RU2228456C2 - Method of and device for increasing luminous emittance of nozzle of single use of reusable false heat targets of liquid hydrocarbon fuels - Google Patents

Abstract

FIELD: air and space craft of military and civil application. SUBSTANCE: proposed method to increase luminous emittance of false heat target nozzle comes to afterburning of products of thermal decomposition of liquid hydrocarbon fuels in burning flame. Hard carbon deposit is formed on metal surface in volume of liquid hydrocarbon fuel. Afterburning of hard carbon deposit is done of the limits of false heat target nozzle consists of chamber with liquid hydrocarbon fuel accommodating rod with artificial roughness. Rod is heated to 500-900^oC and is held under said conditions with subsequent displacement into zone of burning flow behind exit section of false heat target nozzle. EFFECT: increased survivability and efficiency of craft. 17 cl, 20 dwg

Description

It is known that one of the ways to protect aerospace aircraft (LA) from enemy air defense, missile defense, and air defense systems is to use false thermal targets (LTC). As a rule, these are powder batch charges placed behind the aircraft along its trajectory or shot from the aircraft in different directions [1]. These LTC can be classified as disposable. However, modern foreign aircraft’s weapons are equipped with very sensitive infrared guidance heads that can direct a missile directly into the aircraft’s nozzle. Protection against such missiles is the method of installing a special nozzle shield that masks the light (and thermal) radiation of the aircraft propulsion system (DU) [2, 3, 4]. The present invention can be used in conjunction with a camouflage screen DU LA and without it.

A new single-use or reusable LTC is proposed, based on an increase in the luminosity of the additional nozzle (LTC DU) due to the afterburning in it of the thermal decomposition products of liquid hydrocarbon fuels (TS-1 kerosene, naphthyl, etc.).

It is assumed that LTC with increased luminosity on liquid hydrocarbon fuels is a single or multi-nozzle device, for example, liquid propellant rocket engine, propulsion engine and other remote control devices with a displacing (or pumping) supply of fuel (and oxidizer), which can be mounted on the main nozzle of the aircraft (or inside LA) and discharged in the overflight zone above the air defense, missile defense, anti-aircraft defense systems of the enemy or upon detection of attacking missiles and other objects. This is a single-use liquid petroleum-based fuels and lubricants.

If you fasten such a fleet to an aircraft on a cable, tow it at different distances from the aircraft throughout the flight or in the danger zone, and then tighten it again in the aircraft (for example, before boarding the aircraft), then this can be considered reusable fleet [5].

In this case, a constant supply of fuel to the LTC from the central fuel system of the aircraft (pumping or displacement) through hoses with armored heat insulation, mounted on a tow rope, is possible. For the protection of aviation aircraft, it is possible to use various WFD, LRE, hybrid and other remote control systems as an aircraft. And for the protection of spacecraft (KL) - LTC with LRE.

It is assumed that all LTCs (single and reusable) should have an external streamlined shell with wings (and plumage), especially for LTCs of air and aerospace applications. Space-based LTC - only the shell (without wings and plumage). To increase the secrecy and effectiveness of an LTC, its shell can be made, for example, radiolucent (using the Stelt technology). In essence, these LTCs are autonomous or towed unmanned aerial vehicles (UAVs). If these LTCs are additionally equipped with a detection system for approaching or passing by aircraft (missiles, shells, etc.), as well as reusable lateral orientation engines (side remote control) (or nozzle devices) and the possibility of a directed explosion, this will not only be LTC or UAV, but also an aerospace or space mine. It is assumed that when an approaching object is detected on the side of the LTC (or at an angle), behind (in the tail), in parallel - at the right moment, the cable system should disconnect (shoot) from the LTC without impulse, and the LTC itself must maneuver due to lateral remote control to attack to an attacking missile (projectile, etc.) and further destruction by an explosion of directional action. In the case of an obvious approach of the enemy object to the LTC nozzle device from behind (i.e., when the attacking missile is aimed at a brighter nozzle), the following options are possible:

a) the explosion of the LTC itself somewhat earlier than the explosion of an attacking rocket;

b) an LTC explosion synchronously with an attacking missile;

c) disconnecting (shooting) the cable from the LTC at the time of its explosion or explosion of an attacking rocket;

d) disconnecting (firing) the cable from the LTC somewhat earlier than the explosion of the LTC or attacking rocket.

