of a chemical generator working gas, for example by reaction of sodium bicarbonate with acid. In this case, the starting device permits operation of the chemical generator. The gas source can also be made in the form of an air intake device in which it is advisable to have a single inlet located on an axis controlled aircraft, in this case managed projectile. The entrance to the air intake device during operation and storage (before firing) can be constantly Otkroy or moved in the direction of ensuring "open" port air intake device before firing or the initial time of the flight, managed projectile. In this case, a mechanism to automatically "open" air intake device performs the function of the starter. Channel 14 extending from the gas source has a branch 18, going to the through holes in the housing of the controlled projectile. At this junction you can go to each through-hole, and, for example, as shown in Fig. 3, to several at once (two, three, and so on), depending on the specific design. It is most expedient to group a through hole or two in the group, because it achieves the most uniform distribution of the incoming gas between them. Through holes 13 in the case of a managed projectile can be designed in the form of round holes, and, for example, as shown in Fig. 2, 3, in the form of slits 19, bigger side located on the perimeter of the cross-section of a managed shell. Running through holes in the form of cracks gives a more even distribution of the working gas on the surface of a managed projectile in its submission during the flight. As sensor start (when electrical actuation of the starting device of the gas source can be used, for example, as shown in Fig. 1 to 3, the inertia is Olsen in the form of gas contactor, closing your work contacts from the effects of the powder gases firing device. When electrical actuation firing device sensor start may be in the form of a branch from the circuit it engaging and reaching the triggering device (solenoid valve, the system is "open" air intake device, and so on) of the gas source (cylinder, the intake device, and so on), providing that their joint operation. It should be noted that when the shot managed projectile from the barrel to the beginning of movement of the controlled projectile in the barrel to give the time interval on leaving the trunk steerable projectile and only after that to give the command to actuate the starter of the gas source. When performing the gas source in the form of an air intake device with a permanently open inlet a function of its starting devices with sensor start in this case is performed by guided projectile receiving power pulse from the firing device and start moving forward (start managed projectile), i.e. with the beginning of the flight managed projectile provides an automatic pnic working gas through the holes in the case of a managed shell, if in the case of a managed shell there are no through holes, except those connected to this channel, can be made in the form of gap 21 between the internal elements 22 a managed shell.

Managed aircraft, in this case guided projectile, works as follows. Guided projectile shot with the device mounted on the launcher or in the trunk artillery (depending on the design of a managed shell) and prepare to fire. Continue to serve on the fire and starts firing device. Guided projectile receives a power pulse from the firing device (starter motor, generator, propellant charge in the cartridge case, and so on) and starts to move forward. Before you start a managed shell or the initial moment of its flight include starter source of working gas and working gas channel is supplied to the outer surface of the controlled shot over the center of pressure rotary air rudders. Coming to the outer surface of managed flying projectile working gas envelops guided projectile, creating a lubricating layer between the flowing guided projectile in the again working gas does not affect the working conditions of the rotary air rudders, because he misses the most sensitive in aerodynamic terms, the part of the swivel steering - its center of pressure displacement which leads to an increase in articulated steering torque (steering pressure to reduce the hinge moment and, accordingly, reduce the required power steering strive "to have" as close as possible to the axis of the steering wheel). The increase in the power steering increases the size and weight of the steering actuator and power supply, with all the ensuing negative consequences, which is not conducive to efficiency. After the flight managed projectile a distance of the order of 1 - 1.5 km enumerated in the reference time, i.e. the time during which the projectile is guaranteed to fly this distance, may be terminated by the flow of the working gas on the side surface of the managed projectile. If the proposed technical solution used in the manned managed aircraft (planes and so on), inclusion of the gas source may be done by the pilot before takeoff and during the flight, depending on the circumstances.

