RU2547963C1 - Method of aircraft start (versions) - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: aircraft (AC) is placed in the Launcher, or in a Launcher transport and starting barrel, or partially in Launcher TSB with an external arrangement of the jet nozzles, or a transport and starting container (TSC), or TSC of Shaft Launcher, the starting propulsion system (SPS) is fixed in AC front part, AC is partially moved forward, SPS is started, the traction is formed by two jet nozzles located on a lateral surface of SDU at an angle to a longitudinal axis of AC, the front part of LA is protected during acceleration by the fairing fixed on SPS, SPS is separated by means of draft force.

EFFECT: invention allows to decrease the weight of an aircraft structure, launcher start load and simplify a launcher design.

7 cl, 4 dwg

Description

The invention relates to guided missiles, in particular to aircraft (LA), mainly unmanned, and devices for their launch.

There is a known method of launching an unmanned aircraft "Yakhont" ("Russia's Arms and Technologies. Encyclopedia. XXI Century", Volume III, edited by S. Ivanov, Arms and Technologies Publishing House, Moscow, 2001, pp. 103-109, and OA Artyomov “In-Line Aircraft Engines”, Sputnik + Company Publishing House, Moscow, 2007, p. 278, 279), which consists in placing the aircraft in a transport-launch container (glass), which in various versions is located on car launcher, rack launcher, suspension units of the carrier aircraft, in the mine tan bnoy launcher ship. The launch of a well-known aircraft can be provided with its placement directly on the launcher, without transport-launch cup (TPS). The start of the powder starter (launch propulsion system, CDS) is carried out after ejection (bailout of the aircraft from the TPS) with a special device that develops significant ejection forces, with the opening of the cover of the launch vehicle and the subsequent dispersal of the aircraft under the influence of thrust generated by the SDS jet nozzle. The CDS is located in the channel of the ramjet engine. Separation of the CDS is carried out by air pressure after the release of its attachment to the body and the burning of its fuel. When you start the aircraft from the silo launcher before starting the CDS open the lid of the mine.

The essential features of the prototype, which coincide with the essential features of the first version of the proposed method, are as follows: the method of launching the aircraft, which consists in placing it in the launcher, and launching its launch propulsion system with subsequent acceleration under the influence of the thrust of its jet nozzle and separation of the launch propulsion system after overclocking.

The essential features of the prototype, coinciding with the essential features of the second and third variants of the proposed method, are as follows: the method of launching the aircraft, which consists in placing it in the transport launcher, placing the transport and launcher in the launcher, launching the launcher propulsion system of the aircraft with the opening the cover of the transport and launch cup and subsequent acceleration under the action of the thrust of its jet nozzle and the separation of the starting propulsion system in after overclocking.

In known versions, during aircraft acceleration, the thrust force of the starting propulsion system acts on the plating sections (walls) of the hull through the power frames fixed to the casing on the rear (in the direction of flight) side, and the inertia forces of the power units located in the housing are on the front side design, fuel marching propulsion system, while the plating sections are loaded with compressive stress. Since thin-walled shells under the action of compressive stresses are prone to loss of stability (they can collapse, crease), it is necessary to increase their thickness and (or) the number and mass of structural elements (frames, stringers) that strengthen the shell, which increases the mass of aircraft structural elements, therefore, it is necessary increase in fuel mass and the design of the starting propulsion system, which provides acceleration of the aircraft. For the ejection of aircraft from the TPS, a special device is required that develops significant ejection forces.

The technical result to which the invention is directed is to reduce the mass of the aircraft structure, reduce the launch load on the launcher and simplify the design of the launcher.

To achieve the named technical result in the first embodiment of the method of launching an aircraft, which consists in placing it in the launcher, and launching its launch propulsion system, followed by acceleration by the thrust of its jet nozzle and separating the launch propulsion system after acceleration, the launch propulsion system is fixed in the bow parts of the aircraft, and thrust is formed by at least two of its jet nozzles located on its lateral surface with the inclination of their axes n At an angle of 10-30 ° to the longitudinal axis of the aircraft, in the process of acceleration they protect the front of the aircraft behind the starting propulsion system with a fairing mounted on the starting propulsion system, and the separation of the starting propulsion system is provided under the influence of its thrust force.