It was experimentally found that when parts of the fuel-cooling equipment of an aircraft washed by liquid hydrocarbon fuels or coolers are heated, a layer of solid carbon precipitate forms on them. For example, in the LRE 2-3 minutes after starting in the cooling jacket, a layer of solid sediment forms, which significantly increases the wall temperature due to the violation of the calculated heat transfer processes and can lead to burnout and, as a result, to a fire and explosion of the remote control and the entire aircraft. And the process of sedimentation, for example, in the nozzles of the airborne propulsion aircraft, leads to coking of the fuel filters, to partial or complete loss of traction, as well as to an accident and disaster [6, 7]. It was experimentally established that sedimentation actively occurs in liquid hydrocarbon fuels at a wall temperature of 200-750 ° C and a pressure higher than atmospheric, up to critical and supercritical. At a temperature of t = 500–900 ° C and p> 0.1 MPa, a solid layer of carbonaceous precipitate forms on metal surfaces washed with fuel. It is noted that in depressions of artificial roughness (in the holes, in the grooves of a tapered thread, in ring cuts, etc.), a precipitate forms faster than on a polished surface. If this negative process (sedimentation) is created artificially and burned in a burning stream, then it will turn from negative into positive, because will help increase the luminosity of the flame. Thus, if an LTC is created on liquid hydrocarbon fuel with elements of artificial (special) nucleation of a solid carbon deposit and its afterburning, the luminosity of the LTC nozzle will be higher than the LA nozzle, which will lead to the redirection of the attacking missile specifically at the LTC nozzle.

So, to increase the luminosity of the LTC nozzle, it is necessary to create conditions for precipitation on some metal surface, and then place this surface in the combustion zone, preferably at the end of the nozzle or outside it (so as not to violate the calculated equilibrium system of intracameral combustion). For example, a rod made of heat-resistant and heat-resistant alloy steel (hereinafter simply a rod) with an artificial roughness in the form of a conical thread with a depth of 3-5 mm can be offered the most effective for precipitation and its further burning. It was experimentally found that the thickness of the solid carbonaceous precipitate does not exceed the depth of artificial roughness, and the retention strength of the precipitate is higher than on a smooth (polished) surface. To ensure sedimentation, this rod must be placed for some minutes in any volume (chamber) with liquid hydrocarbon fuel at a pressure p> 0.1 MPa and heat (t = 500-900 ° C) is brought to it (to the rod). It is possible to supply liquid hydrocarbon fuel from the central fuel and cooling system of the aircraft (KL) or autonomously.

There are 3 possible cases of heating the rod: electric (Joule heat); heating from the outer wall of the combustion chamber (nozzle) of the LTC; heating from combustion products (from the flame from the nozzle of the remote control of the LTC). The most economical and efficient methods of heating are the last two, because do not require additional energy supply, etc. However, electric heating can be used in a single-use LTC with preliminary accelerated preparation of a rod with solid carbon sludge before an aircraft flight or during a flight (before an LTC discharge). In addition, electric heating can also be used in reusable LTCs to reduce the time of rod preparation during the first release and towing of the LTC or generally reduce it, for example, during ground or space preflight preparation.

An analogue of the method for increasing the luminosity of a burning flame is described in [8].

Specifically, the closest analogue to the method of increasing the luminosity of a flame can be considered a method of increasing the luminosity of a nozzle by burning the products of thermal decomposition of liquid hydrocarbon fuels in a burning flame, in which the formation of a solid carbon deposit occurs before burning under conditions of natural or weak forced convection of liquid hydrocarbon fuels at pressures high atmospheric [9].

