RU2725129C1 - Device for protection against ingress of water into inner space of nozzle of solid-propellant engine of rocket carrier with mortar start circuit from underwater position and check valve - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: present invention relates to rocket engineering and can be used in development of design of protection against ingress of water into inner volume of nozzle of starting solid-fuel engine of rocket carrier with mortar start-up circuit from underwater position. Proposed device comprises elastic membrane arranged inside nozzle between critical section plug and rocket launch pad, tightly fixed along the nozzle edge, made in the form of a canopy supported by the ribbed dome frame, in the vertex of which there is a check valve connecting the sealed cavity Wwith volume of 0.25…0.35 of the complete inner volume of the nozzle from the plug to the cut with inner cavity of the nozzle above the cartridge pressure accumulator (CPA). Membrane is fixed along the nozzle edge from the outside with a compression ring with an unlocking element actuated by a command from the rocket carrier control system. Proposed check valve is designed to provide for the control time of the required filling of CPA start-up gases from the launching tube of the sealed chamber Win gases sufficient for axial displacement of the ribbed frame with eversion of the elastic membrane.EFFECT: disclosed invention will make it possible to simplify the nozzle protection device design, to increase its reliability in operation and to reduce costs for autonomous development.2 cl, 7 dwg

Description

The present invention relates to rocket technology and can be used to develop a design for protecting the nozzle of the starting solid propellant engine from water entering the internal volume of the nozzle when the rocket “emerges” and “collapses” the air cavity behind the stern of the rocket carrier.

The known design of "Missile launcher with mortar launch from underwater position" (see US Pat. RU No. 2351890, 2007), adopted by the authors as a prototype, containing an engine with a tail section and a nozzle with a plug, in the cavity of the nozzle of which a gas generator (powder pressure accumulator, launch pad), mounted on the bottom of the launch tube, over which there is a device to protect against water entering the internal volume of the nozzle of the solid rocket engine of the rocket launcher with a mortar launch scheme from the underwater position, made in the form of an elastic heat-resistant gas-tight membrane in the form of a tent, located inside nozzles between the critical section plug and the powder pressure accumulator (PAD) of the rocket launch and hermetically fixed along the nozzle exit. The area of the membrane disk is equal to the area of the circle at the nozzle exit, which (the membrane) is stretched uniformly along the perimeter with the help of heat-resistant cables mounted on the membrane surface and connected to twisted tension springs attached to the frame outside the nozzle (through guide tides with holes located on the exit nozzle). The products of combustion of fuel PAD (T _ps ~ 2600 K) when launched in the pipe enter the tail section and into the nozzle above the membrane. As soon as the lower tail section of the tail section is above the PAD when the rocket moves in the tube, the power membrane occupies a horizontal position, overlaps the nozzle section and is held in this position under the influence of the tension force of the coil springs and cables. In this case, the gas pressure in the nozzle volume ~ is equal to the pressure inside the launch tube during rocket movement.

For a conical-shaped membrane variant (see FIG. 8, Pat. RU No. 2351890, 2007), a heat-resistant spring (for example, from a niobium alloy) 41 is attached to the center of the nozzle plug 40, which is connected to the top of the conical membrane at the intersection of the lines. The spring 41 may be located inside the corrugated tube-casing (for example, made of rubber) for additional thermal protection of the spring from the effects of high-temperature combustion products of the powder of a powder gas generator.

When a rocket carrier leaves the pipe-shell section, the pressure in the nozzle cavity is released through the annular gap between the membrane perimeter and the nozzle section inner diameter, and as it moves toward the water surface, the pressure in the nozzle cavity is equal to the hydrostatic pressure at the moment.

When the rocket’s starting engine starts above the surface of the water, the membrane is torn to pieces from the force of the impact of the solid-propellant charge flowing out from the nozzle of the combustion product and gradually burns out in a hot gas stream for several seconds.

The disadvantage of this device is the occurrence of loads when opening the nozzle plug during engine start until the membrane is destroyed.