To achieve the named technical result in the second version of the method of launching an aircraft, which consists in placing the aircraft in a transport launcher, placing a transport launcher in a launcher, launching a launch propulsion system of the aircraft with the opening of the lid of the transport launcher and subsequent acceleration under the thrust of its jet nozzle and the separation of the starting propulsion system after acceleration, the starting propulsion system is fixed in the axial part of the aircraft, and thrust is formed by at least two of its jet nozzles located on its lateral surface with a tilt of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, before launching the propulsion system, the aircraft is partially extended with exit nozzle block from the cavity of the transport-launch cup, during acceleration, protect the front of the aircraft behind the starting propulsion system fairing mounted on the starting engine noy installation, and separation of the starting of the propulsion system provided under the influence of its traction.

To achieve the named technical result in the third embodiment of the method of launching an aircraft, which consists in placing it in a transport launcher, placing a transport and launcher in a launcher, launching a launch propulsion system of an aircraft with opening the lid of the transport launcher and subsequent acceleration under action thrust of its jet nozzle and separation of the starting propulsion system after acceleration, the starting propulsion system is fixed in the bow of the fly of the aircraft, and the thrust is formed by at least two of its jet nozzles located on its lateral surface with a tilt of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, provide partial placement of the aircraft in the launch vehicle with an external arrangement jet nozzles, in the process of acceleration, protect the front of the aircraft behind the starting propulsion system fairing mounted on the starting propulsion system, and the separation of the starting propulsion system bespechivaet under the influence of its traction. To reduce the thermal effect of jet jets on the aircraft when using a silo launcher, a silo launcher is used with the shaft cover open, and before starting the launch propulsion system, the transport and launch cup is partially extended from the shaft of the mine with the jet nozzles exiting outward.

Additionally, in each variant of the proposed method, to increase the safety of the launch pad or launch vehicle with a vertical launch of the aircraft, the lateral component of the thrust force is formed by tilting the jet nozzles at various angles.

Distinctive features of the first proposed variant of the LA launch method is that the starting propulsion system is fixed in the bow of the aircraft, and thrust is formed by at least two of its jet nozzles located on its side surface with an inclination of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, in the process of acceleration, they protect the front of the aircraft behind the starting propulsion system with a fairing mounted on the starting propulsion system, and the start compartment howling propulsion system provide under the influence of its traction.

Distinctive features of the second proposed variant of the LA launch method is that the starting propulsion system is fixed in the bow of the aircraft, and thrust is formed by at least two of its jet nozzles located on its side surface with an inclination of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, before starting the launch propulsion system, a partial extension of the aircraft is provided with the nozzle block leaving the cavity of the launch vehicle in the process acceleration protect the front of the aircraft behind the starting propulsion system fairing mounted on the starting propulsion system, and the separation of the starting propulsion system is provided under the influence of its traction.

Distinctive features of the third proposed variant of the LA launch method is that the starting propulsion system is fixed in the bow of the aircraft, and thrust is formed by at least two of its jet nozzles located on its side surface with an inclination of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, provide partial placement of the aircraft in the transport-launch cup with the external location of the jet nozzles, during acceleration protect the front of the aircraft of the device for starting propulsion fairing fixed to start the propulsion system and the separation of the starting of the propulsion system provided under the influence of its thrust; a silo launcher is used with the opening of the silo cover, while before starting the launcher propulsion system, the transport and launch cup is partially extended from the cavity of the mine with the jet nozzles going out.

In addition, additional distinctive features for each proposed variant of the LA launch method is that by tilting the jet nozzles at different angles, they form a lateral component of the resulting thrust force.

Due to the presence of these distinctive features, together with the known ones, the following technical result is achieved: in the total mass of the aircraft, the mass and volume of structural elements ensuring its strength decreases, the safety of the launch pad or launch vehicle during vertical launch of the aircraft increases, the reliability of the launch increases, the weight and requirements decrease to the launcher, eliminates the impact of recoil force on the launcher at startup.