Various devices for increasing the luminosity of a burning flame are described in [8, 9]. The closest analogue of the device for increasing the luminosity of an LTC nozzle on liquid hydrocarbon fuels can be considered a device consisting of a chamber with liquid hydrocarbon fuel with natural or low forced convection and a pressure higher than atmospheric [9].

The indicated method and device for increasing the luminosity of the nozzle are not perfect enough and require various improvements based on experimental studies of the characteristics of heat transfer to liquid hydrocarbon fuels, including the process of sedimentation.

The proposed method of increasing the luminosity of the nozzle by burning the products of thermal decomposition of liquid hydrocarbon fuels in a burning flame, in which the process of formation of a solid carbon precipitate occurs before burning under conditions of natural or weak forced convection of liquid carbon fuels at atmospheric pressures, characterized in that:

1. A solid carbon precipitate is formed on a metal surface located in the volume of liquid hydrocarbon fuel, with a low flow rate at pressures higher than atmospheric, including critical and supercritical values, and heated to temperatures of 500-900 ° C, and afterburning of the solid carbon precipitate is carried out outside nozzle false thermal target (LTC).

2. The metal surface is heated electrically, from the outer wall of the LTC nozzle, from contact with the combustion zone at the exit of the LTC nozzle behind its cut, in a hybrid way (by various combinations of the first three methods).

3. The process of sedimentation with its further afterburning in a burning stream is reusable.

The proposed device for increasing the luminosity of the nozzle will have a number of differences and additions, discussed below.

Chamber 2 (FIGS. 1, 2) is filled with liquid hydrocarbon fuel 3 and a core 1 of stainless heat-resistant and heat-resistant steel (hereinafter simply referred to as a core) with artificial roughness in the form of a tapered thread 3-5 mm deep, heated to temperatures of 500-900, is placed inside the chamber ° C and maintained under these conditions for several minutes, with the possibility of further movement to the zone of the burning stream behind the nozzle section of the LTC.

A chamber 2 with a rod 1 is placed longitudinally on the outer wall of the LTC nozzle 5 at an angle of 5-10 ° (Fig. 3) with the possibility of moving part of the rod 1 with solid carbon sediment 4 through the end cover 6 into the combustion zone 7 using a pusher (rod) 8 with a preliminary cessation of fuel supply (figure 4).

The output of fuel residues from the chamber 2 (Fig. 4) is provided together with the rod 1 by an additional air purge system or by constructive creation of the piston 9 at the junction of the rod 1 and the rod 8 by means of a worm-screw pair and an electric motor.

The cover 6 (Fig. 5) is thermo-insulated and is provided with a mechanical opening-closing system of the chamber, consisting of an upper hinge 10, a mechanical (or electromechanical) lock 11, a spring-link mechanism 12, two cables 13 fixed diametrically 14 on the sides of the cover 6 and at the calculated location 15 of the rod 8.

When transferring the rod 1 (Fig. 5) into the combustion zone behind the nozzle exit, it comes into contact with the lock 11, which releases the cover 6 from the control locking. Under the influence of compression of the lever-spring mechanism 12, the cover 6 rotates through a hinge 10 by 90 °, completely exposing the chamber 2. Upon completion of the afterburning, the rod 1 is pulled by the rod 8 back into the chamber 2, where the ropes 13 are tensioned after the rod, which helps to reliably close the cover 6 to activate the control lock 11.

The rod 1 (Fig.6) is placed in contact with the bottom wall 16 of the chamber 2, which is structurally the outer casing of the LTC nozzle (WFD or LRE), which makes it possible to use heat from the combustion chamber for the precipitation process.

Natural or small forced convection of liquid hydrocarbon fuel in the chamber 2 can be provided autonomously from the aircraft tank or LTC or with partial use of external regenerative cooling.

Rod 1 (Fig. 7) is provided with a bare external end 17 without artificial roughness, constantly (or periodically) located near or in the combustion zone behind the nozzle section of the LTC, which allows efficient heating of the entire rod 1 from the combustion products.

The rod is heated simultaneously from the contact of the bare end with the products of combustion (with an open flame) and from contact with the outer surface of the LTC nozzle (Fig. 7).

