RU2438033C1 - Solid-propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: solid-propellant rocket engine includes housing with channel charge of all-round burning, which is arranged in it, film-type igniter, explosive cartridge installed in front cover of engine, and membrane distributor. Film-type igniter is installed between explosive cartridge and membrane distributor, and in membrane distributor there made are peripheral holes oriented in the gap between engine housing and external surface of the charge. Film-type igniter is tightly fixed by means of adhesive composition on the basis of thermoplastic elastomer and indene coumarone resin to membrane distributor. Along explosive cartridge in membrane distributor there is central throttle hole the diameter of which is 0.3…0.5 of diameter of directed flame jet of combustion products of explosive cartridge.

EFFECT: invention allows improving ignition reliability of solid propellant charge.

4 cl, 7 dwg

Description

The invention relates to the field of rocket technology and can be used in the design, development and manufacture of solid propellant rocket engines (solid propellant rocket engines), solid fuel gas generators (GG), solid-fuel on-board actuators (BTIM) rockets, ejection devices (KU) for emergency rescue systems (CAC) ) pilots and other missile systems equipped with a separate charge of solid rocket fuel (TRT).

One of the urgent tasks of improving solid propellant rocket engines, gas generators, BTIM and other rocket systems is to increase the reliability and efficiency of ignition of solid rocket fuel (TRT) charge and to reach the operating mode of these devices in a given, very small period of time.

Known constructions of solid propellant rocket motors with plug-in charges TRT (analogues) according to US Pat. RU 2247254, RU 2286475, RU 2336430 and the design of film ignitors according to US Pat. RU 2170842, RU 2212557. The solid propellant rocket motors according to the indicated patents, together with the use of film structures of igniters, provide mainly high reliability of ignition of the solid propellant charge in the required period of time and improve the overall weight and size characteristics of the solid propellant rocket motor in general.

However, a significant drawback of the above-mentioned solid-propellant solid-propellant structures is the lack of reliable fixation (fixing) of the film igniter in the volume of the solid-propellant solid propellant chamber (CC). Lack of fixing of the igniter can lead, under the influence of the combustion products (PS) of the pyro cartridge, to its movement inside the rocket engine and subsequent abnormal operation, namely, to delay the ignition of the igniter and fail to provide the time requirement for the solid propellant rocket to go to operation due to energy losses due to deformation (crushing) and moving the film housing of the loose igniter. To eliminate these disadvantages, it is proposed to carry out the bonding (gluing) of the film igniter with a dissecting membrane as a part of the solid propellant rocket constructions (Fig. 1, Fig. 2). This contributes to the regular movement of the products of combustion of the igniter along the burning surfaces of the charge and allows, when the igniter is triggered, to ensure, by fastening the igniter with the diaphragm-divider, effective ignition of the actual ignitor sample. The latter is achieved both due to the movement of the force of the flame of the igniter in the axial direction (figure 3), and in the form of a reflected flow of the PS of the igniter in radial directions. This method of ignition of the ignitor’s hinge allows to ensure the minimum time (0.001 ... 0.003 s) for operating the solid propellant rocket engine and solid fuel power devices (primarily GG and KU for rockets and SAS pilots).

The prototype of the patented technical solution adopted the invention according to US Pat. No. 2227254, application No. 2003123209 of 07.22.03, IPC F02K 9/95.

An object of the invention is the development of the design of the solid propellant solid propellant rocket motor, providing increased reliability of ignition of the charge of the solid propellant rocket and the output of the solid propellant rocket rocket to the operating mode.

The technical result of the invention is (Figure 1) in the development of the design of a rocket engine with an additional charge of solid fuel, including a housing (1) with a channel charge (2) for all-round combustion, a film igniter (3), a pyro cartridge (7), a membrane divider (5) and front cover (6). In this case, the igniter is installed in the front cover, and the film igniter is between the igniter and the diaphragm-divider. The membrane-divider is fixed between the igniter and the front end of the TPT charge, and the igniter is bonded (glued) to the membrane-divider with glue based on thermoplastic elastomer (TEP) and indencumarone resin (ICS). In the membrane-divider, peripheral holes (9) are made, oriented in the gap between the outer surface of the charge and the solid propellant rocket housing. A central throttling (10) hole (Dros.), The diameter of which is 0.3 ... 0.5 of the diameter of the force of the squib (Dfors.), Can be made along the axis of the squib in the divider membrane.

When the force (jet) of the PS pyro cartridge (7) acts on the film igniter (3), the force “cuts through” the igniter shell, setting fire to the ignitor hitch (4) along the axial path. Encountering a diaphragm-divider (5), the force of the PS pyro cartridge changes the direction of movement in radial directions (Figure 3), spreading over the entire volume of the igniter, which allows you to efficiently ignite the entire mass of the igniter directly in the main volume of the solid propellant rocket engine. This, in turn, makes it possible to purposefully and uniformly along the charge perimeter (2) direct joint high-temperature PSs of the pyrocartridge and igniter, realized in the form of gas and condensed phases, through the peripheral (9) gap (openings) of the dissecting membrane mainly onto the outer surface of the TRT charge all-round combustion (i.e., the maximum area of charge burning compared to the surfaces of the channel and the ends). In this case, the peripheral gap can be realized in the form of gap sections between the contour of the diaphragm-divider and the surface of the housing, and the diaphragm-divider itself is made of steel.

The essence of the invention lies in both the most efficient use (realization) of the energy of the ignition of the igniter, and in increasing the reliability of ignition of the ignition of the igniter (4), ignited by the igniter of the igniter, due to the movement of the products of combustion of the igniter in both axial and radial directions in the ignitor body of the solid propellant rocket igniter ( Figure 2). The indicated effect is also achieved by reducing the damping of the igniter body and eliminating the movement of the ignitor at the installation site in the solid propellant rocket motor, tightly bonding it to the dissecting membrane. This ensures the use of energy of combustion products of PP with minimal losses, mainly directly on ignition of a sample of the igniter composition of the igniter.