The proposed technical solution can be used in space and defense technology to reduce the mass of the aircraft, increase the safety and reliability of the launch of the aircraft, expand the environmental parameters that limit the launch.

The essence of the proposed solution is illustrated by drawings, figures 1-4.

Figure 1 shows the design of the aircraft placed on the launcher.

Figure 2 presents the design of the aircraft, placed in the transport-launch cup, equipped with a device for partial extension of the aircraft from it, with the exit of the nozzle block from its cavity and placed in the silo launcher.

Figure 3 presents the design of the aircraft shown in figure 2 in a position with a partially extended aircraft from the cavity of the transport-launch cup.

Figure 4 presents the design of the aircraft, partially placed in the transport-launch cup with the location of the nozzle block of the starting propulsion system over the cover of the transport-launch cup, which is placed in a shaft launcher equipped with a device for its partial extension.

The drawings show an unmanned aerial vehicle, comprising a housing 1 with a power casing 2, power frames 3 and 4 attached to the casing of the housing 1, and a starting propulsion system 5 mounted on the power frame 3 by means of a fixing device 6 configured to be unlocked, and a control system 7 communicated with the mounting device 6. The starting propulsion system 5 is located in the front of the housing 1 and is equipped with a nozzle block 8 containing at least two jet nozzles 9 and 10 located on its lateral surface with an inclination of the longitudinal axis of each jet nozzle at an angle of 10-30 ° to the longitudinal axis Housings 1. The longitudinal axis of the jet nozzles 9 and 10 are inclined to the longitudinal axis of the housing 1 at various angles, in the range of 10-30 °. The output sections 11 and 12, respectively, of the jet nozzles 9 and 10 are beveled to the outer sides at an angle of 10-75 ° to a plane perpendicular to the longitudinal axis of each nozzle. As an option, FIG. 1, the aircraft is located in the launcher 13 and is equipped with a protective fairing 14 of the front of the housing 1 behind the starting propulsion system 5, made of heat-resistant material. The protective cowl is attached to the starting propulsion system 5 under its jet nozzles 9 and 10 of the nozzle block 8. The protective cowl 14 is coated with a heat-protective coating 15. The starting engine 5 is equipped with a starting device 16. The starting device 13 is equipped with a control panel 17 in communication with the control system 7 and a starting device 16. The power sheathing 2 of the housing 1 is equipped with reinforcing power elements 18. A sustainer propulsion system 19 with a starting device 20 connected to the system 7 is fixed to the power frame 4 management. As an option, FIG. 2, the aircraft is placed in the transport-launch cup (TPS) 21 with an opening lid 22. The TPS 21 is equipped with an aircraft extension 23 with the exit of the nozzle block 8 from its cavity. The aircraft extension device 23 comprises a drive 24 and a crossarm 25 on which the housing 1 is mounted. TPN 21 is located in a silo launcher 26 provided with a cover 27, a device for opening it 28 and a control panel 29. As an option, FIG. 4, the protective cowl 14 may be the cover of the TPS 21, and the shaft installation 26 is equipped with a device 30 for partial extension of the aircraft from the cavity of the shaft 26, which is equipped with a drive 31 in communication with the control panel 29.