Rod 1 (Fig. 8) is made in the form of a ring (hereinafter simply a ring) with a central axial sleeve 18 and a rigid diameter 19 placed in a chamber 2 (Fig. 9) with a partial bare sector 20 perpendicular to the end face (cut) of the LTC nozzle 5 with the possibility heating from the burning stream and periodic rotation around its axis through the rotation mechanism, consisting of an electromechanical (or spring, etc.) engine 43, rigidly connected to the sleeve 18 through the axis 44 (see Fig. 9).

Here, starting from the 2nd cycle, 3 processes are carried out immediately: heating of the bare sector 20 (see Figs. 9, 10), and hence the entire ring; afterburning of solid carbon sludge; sedimentation process. This option is one of the most profitable and economical. 10, the above fragment is depicted in rear view of the LTC nozzle.

The rods (or rings) are evenly distributed around the perimeter of the nozzle 5 LTC (Fig.7, 10), and their number must be at least at least two.

The chamber 2 is made in the form of an individual bellows-type corrugated cylinder with an internal spring 21, inside of which a rod 1 is placed, having an external bare threadless end of the valve type 22 with the possibility of full extension for afterburning (Fig. 11) and returning to its original position.

The extension of the rod 1 (Fig. 12) to the working position is carried out by increasing the fuel pressure in the individual corrugated cylinder 23 or by the lateral nodes of the movable rhombus 24 (Fig. 13), driven by the supply of increased fuel pressure in the common corrugated cylinder 25 (Fig. 13) or electric motor 26 (Fig.14) through a worm-screw pair 27.

The fuel supply to the chamber 1 (see Fig. 12, 13, 14) is metered (until it is completely filled) in the presence of the rod 1 at a pressure higher than atmospheric (this was mentioned earlier). The supply of fuel to the individual corrugated 23 (Fig. 12) or to the general corrugated 25 (Fig. 13) cylinders is provided so that their pressure significantly exceeds the pressure during compression of the inner spring 21 (Fig. 11, 12, 13, 14) to full the extension of the rod 1 out of the chamber 2 (Fig.12, 13). Here, the rules should be optimally implemented:

a) the length of the extended individual corrugated cylinder 23 (Fig) must be at least the length of the steel rod 1;

b) the pressure in the common corrugated cylinder 25 (Fig.13) and its maximum linear increase, as well as the operation of the electric motor 26 (Fig.14) with a worm-screw pair (transmission) 27 should provide compression of the diamond 24 (Fig.13, 14) so that the linear movement of its lateral joints squeezed the corrugated type chamber 2 (FIGS. 13, 14) as much as possible and pulled the rod 1 out as far as possible to burn out the solid carbonaceous sediment 4 on it.

The return of the rod 1 to its original position (Fig.12, 13, 14) is provided:

a) depressurization in an individual corrugated 23 (Fig. 12) or common corrugated 25 (Fig. 13) cylinders;

b) ensuring the operation of the electric motor 26 (Fig.14) with a worm-screw pair 27 in the opposite direction;

C) the work of the inner spring 21 (11-14) to expand until the chamber 1 is completely sealed.

Rods 1 with bare threaded ends of valve type 22 in chambers 2 (Fig. 12) (corrugated cylindrical bellows type) are placed radially in one (Fig. 15) or several tiers (Fig. 16) in a common cylindrical steel casing 28 (Fig. 15) , 16) with a streamlined head part with ablation, graphite, and other types of thermal protection 29 (Fig. 15, 16).

The number of radial rods in each tier should be optimal (to ensure the necessary increase in the luminosity of the LTC nozzle), and therefore, the same number of corrugated cylinders 23 (Fig. 12) or movable rhombuses 24 (Figs. 13, 14).

The common steel cylindrical body 28 (Fig. 17) in the stowed position (or in the parking position) is mounted on the outer part of the nozzle 5 of the LTC (Fig. 17), and in the fighting position it is led out of the nozzle 5 of the LTC coaxially with it (Fig. 18).