In addition, during the entire life of the rocket, the membrane springs are in a stretched state and a long period (15 ... 20 years) will affect the decrease in the reliability of this system. In addition, the autonomous development of such a design of the protection device requires considerable labor and time, i.e. - an expensive event.

The objective of the proposed technical solution is to simplify the design of the protection device, reduce the load on engine startup, increase the reliability of its operation and significantly reduce the cost of mining.

This problem is solved due to the fact that in the protection device (Fig. 1) from water entering the internal volume of the nozzle of the solid rocket engine of the rocket launcher with the mortar launch circuit from the underwater position, containing an elastic heat-resistant gas-tight membrane located inside the nozzle between the critical section plug and the powder the pressure accumulator (PAD) of the rocket launch and hermetically fixed at the nozzle exit, the membrane is made in the form of a dome over which a power, rib frame is mounted, fastened to it, at the top of which a check valve is mounted, fastened to the power, rib frame and connecting the airtight cavity W _GP , formed between the membrane dome and the nozzle plug, with the internal cavity of the nozzle above the PAD, the power rib cage with the membrane is pressed against the inner cone-shaped surface of the nozzle by an annular ring with a pressure ring, while the volume of the sealed cavity W _GP is 0.25 ... 0.35 full internal volume W _c nozzle from plug to cut a, and the membrane is fixed at the nozzle exit in the form of a detachable compression ring mounted on the outside of the nozzle with a release element that is triggered by a command from the rocket launcher control system.

The non-return valve is designed to provide, for a control time, the necessary filling of launch pad PAD from the launch tube (ПТ) of the sealed cavity W _gp , limited by the walls of the nozzle plug, nozzle and elastic protective membrane of the device, in an amount sufficient to effect axial displacement of the rib cage with the protective elastic membranes.

The design of the check valve is known (Polytechnical Dictionary. / Gl. Red. Acad. A.Yu. Ishlinsky. - P 50 2nd ed. - M. Sovetskaya Encyclopedia, 1980 - 656 p., Ill.), Presented on page 223 and accepted by the authors for the prototype. The prototype includes a housing with a saddle, a shutter, between which a passage channel is formed. The throughput hole of the non-return valve of the prototype is made at the base of the housing with a saddle, is blocked by a shutter with hermetically pressing it to the housing with a saddle using a clamping spring.

According to the technical analysis of the optimal mode of filling cavities W _r gases PAD start through the check valve of the launch tube includes opening the check valve in the ignition charge PAD start (top field), and the closing of the check valve (end of fill) - during transience output missile from TP.

Based on this, the disadvantages of the non-return valve-prototype include delays in opening and closing it, associated with the inertia of the actuating elastic element of the non-return valve.

When the rocket leaves the launch tube, the delay in closing the check valve can lead to an unacceptable leakage of hot gas from the cavity W _gp and, consequently, to an overwhelming decrease in pressure in it.

These shortcomings reduce the reliability of the protection device and are systematic.

In addition, it should be noted that during storage, the operational characteristics of the elastic element of the non-return valve may deteriorate, which will negatively affect the reliability of the tight contact of the shutter with the housing with the seat of the non-return valve, that is, the reliability of the fail-safe operation of the protection device.

The objective of the invention regarding the non-return valve is to increase the reliability of its operation and the protection device as a whole by providing guaranteed opening of the non-return valve to fill the start pad gases with a start-up during the control time of the sealed cavity W _GP to the design pressure (with timely guaranteed closing of the non-return valve) in order to protect water getting inside the nozzle of a solid fuel engine with a mortar launch of a rocket carrier from an underwater position.

