RU2289036C2 - Rocket catapult solid-reactant gas generator - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: proposed solid reactant gas generator for piston catapult of rocket contains afterburner with front cover, support grid, explosive cartridge and granulated solid-propellant charge arranged in sealed sectional shell made of polymeric film in form of cartridge belt tuned to form cylinder with central channel. Sections of cartridge belt are filled up with solid propellant to capacity. Coiled cartridge belt adjoins to inner surface of afterburner body. Partially perforated tube-primer is installed in central channel of charge, being connected with front cover of afterburner of gas generator and support grid. Gas generator is furnished additionally with pressure chamber with solid-propellant progressive burning charge. Afterburner and pressure chamber are connected by common gas coupling - mixing chamber and gas duct providing igniting of charge in pressure chamber by combustion products of charge in afterburner and delivery of joined combustion products to underpiston space of rocket catapult. Charge of pressure chamber is made in form of two channel restricted-burning grains arranged in tandem with displacement by d/4...d/2 along axes of grains where d is outer diameter of grain, grains being arranged in perforated metal jacket. Mass of charge of afterburner is 0.2-0.4 of mass of charge of pressure chamber.

EFFECT: provision of high gas generation of gas generator, compact design of catapult, optimum level inside ballistic characteristics of gas generator and catapult.

2 cl, 3 dwg

Description

The invention relates to the field of rocket technology, and can be used in the design, development and manufacture of gas generators (GG) of solid fuel for ejection devices (KU) of missiles.

Known gas generator according to patent RU 2213245 (published September 27, 2003, application RU 2002108237 dated April 1, 2002), selected by the authors for the prototype (Fig. 1).

The disadvantage of the prototype is the low energy GG, providing the launch of only enough "light" missiles with a launch mass of 100 ... 300 kg. For the ejection launch of rockets with a launch mass of 500 ... 1000 kg or more, a significant increase in the gas production of launching GGs is necessary. The launching GG needs to provide both stragging of the rocket in the launch tube (container) and a sufficient impulse of force (F · Δt) to ensure the subsequent movement of the rocket in the launch container (tube) and ejection of the rocket from the container to the required height. At the same time, the dimensions of the GG strictly limits the diametrical size of the launch container.

An object of the invention is the development of an effective GG design that provides high gas generation, compactness, primarily in the diametrical direction, as part of the launch container of the missile system, and the optimal level of ballistic characteristics (VBH) in the under-piston space of the KU.

The specified technical problem is solved in the patented invention by equipping the starting GG with an additional charging chamber (escort) with a solid-fuel charge of progressive combustion in relation to the implementation of the compressor unit in the form of a small-caliber piston system.

The technical result of the invention consists in the implementation of solid propellant GG (figure 2) ejection device of the rocket in 2-chamber execution - afterburner and boost chamber (escort), located on the same axis and connected to each other by a common gas connection - a mixing chamber and a gas duct - providing ignition of the charge in the pressurization chamber by the combustion products of the afterburner’s charge and supply of joint combustion products (PS) into the under-piston space of the ejection device (KU). In this case, the afterburner is equipped with a front cover, a squib cartridge, a support grill and an afterburn charge of granular solid fuel placed in a sealed sectional shell made of a polymer film in the form of a bandolier rolled into a cylinder with a central channel, while the bandolier sections are filled with granular solid fuel (smoke powder, pellets of ballistic fuel) until tight packing, and a rolled bandolier is adjacent to the inner surface of the afterburner body. An ignition tube partially perforated along the length of the afterburner is mounted in the central channel of the afterburner.

To increase the efficiency of the afterburner charge, it can be performed combined in composition: part of the sample from smoke powder, and part of the sample from thin-tube tubes of ballistic fuel. In the proposed composition, it is possible to provide an increase in the energy (gas generation) of the afterburner charge with acceptable intra-ballistic characteristics of the KU (maximum pressure, operating time) while ensuring the weight ratio of the sample of smoke powder and thin-tube tubes of ballistic fuel 0.8 ... 1.2. As experiments showed when the lower limit was not observed according to the indicated relation (0.8), due to a decrease in the fraction of “burning”, condensed particles in the composition of the PS afterburner charge of smoke powder decreases the reliability of ignition of the charge of the boost chamber, and exceeding the upper limit (1.2) leads to an unacceptable increase in maximum pressure (p _max ) in the under-piston space of the compressor unit.

In the chamber of pressurization (escort) there is a charge of progressive combustion, the ignition of which is carried out by the PS afterburner charge. The charge of the boost chamber is made of quick-burning ballistic fuel in the form of two channel half charges (channel blocks), armored on the outer surface, which ensures the necessary progressive gas formation. Joint exposure ps charges of the afterburner chamber and the boost chamber, with the ratio of the mass of the afterburner and the charge of the boost chamber 0.2 ... 0.4, they allow launching a rocket weighing more than 500 kg. The lower limit of this ratio allows for effective stragging of the rocket in the launch container, and the upper one is limited by the value of the permissible maximum pressure in the cylinder KU. In this case, the half-charges of the boost chamber are placed sequentially one after another with an axial displacement of d / 4 ... d / 2, where d is the outer diameter of the half-charge.