The length of the fastening tubes 30 (Fig.17, 18) is selected from the conditions of the optimal effect of afterburning steel rods 1 (Fig.11-14) with solid carbon sludge 4. In addition, the fastening tubes 30 (Fig.17, 18) must be refractory, thermally insulated, as their internal channels can be used: for supplying fuel (and an oxidizing agent if necessary); for power supply - for internal heating of steel rods 1; for communication and signaling channels (for example, readiness of steel rods 1 for afterburning, pressure increase in governing bodies and chambers 2, completion of fueling in working chambers, etc.).

On the moving lateral joints of the movable rhombuses 24 (Fig. 19), chambers 2 (circular sealed type) are installed with rods 1 (ring type), that is, with rings, the bare sectors 20 of which are subjected to afterburning and simultaneous complete heating of the closed parts of the rings with their further periodic turning around its axis.

It was previously said (see Figs. 8-10) that the use of ring-shaped rods is the most economical and almost continuous afterburning process, i.e. increasing the luminosity of the LTC nozzle. Each chamber 2 (Fig. 19) is equipped with a bevel gear 31 rigidly fixed on its axis, i.e. on the axis passing through the sleeve 18 on a rigid diameter 19 (see Fig. 8).

To transfer the device (Fig. 19) to the firing position, i.e. to extend the chambers 2 until the bare sectors 20 with solid carbon sludge are left out of the housing 28 for afterburning, it is necessary to apply pressure to the common corrugated cylinder 25 (or apply power to the electric motor 26 with a torque to the worm-screw pair 27) to compress the diamond 24, the lateral movable nodes of which are associated with the ends of the chambers 2, will facilitate the longitudinal movement of the chambers 2 to the stop. In this case, the gears 31 will mesh with the main central bevel gear 32, the main central bevel gear 32, mounted on the main axis 35, passing through a solid partition (wall) 34 and mounted on it using bearings. On the main central bevel gear 32, a cylindrical gear of a smaller diameter 33 is rigidly fixed, which is connected to the movable gear plates 38, 39 (Fig. 19, 20) emerging from the metal housings 36, 40 (Fig. 19, 20), rigidly fixed to the lower the base of the partition 34 (Fig.19, 20), inside of which are movable corrugated chambers 37, 41 (Fig.19, 20), rigidly connected to the beginning of the gear plates 38, 39. If necessary (after reburning) rotation of the rod 1 (ring type ) (to bring out the new sector 20 for afterburning) is necessary it is possible to apply increased fuel pressure, for example, to the corrugated chamber 37 (Fig. 20), which will increase its linear size and push the gear plate 38 from the housing 36, which will engage with the cylindrical gear 33, will set it in motion, which means and gear 32, from which gears 31 also turn, i.e. the rotation of the rod 1 (ring type) will be ensured with the output of the new sector 20 for afterburning. The calculation of all gears, gear plate 38 and corrugated chamber 37 is made so that in three feed portion pressure into the corrugated chamber 37, the gear plate 38 rotates gear 33 three times, providing rotation of the shaft 1 by 120 °, i.e. the full exit of the gear plate 38 provides one complete rotation of the rod 1 (ring type) with interruptions for burning off the sectors 20. When the gear plate 38 is extended, another identical plate 39 (Fig. 20) will retract and its corrugated chamber 41 will contract. The extension of the toothed plate 39 (Fig. 20) will begin after the operation of the plate 38 (after the third pressure is applied to the corrugated chamber 37) by applying the portioned pressure of the fuel into the corrugated chamber 41 and first depressurizing the corrugated chamber 37. In this case, all gears (and sectors 20) will rotate in the other direction. If it is necessary to push sectors 20 into the housing 28 (at the end of work), it is necessary to relieve pressure in the common corrugated cylinder 25, after which the spring 42 will compress and draw the sectors 20 into the housing 28. (The number of springs 42 depends on the number of pairs of casings 2). In the presence of an electric motor 26 with a worm-screw pair - to retract the sectors 20 into the housing 28 - it is sufficient to ensure the rotation of the shaft of the electric motor 26 in the other direction.