и равномерные кольцевые проходные сечения, высота Δ_r которых обратно пропорциональна удалению «r» их от центральной вертикальной оси обратного клапана, угол наклона оси радиального центрального сечения канала к плоскости входного отверстия обратного клапана, перпендикулярной к его центральной оси, ϕ_к=10°…13°, половина угла конусности кольцевого входа в пропускной канал Θ_вх=60°…70°, ширина кольцевых стенок затвора h_з и седловины h_c, образующих конический кольцевой вход в пропускной канал, составляет (0,4…0,6)⋅Δ_вхк - высоты входного кольцевого сечения пропускного канала, причем высота выходного кольцевого сечения пропускного канала определяется по формуле

расстояние между входом в кольцевой пропускной канал обратного клапана и центральной его осью равно r_вхк=(0,5…0,55) d_вх, а

гдеThe problem is solved due to the fact that in the known non-return valve comprising a housing with a saddle and a shutter, between which a passage channel is formed, the housing includes a perforated cover mounted with fastening on the housing with a saddle, and the valve passage is formed by an external profiled annular valve wall and internal profiled annular wall of the housing with a saddle, has a relative radial length

and uniform annular passage sections, the height Δ _{r of} which is inversely proportional to the distance "r" them from the central vertical axis of the check valve, the angle of inclination of the axis of the radial central section of the channel to the plane of the inlet of the check valve perpendicular to its central axis, ϕ _to = 10 ° ... 13 °, half the taper angle of the annular entrance to the passage channel Θ _in = 60 ° ... 70 °, the width of the annular walls of the shutter h _h and the saddle h _c forming a conical ring entrance to the passage channel is (0.4 ... 0.6) ⋅ Δ _vhk - the height of the input annular section of the passage channel, and the height of the output annular section of the passage channel is determined by the formula

the distance between the entrance to the annular pass-through channel of the _non- return valve and its central axis is r _vhk = (0.5 ... 0.55) d _vh , and

Where

Δ _vhk is the height of the inlet annular section of the check valve passage channel;

μ _I - the coefficient of gas flow entering the check valve through its inlet;

μ _to - the coefficient of gas flow entering the annular passage channel of the check valve through its annular conical inlet;

d _I - the diameter of the inlet of the check valve;

r _vhk is the distance from the central vertical axis of the check valve to the inlet annular section of the passage channel;

r _o - the distance from the Central vertical axis of the check valve to the output annular section of the passage channel.

The proposed device is illustrated by drawings.

In FIG. 1 schematically shows the protective device of the nozzle of the starting engine in the initial state of the rocket. (The position of the launch pad at the bottom of the launch tube is shown conditionally).

In FIG. 2 schematically shows the intermediate position of the protective device during the eversion of the membrane after the rocket leaves the launch tube.

In FIG. 3 shows a diagram of a protective device with an inverted membrane when the rocket leaves the water.

In FIG. 4 shows a vertical section through the check valve in the closed state (initial and final state).

In FIG. 5 shows a vertical section through a check valve in an open state.

In FIG. 6 shows a check valve shutter.

In FIG. 7 shows the basic geometric parameters of the check valve passage channel.

The proposed device against water ingress into the internal volume of the nozzle of a solid propellant rocket launcher with a mortar start circuit from an underwater position contains (see Fig. 1) an elastic, heat-resistant (based on carbon fabric) placed in the nozzle 1 with a plug 2, gas-tight membrane 3, dome 4, which is externally fixed to the power rib frame 5 with glue. In the center of the membrane dome, a non-return valve 6 is installed to fill the nozzle volume between the nozzle plug and the surface of the dome 4 by the PAD 7 charge combustion products installed on the bottom 8 of the launch tube 9 on the uprights 10 and having a reflector 11 of the PAD 7 charge combustion products into the volume of the nozzle and the launch pipe. The annular base of the rib cage 5 with the adjacent membrane 3 is tightly pressed against the conical surface of the nozzle by a pressure-sensitive split heat-resistant metal ring 12, in the context of which (between the ends) a threaded ring clamp regulator 13 is installed.

At the nozzle exit, the membrane is secured externally by means of a compressive force ring 14 with a release 15 (with a squib connected to the missile control system).