и $$R_{10}^{"}$$

сил R₉ и R₁₀ тяги сопел 9 и 10, отклоняющая результирующую силу R_TΣ тяги на угол β от вертикали, см. фиг.1. Корпус 1, ускоряясь в направлении R_TΣ, смещается также и в боковом направлении от места старта, поэтому при незапуске маршевой двигательной установки 23 падение ЛА не приведет к повреждениям корабля-носителя или наземного стартового комплекса. Выполнение выходных сечений 11 и 12, соответственно, реактивных сопел 9 и 10, скошенными в наружные боковые стороны под углом 10-75° к плоскости, перпендикулярной оси соответствующего сопла, приводит к укорачиванию длины каждого сопла 9 и 10 с наружной боковой стороны и обеспечивает более раннее расширение реактивной струи в боковую от корпуса 1 сторону, реактивная струя дополнительно отодвигается на большее расстояние от обшивки 2 и меньше ее нагревает. При углах скоса меньше 10° отклонение струи несущественно, а при углах больше 75° существенно увеличивается масса реактивных сопел 9 и 10. Обтекатель 14, выполненный из термостойкого материала, защищает от перегрева переднюю часть корпуса 1, где располагается система 7 управления и система наведения ЛА (на чертеже не показана). Теплозащитное покрытие 15 уменьшает температуру нагрева обтекателя 14 и дополнительно уменьшает температуру нагрева передней части корпуса 1 и системы 7 управления. В случае возмущающего воздействия на корпус 1 пусковой установки 13, вследствие динамического их взаимодействия при выходе корпуса 1 или порыва ветра, приведшего к повороту корпуса 1 в автономном полете ЛА вокруг центра тяжести (ЦТ, см. фиг.1) на угол α, проекция $$R_g^{"}$$

гравитационной силы тяжести R_g на ось, перпендикулярную новому положению продольной оси корпуса 1, создает вращающий момент относительно точки приложения суммарной силы тяги R_TΣ реактивных сопел 9 и 10, возвращающий корпус 1 в положение, близкое к вертикальному. В отличие от прототипа, у которого при повороте корпуса 1 на угол α вокруг центра тяжести проекция $$R_g^{"}$$

создает момент относительно хвостовой части корпуса 1, увеличивающий угол поворота α. Таким образом, в предлагаемом устройстве обеспечивается стабилизация положения корпуса 1 при стартовом разгоне, что повышает надежность старта и снижает требование по жесткости пусковой установки 17, следовательно, обеспечивает возможность упрощения ее конструкции и уменьшения ее массы. Запас топлива стартовой двигательной установки 5 выбирается таким, чтобы необходимый разгон корпуса 1 обеспечивался до момента полного выгорания топлива, при этом система 7 управления ЛА задействует расфиксацию устройства 6 крепления и при воздействии тяги R_TΣ обеспечивается быстрое удаление стартовой двигательной установки 5 от корпуса 1. Благодаря тому что струи реактивных сопел 9 и 10 не воздействуют на транспортно-пусковой стакан 13, устраняется воздействие силы отдачи на пусковую установку 17 при старте.The first variant of the method according to claims 1 to 2 of the formula is implemented as follows. To start the aircraft from the remote control 17, figure 1, the control is activated starting device 16, ensuring the launch of the starting propulsion system 5. Under the action of the total thrust (R _TΣ , see _figure 1) of the jet nozzles 9 and 10, the starting propulsion system 5 together with the housing 1 moves with acceleration, determined by the ratio of R _TΣ to the weight of the aircraft, when the housing 1 leaves the launcher 13 and in autonomous flight of the aircraft. During the starting acceleration of the housing 1, the thrust force R _TΣ is transmitted through the frame 3 to the upper part of the casing section 2 between the power frames 3 and 4, and the force R _{And the} inertia of the main propulsion system 19 mounted on the frame 4 is transmitted to the lower part of the casing section 2 and equal to the product of the mass of the marching propulsion system 19 by the value of the starting acceleration of the hull 1. The forces R _TΣ and R _And stretch (straighten) the skin section 2 between the frames 3 and 4, which, unlike the prototype, where the traction and inertia forces act towards each other compressing similar th section of the skin. Due to the stretched state of the casing section 2 between the frames 3 and 4, the dynamic stability (critical fracture stress) of the casing 2 increases with elastic vibrations of the casing 1 during flight of the aircraft, therefore, the required number and mass of power elements 22 and / or the thickness of the casing can be reduced. Similarly, for other compartments of the housing 1 (fuel, instrument, cargo, not shown in the drawing). By reducing the total mass of structure 1, the following possibilities appear: while maintaining the mass of the starting propulsion system 5, reduce the acceleration time of the hull 1 or increase the mass of fuel of the propulsion engine 23 and the flight range of the aircraft; while saving time, the acceleration of the housing 1 reduce the mass of the starting propulsion system 5. At angles of inclination of the longitudinal axes of the jet nozzles 9 and 10 less than 10 °, the jet of high-temperature gases leaving them is too close to housing 1, which can lead to overheating of the casing 2, and with these angles greater than 25 °, the longitudinal component of the thrust R _TΣ , accelerating the housing 1, will be less than 90% of the total thrust of the jet nozzles 9 and 10. Due to the different angles of inclination of the longitudinal nozzles 9 and 10, a horizontal projection difference is formed $${\mathrm{<figure-callout\; id="9"\; label="R"\; filenames="00000007.png"\; state="\{\{state\}\}">R</figure-callout>}}_9^{"}$$