The whole system (Fig. 19) is also placed in a steel cylindrical streamlined body 28 with ablative, graphite and other heat-protective coatings (TZP), as in Fig. 15, 16, in one or more tiers (layers).

Afterburning of rods or sectors 20 rods of a ring type are performed simultaneously in all tiers or alternately.

The number of tiers and rods 1 in each tier of a cylindrical steel streamlined body 28 (FIGS. 15, 16, 19) depends on the dimensions of the LTC nozzle, on the required level of increased luminosity, on the required time of combat use of the LTC, etc. The regulation of the afterburning sequence is possible with various command signals: to supply fuel pressure to individual, common corrugated cylinders 23, 25 37, 40; into the electric motor 26.

Each subsequent tier (with straight or ring-shaped rods) should be rotated at a certain angle relative to the central axis so that the space between the (straight, ring) rods in one tier is overlapped by their presence in the other (i.e. in a checkerboard pattern). With the simultaneous afterburning of all rods (rings) in all tiers, the maximum luminosity of the LTC nozzle is achieved. But this process lasts 1-1.5 minutes, and for repeated inclusion, time is required for the formation of a solid carbon deposit on steel rods (rings): 3-5 minutes. Therefore, it is more rational to burn one or two tiers, and then others, etc. That is, in this way it is possible to maintain the increased luminosity of the LTC nozzle during the period of the necessary time of flight over the enemy’s air defense, missile defense, and air defense dangerous zones.

All (straight and ring) rods provide internal electrical heating with reliable electrical insulation. For this purpose, all (straight, ring) rods should be hollow inside (for example, with preliminary drilling of the core or using finished tubes).

Electric heating can be supplied in rods of the ring type through the rotation axis, rigid diameter, etc. Calculation of the length of filaments (straight, twisted - spiral-shaped, etc.), as well as voltage and insulation, must be made from the need for quick, complete and reliable heating to the technologically necessary temperature for sedimentation in the recesses of the artificial roughness of the rods (rings).

All aircraft and airborne vehicles (air, aerospace, space) are equipped with a detection system for approaching objects (attack missiles, shells, etc.) with the possibility of necessary maneuvering of the airborne vehicles with reusable side remote control (nozzles) with the implementation of directional explosion and timely pulse-free towing shooting cable from the LTC.

The reusable auxiliary control devices (nozzles) should be located in the center of mass and perpendicular to the longitudinal main axis of the LTC. For effective maneuvering, four solid fuel control (nozzles) on solid fuel (solid propellant) are sufficient, but are more economical and more convenient to use on liquid hydrocarbon fuel.

The transfer of the LTC to the combat position is carried out automatically or at the signal of the pilot, astronaut, ground operator with the conclusion of information about all stages of the LTC’s operation on their special display.

Thus, taking into account the above material, it is possible in a more specific and correct form to propose a device for increasing the luminosity of the nozzle, consisting of a chamber with liquid hydrocarbon fuel with natural or low forced convection and pressure, more than atmospheric, characterized in that:

the chamber is filled with liquid hydrocarbon fuel and a core of stainless heat-resistant and heat-resistant steel with an artificial roughness in the form of a tapered thread 3-5 mm deep is placed inside the chamber, heated to temperatures of 500-900 ° C and maintained under these conditions for several minutes, with the possibility of further movement into the zone of the burning stream behind the nozzle exit of the false thermal target;

a chamber with a rod is placed longitudinally on the outer wall of the nozzle of a false thermal target with the possibility of moving part of the rod with solid carbon sediment through the end cap into the combustion zone using a pusher with a preliminary shutdown of fuel supply;

the rod is placed in contact with the lower wall of the chamber, which is structurally the outer wall of the nozzle of the false thermal target;

the rod is provided with a bare external end without artificial roughness, constantly or periodically located either near or in the combustion zone behind the nozzle exit of the false thermal target;

the rod can be simultaneously heated from contact of the exposed outer end without artificial roughness with the combustion products (with an open flame) and from contact with the outer wall of the nozzle of a false thermal target;

