RU2362035C1 - Charge for solid rocket fuel - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of rocket technology and can be used at for designing, developing and preparing solid rocket fuel charges for gas generators and rocket engines. The charge for solid rocket fuel is executed in the shape of a cylindrical cone cartridge with an end-to-end, axially symmetrical channel and partially covered with metal, external surfaces, furthermore, the butt end to the cartridge from the side of the cylindrical part is covered with metal. The cartridge is executed taking into account the correlations protected by the current invention. The charge, in its preferable form for execution, is made from ballistite rocket fuel, and the metal covering from material based on cellulose acetate.

EFFECT: invention increases operational efficacy and also reliability of the charge.

3 cl, 5 dwg

Description

The invention relates to the field of rocketry and can be used in the design, development and manufacture of charges of solid rocket fuel (TRT) to gas generators (GG) and rocket engines of solid fuel (RTTT).

Known designs of charges TRT for GG, solid propellant rocket launchers and other missile devices in the form of channel pieces TRT, partially or fully armored on the side and end surfaces (patents RU 2164616, RU 2211350, RU 2259495). Among the known designs, one of the most effective is the charge design according to US Pat. RU 2259495, IPC F02K 9/10 10/16/2003. The design of this charge allows you to ensure both the purity of the combustion products (PS) of the charge, and a high level of ballistic characteristics. However, this design is unsuitable in a "pure form" for use in a conical-cylindrical combustion chamber (COP). At the same time, there is an objective need for conical-cylindrical charges for starting GG ramjet engines (ramjet), for example, according to US Pat. RU 2241845, where the GG case is used as a central body in the ram ram intake (FIG. 1). In this case, the GG charge (according to preliminary estimates) should provide an operating time within ~ (2 ... 4) s, a maximum pressure in the GG CS not more than 200 kg / cm ² and a pressure-time relationship (flow ^{* *} ( ^* The term "flow rate" in the application means the second mass flow rate of TPT combustion products flowing through the nozzle (s) of the gas generator.) - time "). The closest technical solution to patentable is given in US Pat. RU 2079689, the disadvantage of which is the lack of recommendations on the ratio of the size of the charge (D / d, booking length of the cylindrical section, etc.), as well as on the type of used TRT and armored personnel. The invention according to US Pat. RU 2079689 C1, IPC F02K 9/08, published on 05/20/1997, priority from 08/08/1994.

An object of the invention is the development of the design of the conical-cylindrical charge TRT for starting ramjet gas generator with increased operational efficiency and reliability.

The specified technical problem is solved within the framework of the present invention by choosing the optimal charge design, namely the optimal ratio of the geometric dimensions of the conical-cylindrical charge.

The technical result of the invention is to perform the charge TRT in the form of a conical-cylindrical block of solid rocket fuel with a through axisymmetric channel and partially armored outer surfaces, including at the end, from the side of the cylindrical section of the block, and the side surface. In this case, the charge is fulfilled:

- with the ratio of the lengths of the cylindrical L _c and the conical L _{to the} outer surfaces within:

L _c / L _k = 1.0 ... 2.0;

- with the ratio of the diameter of the charge (D) on the outer cylindrical portion of the charge (fuel) to the diameter of the channel (d) within:

D / d = 5.0 ... 8.0.

In this case, the cylindrical surface of the charge is armored from the side of the cylindrical end by at least 0.5L, where L is the length of the charge (for fuel).

The charge is made of ballistic TPT, and the armor plating of armored material based on cellulose acetate.

The essence of the invention lies in the targeted selection (purpose) of the optimal ratios of the geometric dimensions of the charge, namely:

- D / d ratios for the lower limit of at least 5.0 - limits the minimum permissible operating time of the GG, and for the upper limit of not more than 8.0 - provides the maximum permissible operating time of the GG;

- the ratio of L _c / L _to with the level of the length of the reservation L _c not less than 0.5L, which allows to ensure the dependence of "pressure-time"("flow-time"), close to neutral.

The latter, in turn, allows you to limit the maximum pressure level in the HG CS (using medium-burning ballistic-type solid-state solid fuel) to no more than 200 kg / cm ² . The use (application) of a ballistic TPT (for a fuel bomb) charge of an armored coating based on cellulose acetate contributes to the reliability of the GG by ensuring the minimum mechanical impact of PS on the turbine wheel blades of the ramjet compressor, due to the minimum K - phase content in the PS of the latter.

The invention is illustrated by drawings:

Figure 1 - the entrance of the ramjet

1 - body ("shirt") ramjet

2 - GG case (central body)

3 - charge TRT

4 - blades of turbine wheels of the ramjet compressor

5 - nozzle holes GT

Figure 2 - design patentable charge

6 - checker TRT

7 - armor plating charge TRT

8 - nozzle end face of the charge

9 - outer cylindrical surface

10 - channel

Figure 3 - dependence S (e) for patentable charge

Figure 4 - experimental dependence p (τ) for an example of a patentable design at an initial charge temperature of 60 ° C

Figure 5 - experimental dependence p (τ) for an example of a patentable design at an initial charge temperature of minus 30 ° C.

The charge (Figure 2) consists of a conical-cylindrical checker TRT (6) with armor plating (7) on the nozzle end (8) and the outer cylindrical surface (9). The checker has a through axial channel (10) and is made of ballistic TPT. The checker is armored with cellulose acetate armor.

The charge works as follows. After applying a pulse to the initiator, the charge ignites on unarmoured surfaces and burns in parallel layers on equidistant surfaces. The resulting PS GGs expire through nozzle (consumable) openings and, due to the gas-dynamic effect on the blades of the turbine wheels of the compressor, ensure its unwinding and subsequent launch of the ramjet. The efficiency of the conical-cydindric charge was evaluated using the example of a charge from a medium burning ballistic TPT with the following parameters:

D - 130 mm, d - 20 mm, L - 100 mm, L _c - 65 mm, L _c - 35 mm, L _c ^br - 55 mm.

When adopted in the framework of this patent, the ratio of the size of the charge and the armored surfaces provides close to neutral dependence (Figure 4, Figure 5) "pressure-time" ("flow-time") and the required VBH of the gas generator

(p _max , τ), which characterizes the positive effect of the invention.

Claims (3)

1. The charge of solid rocket fuel, made in the form of a conical-cylindrical block of solid rocket fuel with a through axisymmetric channel and partially armored outer surfaces, and the end face of the block from the side of the cylindrical section is reserved, characterized in that the block is made taking into account the ratios
L _c / L _k = 1.0 ÷ 2.0,
D / d = 5.0 ÷ 8.0,
L _q ^br ≥0,5L,
where L _C - the length of the cylindrical section of the checkers;
L _to - the length of the conical section of the checkers;
D is the diameter of the cylindrical section of the checker;
d is the diameter of the channel;
L _C ^br - the length of the reserved portion of the outer surface of the checkers;
L is the length of the checker. 2. The charge of solid rocket fuel according to claim 1, characterized in that the checker is made of ballistic rocket fuel. 3. The charge of solid rocket fuel according to claim 1, characterized in that the checker is made of ballistic rocket fuel, and the armor plating is made of cellulose acetate-based material.

Images