In the absence of tight bonding (bonding) of the film igniter with the diaphragm-diaphragm, the igniter can move and “actively” deform both under the influence of the force of the squib and its own PS. This significantly reduces the share of PS energy of the squib and igniter, which goes directly to ignition of the TRT charge itself. The ignition efficiency in the patented design of the TPT charge is also achieved by uniformly supplying PS (igniter + pyro cartridge) mainly to the outer surface of the charge through the peripheral holes of the dissecting membrane. At the same time, the fastening of the igniter with the dissecting membrane is performed using glue based on TEP and IKS, which ensures guaranteed operation of the solid-propellant solid-propellant in the temperature range of ± 50 ° C (permissible shear stresses on the polymer-steel-film contact are 2.4 ... 4.9 kgf / cm ² ). The supply of flammable PS to the outer surface of the charge can be carried out by performing slotted sections between the contour of the diaphragm-divider and the surface of the housing.

When using large elongation charges in solid propellant rocket motors, a central throttling hole (Dros.) Can be made in the dissecting membrane, the diameter of which is 0.3 ... 0.5 of the diameter of the jet of the PS (Dfors) squib. This makes it possible to improve the ignition of a charge of large elongation. Moreover, with a diameter of Ddros. less than 0.3 Dfors, an effective “connection” of the burning surface of the channel to the ignition of the charge is not achieved, but with Ddros. more than 0.5 Dforsa, the likelihood of tensile radial stresses in the charge increases when the solid propellant rocket enters the regime that is dangerous from the point of view of its functioning (charge destruction is possible).

The invention is illustrated graphic materials.

Figure 1 General view of the patented design (with a volume igniter according to US Pat. RU 2212557),

where 1 is the body of the solid propellant rocket engine;

2 - charge TRT;

3 - igniter;

4 - hitch igniter composition;

5 - membrane-divider;

6 - front cover;

7 - a squib;

8 - adhesive composition;

9 - peripheral holes in the membrane-divider;

10 - Central throttling hole.

Figure 2 General view of the patented design (with a "batch" igniter according to US Pat. RU 2170842).

Figure 3 The nature of the movement of the PS at the time of launch of the taxiway,

where 11 are PS current lines.

Figure 4, 5, 6, 7 shows the options for the design of the membrane-divider (view from the side of the squib in Figure 1).

Figure 4 A design variant of the membrane divider with peripheral protrusions,

where 12 is the contour of the charge channel TRT;

13 - contour of the outer surface of the charge;

14 - the inner contour of the membrane-divider;

15 - the outer contour of the membrane-divider;

16 - the internal circuit of the rocket engine.

Figure 5 A design variant of the diaphragm divider with peripheral protrusions and a central throttling hole.

6 Design variant of the membrane-divider with peripheral circular holes,

where 17 are peripheral holes - circular.

Fig.7. A design variant of the membrane-divider with peripheral circular holes and a central throttling hole.

An example implementation of a patentable design

The design is implemented in the form of solid propellant solid propellant rocket propellant with a channel charge of all-round combustion based on ballistic TPT (outer diameter 61.1 mm, channel diameter 28 mm, length 500 mm), a film igniter of a "packet" design (external surface - PET film) with a sample of 10 g of DRP -2, a steel diaphragm-divider with peripheral holes and a central throttling hole, and a squib with a PS force diameter of ~ 12 mm.

Patented design works as follows (Figure 2).

When the squib (7) is triggered, the force PS of the squib “cuts through” the film igniter body (3) and the thickness of the igniter composition and encounters an obstacle - a diaphragm-diaphragm (5), or an obstacle - a diaphragm-diaphragm with a central throttling hole (10), diameter which is not more than 0.5 of the jet diameter of the PS pyro cartridge, completely or partially changes the direction of motion of their own combustion products in radial directions. This movement of the PS pyrocartridge contributes to the effective ignition of the sample (4) of the igniter composition (Figure 1) of the igniter. High-quality ignition of the igniter hitch contributes to the effective ignition of the burning surfaces of the charge (2) TPT. The expiring PS of the TRT charge through the nozzle block provides the required propulsion thrust for the rocket, or the necessary energy characteristics for gas generators, BTIM, KU, etc.

The positive effect of the invention is to increase the efficiency and reliability of solid-propellant rocket devices, increase the efficiency of the ignitor (reducing the weight of the igniter composition while ensuring the required level of reliability of the ignition charge TRT).

Claims (4)

1. A rocket engine of solid fuel, comprising a housing with a channel charge of all-round combustion placed in it, a film igniter, a squib mounted in the front cover of the engine, and a diaphragm-diaphragm, the film igniter being installed between the pyrocartridge and the diaphragm-divider, and in the diaphragm-diaphragm peripheral holes are made, oriented in the gap between the engine housing and the outer surface of the charge, characterized in that the film igniter is tightly bonded with an adhesive composition n and indenkumaronovoy based thermoplastic resin with the membrane-divider, and on the axis of the cutter in the membrane-divider means provided with a central throttle bore whose diameter is 0.3 ... 0.5 the jet diameter - Force cutter combustion products. 2. The rocket engine according to claim 1, characterized in that the peripheral holes are made in the form of gap portions between the contour of the diaphragm-divider and the surface of the housing. 3. The rocket engine according to claim 1, characterized in that the peripheral holes are made circular. 4. The rocket engine according to claim 1, or 2, or 3, characterized in that the divider membrane is made of steel.

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