the rod is made in the form of a ring with a central axial sleeve and a rigid diameter and is placed with a partially exposed sector in the chamber perpendicular to the nozzle exit of the false thermal target with the possibility of heating from the burning stream and periodic rotation around its axis through the rotation mechanism;

additionally contains chambers evenly distributed along the perimeter of the nozzle of the false thermal target with rods located inside, and the total number of chambers must be at least two;

the chamber is made in the form of an individual bellows-type corrugated cylinder with an internal spring, inside of which there is a rod with an exposed bare threadless end of the valve type without artificial roughness, which can be fully extended to re-burn a solid carbon deposit and return to its original position;

the rod is extended to its working position by increasing the fuel pressure in the individual corrugated cylinder or by the lateral nodes of the movable rhombus, driven by either applying increased fuel pressure in the common corrugated cylinder, or by an electric motor through a worm-screw pair;

additionally contains chambers with rods placed inside, all chambers are made in the form of individual corrugated cylinders and placed radially in one or several tiers in a common cylindrical steel case with a streamlined head with ablative, graphite and other types of thermal protection, and all rods are equipped with bare threadless ends valve type;

the common steel cylindrical body in the stowed position or in the parking lot is fixed on the outer part of the nozzle of the false thermal target, and in the combat position it is led out of the nozzle of the false thermal target in alignment with it;

additionally contains chambers with rods placed inside, all chambers are located on the joints of movable rhombuses, all rods are made in the form of rings, on the bare sectors of which they burn solid carbon sediment with simultaneous complete heating of the closed parts of the rings and their further periodic rotation around its axis;

afterburning of solid carbonaceous sediment or rod sectors made in the form of rings is carried out simultaneously in all tiers or alternately;

the rod is provided with internal electric heating with reliable waterproofing.

This invention will significantly increase the survivability, combat effectiveness and reliability of military, civil and airborne, aerospace and space aircraft.

Sources of information

1. Scherbinin O. Strategic military transport aircraft S-17A “Globmaster-3” US Air Force. Foreign Military Review, 1996, No. 7, pp. 38-40.

2. Volzhin A.N., Sizov Yu.G. Fight against homing missiles. M .: Military Publishing, 1983.

3. Lazarev L.P. Infrared and light devices for homing and guidance of aircraft. M .: Engineering, 1976.

4. Paly A.I. Electronic warfare. M .: Military Publishing, 1974.

5. Alekseev A. Modernization of strategic B-1B bombers. Foreign Military Review, 1997, No. 9, pp. 55-56.

6. Zrelov V.N., Piskunov V.A. Jet engines and fuel. M .: Engineering, 1968.

7. Dregalin A.F., Altunin V.A. et al. Investigation of the possibility of intensifying heat transfer processes and preventing precipitation in power plants of ekranoplanes. University News. Aviation Engineering, 1995, No. 2, pp. 69-76.

8. Copyright certificate SU 787802 A, published on December 15, 1980.

9. Copyright certificate SU 399682 A, published on 10/03/1973.

Claims (17)