и равномерные кольцевые проходные сечения, высота Δ_r которых обратно пропорциональна удалению «r» их от центральной вертикальной оси обратного клапана 6. Угол наклона оси радиального центрального сечения канала к плоскости входного отверстия d_вх обратного клапана, перпендикулярной к его центральной оси, ϕ_к=10°…13°. Половина угла конусности кольцевого входа в канал Θ_вх=60°…70°, ширина кольцевых стенок затвора h_з и седловины h_c, образующих конический кольцевой вход в канал, составляет (0,4…0,6)⋅Δ_вхк - высоты входного кольцевого сечения канала. Высота выходного кольцевого сечения канала определяется по формуле

расстояние между входом в кольцевой канал обратного клапана и центральной его осью равно r_вхк=(0,5…0,55) d_вх, а

гдеThe check valve 6 (see Fig. 4, Fig. 5, Fig. 6, Fig. 7) contains a housing with a saddle 16 and a shutter 17, between which a passage channel is formed. The housing with a saddle 16 is provided with a perforated cover 18, mounted with fastening on the housing with a saddle 16, in which a shutter 17 is mounted on a sliding fit. The check valve passage channel is formed by an external profiled annular wall of the shutter 17 and an internal profiled annular wall of the housing with a saddle 16, has a relative radial length

and uniform annular passage sections, the height Δ _{r of} which is inversely proportional to their distance "r" from the central vertical axis of the check valve 6. The angle of inclination of the axis of the radial central section of the channel to the plane of the inlet d _{in of the} check valve perpendicular to its central axis, ϕ _to = 10 ° ... 13 °. Half of the taper angle of the annular entrance to the channel Θ _in = 60 ° ... 70 °, the width of the annular walls of the shutter h _s and the saddle h _c forming a conical annular entrance to the channel is (0.4 ... 0.6) ⋅Δ _vhk - the height of the input annular section of the channel. The height of the output annular section of the channel is determined by the formula

the distance between the entrance to the annular channel of the _non- return valve and its central axis is r _vhk = (0.5 ... 0.55) d _vh , and

Where

Δ _vhk is the height of the inlet annular section of the check valve passage channel;

μ _I - the coefficient of gas flow entering the check valve through its inlet;

μ _to is the coefficient of gas flow entering the annular channel of the check valve through its annular conical inlet;

d _I - the diameter of the inlet of the check valve;

g _vhk - the distance from the Central vertical axis of the check valve to the inlet annular section of the channel;

r _o - the distance from the Central vertical axis of the check valve to the output annular section of the channel.

(диаметр крепления крышки). Суммарная площадь перфораций крышки 18 в виде круглых отверстий диаметром d_вых (фиг. 4), симметрично расположенных по поверхности крышки, не меньше площади входного отверстия d_вх обратного клапана.The perforated cover 18 is attached to the housing with a saddle 16 screws (not shown in Fig. 4), uniformly distributed around the circumference of the diameter

(diameter of cover fastening). The total area of perforations of the cover 18 in the form of round holes with a diameter d _o (Fig. 4), symmetrically located on the surface of the cover, is not less than the area of the inlet d _{in the} check valve.

Contact connections (see Fig. 4) between the shutter 17, the housing with the saddle 16, the integral ring of the rib cage 5 (see Fig. 1) and the membrane 3 with the closed check valve 6 ensure the tightness of the cavity W _GP .

The shutter 17 (in Fig. 4, Fig. 5 and Fig. 6) has a design associated with the design of the housing with a saddle 16, which ensures the formation of design chamber 19, an annular passage channel with uniform passage sections and a tapered annular entrance (Fig. 5 ), as well as the possibility of hermetically closing the passage channel when the shutter 17 is in contact with the housing with a saddle 16 along a ring of width H _s = 0.5 (d _nz - d _kpz ) (see Fig. 4, Fig. 6).

The prechamber 19 (Fig. 5), which includes a semi-closed shutter cavity 17 and an inner body cavity with a saddle 16 with a boundary along the plane of the inlet with a diameter d _{in of the} check valve 6, helps to equalize the flow rates of gas jets flowing into the annular passage and increases the protection of the cavity W _gp from the ingress of sea water into it when the rocket leaves the launch tube 9. The volume of the pre-chamber 19 is ~ 0.6 of the internal volume of the annular pass-through channel of the check valve 6, limited by the profiled conical walls of the shutter 17 and the housing with a saddle 16.