and $${\mathrm{<figure-callout\; id="10"\; label="R"\; filenames="00000005.png,00000006.png"\; state="\{\{state\}\}">R</figure-callout>}}_{10}^{"}$$

thrust forces R ₉ and R _{10 of} the nozzles 9 and 10, deflecting the resulting thrust force R _TΣ at an angle β from the vertical, see _figure 1. The hull 1, accelerating in the R _TΣ direction _, is also shifted laterally from the launch site, so if the main propulsion system 23 does not start, the aircraft’s fall will not cause damage to the launch vehicle or the ground launch complex. The implementation of the output sections 11 and 12, respectively, of the jet nozzles 9 and 10, beveled to the outer sides at an angle of 10-75 ° to the plane perpendicular to the axis of the corresponding nozzle, leads to a shortening of the length of each nozzle 9 and 10 from the outer side and provides more early expansion of the jet stream to the side of the housing 1 side, the jet stream is additionally moved to a greater distance from the casing 2 and heats it less. At bevel angles of less than 10 °, the deviation of the jet is not significant, and at angles of more than 75 ° the mass of the jet nozzles 9 and 10 increases significantly. A cowl 14 made of heat-resistant material protects the front of the housing 1, where the control system 7 and the aircraft guidance system is located, from overheating (not shown in the drawing). The heat-shielding coating 15 reduces the heating temperature of the fairing 14 and further reduces the heating temperature of the front of the housing 1 and the control system 7. In the case of a disturbing effect on the launcher 1 housing 13, due to their dynamic interaction at the exit of the housing 1 or a gust of wind that led to the rotation of the housing 1 in an autonomous flight of the aircraft around the center of gravity (CT, see figure 1) at an angle α, projection $$R_g^{"}$$

gravitational gravity R _g on the axis perpendicular to the new position of the longitudinal axis of the housing 1, creates a torque relative to the point of application of the total thrust force R _{TΣ of the} jet nozzles 9 and 10, returning the housing 1 to a position close to vertical. In contrast to the prototype, in which, when the housing 1 is rotated through an angle α around the center of gravity, the projection $$R_g^{"}$$

creates a moment relative to the rear of the housing 1, increasing the angle of rotation α. Thus, the proposed device provides stabilization of the position of the housing 1 during starting acceleration, which increases the reliability of the launch and reduces the requirement for the rigidity of the launcher 17, therefore, provides the opportunity to simplify its design and reduce its weight. The fuel supply of the starting propulsion system 5 is selected so that the necessary acceleration of the hull 1 is ensured until the fuel is completely burned out, while the aircraft control system 7 activates the fixing device 6 and, when exposed to the traction R _{TΣ, the} starter propulsion system 5 is quickly removed from the housing 1. Thanks the fact that the jets of the jet nozzles 9 and 10 do not affect the transport and launch cup 13, eliminates the impact of the recoil force on the launcher 17 at startup.