1. The method of increasing the luminosity of the nozzle by burning the products of thermal decomposition of liquid hydrocarbon fuels in a burning flame, in which the process of formation of a solid carbon precipitate occurs before burning under conditions of natural or weak forced convection of liquid hydrocarbon fuels at atmospheric pressures, characterized in that the solid carbon a precipitate is formed on a metal surface located in the volume of liquid hydrocarbon fuel, with a low flow rate at pressures greater than atmo- spheric including critical and supercritical values, and heated to temperatures of 500-900 ° C, and solid carbonaceous sludge reburning is performed outside the heat nozzle false targets. 2. The method of increasing the luminosity of the nozzle according to claim 1, characterized in that the metal surface is heated electrically, from the outer wall of the nozzle of a false thermal target, from contact with the combustion zone at the outlet and behind its cut, in a hybrid way (various combinations of the first three methods ) 3. A method for increasing the luminosity of a nozzle according to claim 1 or 2, characterized in that the process of sedimentation with its further afterburning in a burning stream is reusable. 4. A device for increasing the luminosity of a nozzle, consisting of a chamber with liquid hydrocarbon fuel with natural or low forced convection and a pressure higher than atmospheric, characterized in that a rod made of stainless heat-resistant and heat-resistant steel with artificial roughness in the form of a conical thread 3- deep in 5 mm, heated to temperatures of 500-900 ° C and maintained under these conditions for several minutes, with the possibility of its further movement into the zone of the burning stream behind the nozzle exit of the false thermal target. 5. A device for increasing the luminosity of the nozzle according to claim 4, characterized in that the chamber with the rod is placed longitudinally on the outer wall of the nozzle of the false thermal target with the possibility of moving part of the rod with solid carbon sludge through the end cap into the combustion zone using a pusher with preliminary cessation of supply fuel. 6. A device for increasing the luminosity of a nozzle according to claim 4 or 5, characterized in that the rod is placed in contact with the lower wall of the chamber, which is structurally the outer wall of the nozzle of a false thermal target. 7. A device for increasing the luminosity of a nozzle according to any one of claims 4 to 6, characterized in that the rod is provided with a bare external end without artificial roughness, constantly or periodically located either near or in the combustion zone behind the nozzle exit of a false thermal target. 8. The device for increasing the luminosity of the nozzle according to claim 7, characterized in that the rod can be simultaneously heated from contact of the exposed outer end without artificial roughness with the combustion products (with an open flame) and from contact with the outer wall of the nozzle of a false thermal target. 9. A device for increasing the luminosity of a nozzle according to claim 4, characterized in that the rod is made in the form of a ring with a central axial sleeve and a rigid diameter and is placed with a partially exposed sector in the chamber perpendicular to the nozzle exit of a false thermal target with the possibility of heating from a burning stream and periodic rotation around its axis through the rotation mechanism. 10. A device for increasing the luminosity of a nozzle according to any one of claims 4 to 9, characterized in that it further comprises chambers evenly distributed around the nozzle’s false thermal target with rods inside, and the total number of chambers must be at least two. 11. A device for increasing the luminosity of a nozzle according to any one of claims 4 to 6, characterized in that the chamber is made in the form of an individual bellows-type corrugated cylinder with an internal spring, inside of which there is a rod with an exposed bare threadless end of the valve type without artificial roughness, having the ability full extension for afterburning solid carbon sludge and returning to its original position. 12. The device for increasing the luminosity of the nozzle according to claim 10, characterized in that the rod is extended to its working position by increasing the fuel pressure in the individual corrugated cylinder or by the side nodes of the movable rhombus, driven by either supplying the increased fuel pressure in the common corrugated cylinder, or an electric motor through a worm-screw pair. 13. The device for increasing the luminosity of the nozzle according to claim 11 or 12, characterized in that it further comprises chambers with rods located inside, all chambers are made in the form of individual corrugated cylinders and are arranged radially in one or several tiers in a common cylindrical steel case with a streamlined head part with ablation, graphite and other types of thermal protection, and all the rods are equipped with bare threadless valve ends. 14. The device for increasing the luminosity of the nozzle according to claim 13, characterized in that the common steel cylindrical body in the stowed position or in the parking position is fixed on the outer part of the nozzle of the false thermal target, and in the combat position it is discharged coaxially with the nozzle of the false thermal target. 15. The device for increasing the luminosity of the nozzle according to claim 4, characterized in that it further comprises chambers with rods located inside, all chambers are located on the joints of movable rhombuses, all the rods are made in the form of rings, on the bare sectors of which they burn out the solid carbon sediment while complete heating of the closed parts of the rings and their further periodic rotation around its axis. 16. A device for increasing the luminosity of a nozzle according to any one of paragraphs.13-15, characterized in that the afterburning of a solid carbon deposit on the rods or sectors of the rods, made in the form of rings, is carried out simultaneously in all tiers or alternately. 17. A device for increasing the luminosity of a nozzle according to any one of claims 4-16, characterized in that the rod is provided with internal electric heating with reliable electro-hydro isolation.

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