Здесь Δ_кср - средняя высота кольцевого проходного сечения пропускного канала:

Δ_вхк и Δ_вых - высоты входного и выходного кольцевых сечений пропускного канала.The radial length L _{k of the} annular passage channel is measured along the axis "About _to " (Fig. 7). Its relative value is

Here Δ _ksr is the average height of the annular passage section of the passage channel:

_HHC and Δ Δ _O - height of the inlet and outlet sections of annular passageway.

где const=Δ_вхк⋅r_вхк, то есть равномерные кольцевые проходные сечения пропускного канала имеют переменный зазор Δ_r между стенками затвора и седловины - обратно пропорциональный расстоянию "r" от сечения до центральной оси обратного клапана, то есть кольцевой пропускной канал сужается по высоте в радиальном направлении от его входного кольцевого сечения к выходному.The uniformity of the areas of the passage annular sections of the check valve passage channel ensures that a subsonic gas stream is formed in the channel with compression and, accordingly, with reduced static pressure before the rocket leaves the launch tube. At the same time, a calculated differential pressure is set on the shutter 17, which is necessary for timely, tight closing of the valve. The uniform annular passage sections of the passage channel are normally oriented towards the radial velocity vector of the gas flow and are realized when the relation is fulfilled (see Fig. 7):

where const = Δ _vkhk ⋅r _vkhk , that is, the uniform annular passage sections of the passage channel have a variable gap Δ _r between the walls of the shutter and the saddle - inversely proportional to the distance "r" from the section to the central axis of the check valve, that is, the ring passage channel narrows in height in the radial direction from its input ring section to the output.

The non-return valve 6 has an annular conical inlet to the passage channel formed by the widthwise normalized annular walls of the shutter h _s and the saddle h _c , which form an inlet with a design taper angle of 2Θ _in (see Fig. 5, Fig. 7).

The non-return valve 6 is installed on the solid ring of the rib cage 5, having an inner diameter d _{uk of the} installation of the valve (see Fig. 4), and is attached to it (to the ring) by screws 20. This ensures a strong and tight connection of the whole ring of the frame 5 with an elastic protective membrane 3.

(см. фиг. 7) определен с учетом рекомендации [1]: А.А. Шишков. Газодинамика пороховых ракетных двигателей. М., «Машиностроение», 1974. См. стр. 33 [1] или прилагаемую копию - использовать удлиненную трубку Борда (~10 калибров) при исследовании сжимаемости газовой струи.Parameter value line

(see Fig. 7) is determined taking into account the recommendations [1]: A.A. Bumps. Gas dynamics of powder rocket engines. M., "Mechanical Engineering", 1974. See page 33 [1] or the attached copy — use an elongated Bord tube (~ 10 gauges) when studying the compressibility of a gas stream.

According to the obtained solution of the compiled differential equation that determines the area of the annular passage section of the check valve passage channel depending on its (section) distance from the vertical axis of the check valve, for uniform ring cross sections, their heights are inversely proportional to the distances to the central vertical axis of the check valve:

The range of values [0.4 ... 0.6] ⋅Δ _{vhk of the} parameters h _s and h _c (Fig. 7) was determined using the geometrical dimensions of the subsonic part of the rotary control nozzle of the solid-fuel engine, ensuring a uniform gas flow at the end of the narrowing.

From the geometrical construction of the vertical cross section of the check valve channel, the angle ϕ _k = 10 ° ... 13 ° was determined, which provides the possibility of a conical entry into the check channel of the check valve with the same width of the annular walls of the shutter h _s and saddle h _c from the range of values [0.4 ... 0, 6] ⋅Δ _vhk (see Fig. 7).

The parameter Θ _in = 60 ° ... 70 ° (see Fig. 7) is determined from the construction of a symmetrical conical ring inlet to the check valve passage to provide the calculated reduced flow rate with compression according to equations [1] on pages 35, 81, copies are attached :

где

Where

p_овх=~p_пт; p_вых=~p_гп,

p _ovh = ~ p _pt ; p _out = ~ p _gp ,

z (λ _out ), z (λ _squ ), ƒ _cr ⋅ q (λ _squ ) are gas-dynamic functions.