The proposed arrangement of the half-charges of the boost chamber allows for a consistent, stable and relatively smooth nature of ignition by the combustion products of the afterburner of the half-charges of the boost chamber and thereby reduce the maximum pressure (pressure-time diagram, Fig. 3) in the under-piston space KU. The shift of half charges more than d / 2 is limited by the dimensions of the launch container, and less than d / 4 significantly reduces the effect of the sequence and smoothness of ignition of the charge of the boost chamber.

It was experimentally established that the smoothness of ignition of the charge of the charge chamber to a certain extent also contributes to the influence of the fastening elements of the charges in the charge chamber. The most optimal option, experiments have shown, is the placement of half-charges of the boost chamber in metal perforated shirts, which allows purposefully increasing somewhat the heat loss of the PS afterburner in the process of ignition of half charges in the boost chamber and thereby "smooth" the curve P (τ) in the under-piston space KU. In the process of short-term operation of the KU (0.10 ... 0.15 s), metal perforated shirts work in the "absorbing heat pump" mode, reducing the heat load on the armor coatings of half-charges (which eliminates the "blow-off" of the armor coating and can significantly reduce its thickness) and somewhat delaying (stretching in time) the ignition of the I and II half charges. Moreover, the presence of the perforation of the shirts prevents their deformation under the influence of gas-dynamic loads, and the placement of half-charges in the shirts prevents the destruction of half-charges under the influence of a powerful gas-dynamic flow (pressure wave) coming from the afterburner into the pressurization chamber.

The invention is illustrated in figure 1, 2, 3.

Figure 1. The design of the prototype.

1 - ignition tube;

2 - front cover;

3 - throttling hole;

4 - a support lattice;

5 - radial holes;

6 - holes in the support grid;

7 - a squib;

8 - section of the afterburning solid fuel charge;

9 - afterburner body.

Figure 2. Design patentable GG.

7 - a squib;

9 - afterburner body;

8 - section afterburner charge;

4 - a support lattice;

1 - ignition tube;

10 - mixing chamber;

11 - boost chamber;

12 - charge of the boost chamber;

13 - shirts;

14 - holes (perforation);

15 - gas duct;

16 - stock;

17 - under-piston space;

18 - a piston;

19 - cylinder;

20 - bleed holes.

Figure 3. Pressure-time diagram in the sub-piston space for the patented GG.

The positive effect of the invention is to equip the GG with a boost chamber (escort) with a solid fuel charge from quick-burning fuel, which allows not only to ensure the fulfillment of the technical task (rocket bailout), but also to realize it at an acceptable level of VBH, in particular, according to the maximum pressure level ( see figure 3).

Patented GG works as follows (figure 2).

When the pyro cartridge (7) is activated, sections of the G afterburner charge are ignited, the combustion products of which enter the mixing chamber (10) and the boost chamber and then move into the under-piston space (17) of the KU, ensuring the rocket is strained in the launch tube and simultaneously igniting the chamber charges boost (11). With the accepted ratio of the mass of the charge of the afterburner and the boost chamber (0.2 ... 0.4), both efficient ignition of the charges of the boost chamber and the optimum, acceptable from the point of view of force impact (pressure) ps on the design of KU (figure 3), the nature of the pressure-time curve in the under-piston space of the catapult. Pressure developed in the sub-piston space to the piston (18), it allows the rocket to be ejected from the container by transferring the ejection force to the bottom of the rocket using a hook rigidly connected to the piston rod (16) moving in the cylinder (19).

Patented GG design, implemented in relation to a rocket propulsion system with a mass of 0.6 tons. Charges from smoke powder and ballistic solid fuel were used as a gas-generating source. At the same time, the actual mass of the afterburner charge (smoke powder and fine-ballistic tubes of ballistic fuel with an actual mass ratio of 0.9) is 0.19 kg, and the charge mass of the boost chamber is 0.76 kg. Charges of the boost chamber were made in the form of two half-charges - channel pieces 34 mm in caliber and 280 mm long, armored on the outer surface, placed in perforated metal shirts sequentially one after another with an offset of d / 2 along the axes of the blocks.

Claims (2)

1. A solid fuel gas generator for a rocket ejection piston device, including an afterburner with a front cover, a support grill, a squib and a charge of granular solid fuel, placed in a sealed sectional shell made of a polymer film in the form of a cartridge belt rolled into a cylinder with a central channel, with sections The cartridge belt is filled with solid fuel until it is tightly packed, and the rolled-up cartridge belt is adjacent to the inner surface of the afterburner body, with an acoustically perforated ignition tube bonded to the front cover of the afterburner chamber of the gas generator and a support grill, characterized in that the gas generator is additionally equipped with a boost chamber with a solid fuel charge of progressive combustion, while the afterburner and the boost chamber are connected by a common gas connection - a mixing chamber and a gas duct, providing ignition of the charge in the pressurization chamber by the combustion products of the afterburner charge and the supply of joint combustion products into the sub-piston space catapult th device of the rocket, while the charge of the boost chamber is made in the form of two channel blocks, armored on the outer surface, arranged sequentially one after another with an offset along the axes of the blocks by the amount d / 4 ... d / 2, where d is the outer diameter of the block, and placed in perforated metal shirts, and the mass of the afterburner charge is 0.2 ... 0.4 the mass of the charge of the boost chamber. 2. A solid fuel gas generator for a rocket ejection device according to claim 1, characterized in that the charge of the afterburner includes granular smoke powder and fine tubes made of ballistic solid fuel in a ratio of 0.8 ... 1.2.

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