Supply managed aircraft source of working gas with the starting uznikom working gas, behind the center of pressure rotary air rudders can reduce the frictional resistance, which reduces the total aerodynamic resistance. Raise the speed controlled aircraft (reduced time defeat the purpose if this solution is used in guided missiles and rockets) and increases the possible range (increases the possible area of defeats the purpose). This improves the working conditions of the rotary air rudders. This is because applied to the outer surface of managed aircraft working gas does not fall on the most sensitive in aerodynamic terms, the part of the swivel air rudders - their center of pressure. Increases manageability managed aircraft, and the possibility to reduce the required area of these surfaces, and hence the power drive and power supply. Improved dimensional and weight characteristics. All this increases the efficiency. The flow of the working gas on the outer surface of managed aircraft for rotary air rudder improves its handling and speed, because in this case applied to the outer surface of the working gas is gas the outer surface of managed aircraft and, accordingly, a possible reduction in speed is compensated by improving the manageability, which allows to reduce the dimensions and weight of the steering actuator and the source of his power, and thus for all of the managed device. Therefore, when the same motor setup managed aircraft with reduced dimensions and weight (by reducing the size and weight of the steering actuator and the source of his power) gets an extra speed boost. Efficiency increases. When the supply of the working gas on the outer surface of managed aircraft razreseno around the perimeter of the cross-section of its body working gas is more uniformly distributed on the outer surface, reducing this friction. Speed controlled aircraft increases. Efficiency increases. Most appropriate to apply the proposed solution for guided projectiles, particularly small, and having aerodynamic scheme "duck". The flow of the working gas on the outer surface of managed aircraft (managed projectile) during a reference time of flight corresponding to the guaranteed flight controlled flying apparatus is th aircraft (managed projectile) at the site, the most dangerous from the point of view of possible detection by the enemy designated start and, consequently, reduce the time on his possible response (open fire or shelter for any protective construction, folds, and so on). The winning time at this distance (about 1 - 1.5 km) even in the few tenths of a second can decide the outcome of the fight. When the distance between the location of the start and goal more than 1 - 1.5 km, despite the increase in the time response, the probability of detection by enemy designated start a managed aircraft (managed projectile), due to the increase in distance decreases. Ensuring the supply of the working gas during the control time, guaranteeing flight operated aircraft (operated by shell) distances of the order of 1 - 1.5 km, can be provided, for example, the volume of the working gas (compressed or liquefied), located in the container, or the same time chemical generator working gas, and is the most simple, which increases the reliability, and hence the efficiency. This reduces the necessary size and weight of the gas source (cylinder, chemical generator and so on), which reduces the envelope is as a working gas can be nitrogen, carbon dioxide, air, etc. as well as special gas mixture, reducing the frictional resistance. It should also be noted that the working gas must be optically transparent, because otherwise he will unmask the location of the start of the managed aircraft (managed projectile), which reduces the efficiency. The implementation of the gas source in the form of a cylinder with a working gas enables to use as a working gas special gas mixture, reducing the frictional resistance, and thus further increase the speed controlled aircraft (managed projectile), which increases the efficiency. Performing channel connecting the gas source with the hole in the hull managed aircraft (controlled by the shell) in the form of a gap between the internal elements of managed aircraft (managed projectile) greatly simplifies the proposed design controlled aircraft (managed projectile), which increases the reliability, and hence the efficiency.

The proposed solution allows to raise efficiency by increasing flight speeds, with improved manageability and dimensional-scales the x rudders. It can be used in both unmanned and manned managed aircraft.

Sources of information

1. A. N. Latukhin. "Anti-tank weapons". M, Voenizdat, pages 192-208, Fig. 43.

2. Russia, patent N 2033945 (C-CA N 5037896 from 22.05.92), IPC 7 64 39/10.

1. The method of controlling the flight of a managed aircraft, which consists in managing a rotary air rudders and applying to the outer surface of the working gas, characterized in that during the flight managed aircraft, the supply of the working gas on its outer surface is at the center of pressure rotary air rudders.

2. The method of controlling the flight of a managed aircraft under item 1, characterized in that the flow of the working gas on its outer surface is at a turning air rudders.

3. The method of controlling the flight of a managed aircraft on PP.1 and 2, characterized in that the flow of the working gas on its outer surface is razreseno around the perimeter of the cross-section of the hull managed aircraft.

4. Managed aircraft, containing the rotary wondet performed through hole, connected with a source of working gas channel, wherein the through hole in the casing controlled aircraft connected to a source of working gas channel, made for the center of pressure rotary air rudders.

5. Managed aircraft under item 4, characterized in that the through hole in the casing controlled aircraft connected to a source of working gas channel, made for rotary air rudders.

6. Managed aircraft under item 4 or 5, characterized in that the through hole in the casing controlled aircraft, connected with a source of working gas passage spaced around the perimeter of the cross-section of the hull managed aircraft.

7. Managed aircraft according to any one of paragraphs.4 to 6, characterized in that the gas source in the form of a cylinder with a working gas, and its starting device in the form of a solenoid valve.

8. Managed aircraft according to any one of paragraphs.4 to 7, characterized in that the channel connecting the gas source with the hole in the hull managed aircraft, done the

 

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