(см. фиг. 5, фиг. 7) получено из условия равенства площадей «живых» сечений газового потока в входном отверстии обратного клапана и в сжатом сечении кольцевого пропускного канала.Expression for the height of the output ring section

(see Fig. 5, Fig. 7) is obtained from the condition that the areas of the "live" cross sections of the gas stream are equal in the inlet of the non-return valve and in the compressed section of the annular passage channel.

The ratio r _vhk = (0.5 ... 0.55) d _{vh was} obtained when developing the check valve chamber with a simplified algorithm for calculating and constructing an annular passage channel with a conical inlet.

The operation of the device of protection against ingress of water into the internal volume of the nozzle of a solid propellant rocket carrier engine with a mortar scheme for starting from an underwater position is as follows.

In the initial position, before starting PAD 7 start (Fig. 1), the check valve 6 is closed (Fig. 4): under the action of gravity, the shutter 17 closes the passage channel of the check valve, contacts the ring with the housing with a saddle 16 and separates the cavity W _GP filled with atmospheric air.

After ignition of the charge PAD 7 start, hot gases enter the pre-chamber 19 of the check valve 6 through an inlet with a diameter of d _in , (Fig. 4), open the check valve 6 (Fig. 5) and flow into the cavity W _GP , limited by a plug 2 of the critical section of the nozzle 1, the walls of the nozzle 1 and the dome 4 of the membrane 3.

The filling of the cavity W _GP with the gases of the launch pad falls from the moment the check valve 6 is opened until it closes immediately before the rocket leaves the launch tube 9.

As the gas cavity W _{gp is} filled with gas and pressure increases in it, a subsonic flow is established over the entire radial length of the check valve passage channel. Due to the conical entry into the annular channel of the non-return valve, the gas jet in the channel has compression, increased speed and reduced static pressure. This ensures the establishment of the calculated differential pressure on the opposite walls of the shutter 17 for the timely closing of the check valve 6.

The process of closing the check valve 6 begins when the engine approaches with a protection device to exit the launch tube 9 (see Fig. 5, Fig. 4). It includes a mode with short-term (pulsed) gas supply from the launch tube 9 to the cavity W _GP . During such a single gas supply, the shutter 17, under the action of the resulting force from the pressure difference on its walls, “closes” the check valve channel 6. “This mode with automatically repeated“ pulse ”closing of the check valve occurs when the rocket approaches the exit from the launch tube 9, when the pressure p _gp in W _{gp is} close to the total pressure at the inlet to the non-return valve and the inequality

где

Where

- площадь; m_з - масса затвора 17; g - ускорение свободного падения; а_изд - ускорение ракеты в пусковой трубе 9; р_гг - давление горячих газов у стенок затвора 17, со стороны входного отверстия обратного клапана 6,

- осевая сила давления горячих газов, препятствующая закрытию обратного клапана 6.p _gp S _nz - axial force from the pressure p _gp in the cavity W _gp ;

- area; m _s - the mass of the shutter 17; g is the acceleration of gravity; and _ed - acceleration of the rocket in the launch tube 9; p _g - the pressure of the hot gases at the walls of the shutter 17, from the inlet of the check valve 6,

- axial pressure force of hot gases, preventing the closing of the check valve 6.

The cessation of the replenishment of the W _gp cavity by hot gases and the tight closing of the check valve 6 will occur immediately after the rocket leaves the PT 9. This eliminates the leakage of hot gases from the W _gp cavity and the ingress of sea water into it.

When the rocket leaves the section of the launch tube 9, the pressure in the nozzle 1 drops sharply (~ 2 times), and the force 3 acts on the membrane 3 from the pressure drop in the volume W _GP and in the nozzle 1. This leads to the movement of the membrane with the rib cage 5 k a cut of the nozzle 1, accompanied by a gradual inversion of the membrane 3. Moving and turning out, the membrane acts on the pressure ring 12, which is shifted to a larger inner diameter of the nozzle and freely falls out of it.