The second variant of the method according to claims 3 to 4 of the formula, FIGS. 2 and 3, is implemented similarly to the first embodiment. The difference lies in the fact that before the launch operations are completed, the aircraft is located in the TPS 21 without contacting the environment at all stages of operation, including storage, loading, transportation, being on the launcher, for example, shaft 26, which reduces the likelihood of accidental damage to the aircraft and increases its service life. Cover 22 TPS 21 can be made discharged, hinged, breakthrough or destroyed when the aircraft is pulled out of the TPS. To start, in addition, from the remote control 29, the device 28 is activated, ensuring the opening of the cover 27, then the drive 24 of the device 23 of the partial extension of the aircraft is activated, ensuring the exit of the jet nozzles 9 and 10 of the nozzle block 8 from the cavity of the TPS 21, see Fig. 3, which prevents overheating of the housing 1 by high-temperature jets of gases from jet nozzles 9 and 10 until the aircraft leaves the TPS 21. When placing the TPS in the silo launcher 26, the device 23 partially extends the aircraft from the cavity of the TPS 21 also provides the possibility of extension su- nozzles 9 and 10 outside of the silo 26, which provides the possibility of increasing its life.

The third variant of the method according to claims 5 to 7 of the formula, FIG. 4, is implemented similarly to the second embodiment. The difference is that due to the fact that the protective fairing 14 is the cover of the TPS 21, when the aircraft starts, high-temperature gases from the jet nozzles 9 and 10 do not enter the cavity of the TPS 21, so there is no need to equip each TPS 21 with an extension device 23. When starting from the automobile or rack launcher, not shown in the drawings, TPN 21 is in a stationary position, and to ensure the launch of the aircraft from the silo launcher 26, the drive 31 is activated and the device 30 provides a partial extension of the transport -puskovogo cup cavity of the output shaft with outwardly jet nozzles 9 and 10.

Claims (7)

1. The method of launching the aircraft, which consists in placing it in the launcher, starting its launch propulsion system, followed by acceleration under the influence of the thrust of its jet nozzle and separating the launch propulsion system after acceleration, characterized in that the launch propulsion system is fixed in the nose of the aircraft , and thrust is formed by at least two of its jet nozzles located on its lateral surface with a tilt of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft ATA, during acceleration, they protect the front of the aircraft behind the starting propulsion system with a fairing mounted on the starting propulsion system, and the separation of the starting propulsion system is provided under the influence of its thrust. 2. The method of launching an aircraft according to claim 1, characterized in that the lateral component of the thrust force is formed by tilting the jet nozzles at various angles. 3. The method of launching an aircraft, which consists in placing it in a transport launch tube, placing a transport launch tube in a launcher, launching a launch propulsion system of an aircraft with opening the lid of the transport launch tube and subsequent acceleration under the influence of the thrust of its jet nozzle and separation the starting propulsion system after acceleration, characterized in that the starting propulsion system is fixed in the bow of the aircraft, and thrust is formed, at least re, with its two jet nozzles located on its lateral surface with a tilt of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, before launching the launch propulsion system, the aircraft is partially extended with the jet nozzles leaving the cavity of the transport-launch canister, in during the acceleration process, the front part of the aircraft is protected behind the starting propulsion system by a fairing mounted on the starting propulsion system, and both the separation of the starting propulsion system are both ensures, under the influence of its traction. 4. The start method according to claim 3, characterized in that the lateral component of the thrust force is formed by tilting the jet nozzles at various angles. 5. The method of launching the aircraft, which consists in placing it in the transport launch tube, placing the transport launch tube in the launcher, starting the launch propulsion system of the aircraft with opening the lid of the transport launch tube and subsequent acceleration under the influence of the thrust of its jet nozzle and separation the starting propulsion system after acceleration, characterized in that the starting propulsion system is fixed in the bow of the aircraft, and thrust is formed, at least re, its two jet nozzles located on its lateral surface with a tilt of their axes at an angle of 10-30 ° to the longitudinal axis of the aircraft, provide partial placement of the aircraft in the transport-launch cup with the external location of the jet nozzles, protect the front part during acceleration the aircraft behind the starting propulsion system fairing mounted on the starting propulsion system, and the separation of the starting propulsion system provide under the influence of its traction. 6. The starting method according to claim 5, characterized in that by tilting the jet nozzles at different angles, a lateral component of the resulting thrust is formed. 7. The starting method according to claim 5 or 6, characterized in that a silo launcher is used with the opening of the shaft cover, while before starting the launcher propulsion system, the transport-launch cup is partially extended from the shaft of the mine with the jet nozzles going out.

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