As the rocket advances to the surface of the water, the membrane 3 under the action of pressure inside the volume W _gp continues to turn out, the rib frame 5 moves together with the dome 4 of the membrane 3 (see Fig. 2).

Before the rocket exits to the water surface, the membrane 3 (see Fig. 3) is completely “turned out” and the pressure inside the nozzle [in the volume W _c + (0.65 ... 0.75) W _c ] is p _rp ≈ (1.05 ... 1.1) ata. This retains the tight adhesion of the membrane 3 with the outer walls of the nozzle 1 along its slice, which ensures the absence of water inside the nozzle.

When the distance above the water surface to the nozzle exit 1 becomes equal to ~ 10 ... 20 m, the pyro cartridge in the release unit is triggered by the control system command and the inverted membrane 3 is completely disengaged with the outer walls of the nozzle 1 along its exit (compressive forces are removed from the membrane 3 with sides of the compression ring 14).

Thus, the protective membrane 3 is smoothly disconnected and there is no water inside the nozzle 1 before starting the starting engine, thereby creating standard conditions for its normal start.

The proposed technical solution will simplify the design of the nozzle protection device, increase its reliability in operation and reduce the cost of autonomous testing.

Claims (8)

1. A device for protecting against water ingress into the internal volume of the nozzle of a solid propellant rocket launcher with a mortar launch scheme from an underwater position, containing an elastic heat-resistant gas-tight membrane located inside the nozzle between the critical section plug and the powder pressure accumulator (PAD) of the rocket launch and tightly fixed at the cutoff nozzle, characterized in that the membrane is made in the form of a dome over which a power rib frame is mounted, bonded to it, at the top of which a check valve is mounted, bonded to the power rib frame and connecting the sealed cavity W _GP formed between the membrane dome and the nozzle plug, with the inner cavity of the nozzle above the PAD, the power rib cage with the membrane is pressed against the inner cone-shaped surface of the nozzle along the annular belt by the pressure ring, while the volume of the sealed cavity W _GP is 0.25 ... 0.35 of the total internal volume W _{c of the} nozzle from the plug to the cut, and fixing the membrane at the slice and the nozzle is made in the form of a detachable ring mounted outside the nozzle with a release element that is triggered by a command from the rocket launcher control system. 2. A non-return valve comprising a housing with a saddle and a shutter between which a passage channel is formed, characterized in that the housing with a saddle is provided with a perforated cover mounted with fastening on the housing with a saddle, in which a shutter is installed along a sliding fit, and a passage channel of the non-return valve formed by the outer profiled annular wall of the shutter and the inner profiled annular wall of the housing with a saddle, has a relative radial length

and uniform annular passage sections, the height Δ _{r of} which is inversely proportional to their distance "r" from the central vertical axis of the check valve, the angle of inclination of the axis of the radial central section of the channel to the plane of the inlet of the check valve perpendicular to its central axis, f _k = 10 ° ... 13 °, half the taper angle of the annular entrance to the passage channel Θ _in = 60 ° ... 70 °, the width of the annular walls of the shutter h _s and the saddle h _c forming a conical annular entrance to the passage channel is (0.4 ... 0.6) ⋅ Δ _vhk - the height of the input annular section of the passage channel, and the height of the output annular section of the passage channel is determined by the formula

the distance between the entrance to the annular passage channel of the _non- return valve and its central axis is r _vhk = (0.5 ... 0.55) d _vh , and

Where Δ _vhk is the height of the inlet annular section of the check valve passage channel; μ _I - the coefficient of gas flow entering the check valve through its inlet; μ _to - the coefficient of gas flow entering the annular passage channel of the check valve through its annular conical inlet; d _I - the diameter of the inlet of the check valve; r _vhk is the distance from the central vertical axis of the check valve to the inlet annular section of the passage channel; r _o - the distance from the Central vertical axis of the check valve to the output annular section of the passage channel.

Images