RU2472963C1 - Method of experimental estimation of launching aircraft missile with solid propellant charge - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises flight test of missile launched from surface launcher in test range conditions with picking up of unburnt propellant particles, i.e. degressive residuals, in the course of missile boost path. Particles are sorted by weight and thrown into aircraft engine air intake secured at test bench and operated in aircraft actual flight conditions. Depth of dints on aircraft engine compressor wheel blades is measured to estimate their magnitude and to specify tolerable weight of said particles in technical papers.

EFFECT: defining tolerable weight of solid propellant particles.

2 dwg

Description

The invention relates to the field of rocketry and can be used in experimental safety assessment of launching aircraft missiles (AR).

Rockets equipped with a solid fuel rocket engine (solid propellant rocket engine) are widespread in modern technology. See “The theory of solid rocket propellant rocket engine” (Y. M. Shapiro, G.Yu. Masing, N.E. Prudnikov, M., 1966). Moreover, one of the main requirements for solid propellant rocket engines is their compatibility with the propulsion system of an aircraft engine (AD) of a carrier aircraft, including the permissible mass of solid particles - degressive residues (DO) of charge fuel thrown from the combustion chamber of the engine rockets at the end of work (exhaust).

For uncontrolled multiple launch rocket missiles (~ 80 mm caliber), channel structures of all-round combustion ballistic missiles TRT on a ballistic basis (insert type) are mainly used. Such charges (patent RU 2178092 from 01/10/2002) are simpler in design and more economical to manufacture compared to charges from composite solid rocket fuel (CTT), firmly bonded to the combustion chamber of a rocket engine.

However, ballistic-based plug-in charges have such drawbacks as the ejection of particulate matter at the end of the job (“exhaust”).

An object of the invention is to develop a method for experimental safety assessment of launching aircraft missiles with an additional charge of solid rocket fuel, which makes it possible to determine the safety of mining both missiles, solid propellant rocket engines, and an aircraft engine.

The technical result of the invention consists in a method for experimental safety assessment of launching aircraft missiles equipped with solid propellant rocket propellant with a fixed charge of solid rocket fuel, including flight testing of a rocket from a ground launcher in a firing range, selection of particles of unburned fuel charge over the active portion of the flight path of the rocket (Figure 1 ), sorting particles by mass and subsequent throwing of normalized particles of charge fuel into the air intake of an aircraft engine mounted on a stand (Figure 2), work flying in real flight mode, after which they measure the depth of the nicks on the blades of the turbine wheels of the aircraft engine compressor, estimate their allowable values by calculation and assign the permissible norms for the mass of particles emitted from the solid propellant rocket engine to the TPT charge in the technical documentation.

The essence of the patented invention lies in the actual experimental assessment of the mass of the ejected real particles of the TRT charge during the flight of the rocket and the assessment of their direct effect on the performance of the ABP, which allows us to establish acceptable norms for the ejection of particles of charge fuel from the solid propellant rocket of an aircraft missile.

The patented invention is illustrated in the figures:

Figure 1 - diagram of the selection of degressive remnants of the TRT rocket charge:

1 - launcher;

2 - rocket;

3 - degressive particles of the charge TRT;

4 - tarpaulin panels.

Figure 2 - scheme of throwing degressive residues of the charge TRT in the compressor HELL:

5 - capacity with normalized TO fuel charge;

6 - shutter;

7 - blades of a turbocompressor HELL;

8 - HELL.

The patented method is implemented as follows (FIG. 1): the TRT charge is equipped in the rocket solid propellant rocket (2), the rocket is installed in the ground launcher (1) (an analogue of the launch block of the carrier aircraft), the rocket is launched (2), and then they are selected on pre-lined tarpaulin panels (4) degressive residues (DO) (particles) TPT (3), sort (normalize) them by weight and, taking into account the normalization of particles, carry out (Figure 2) they are thrown from the tank (5) by opening the shutter (6) with the working HELL on the blades of the turbine wheels (7) of the HELL compressor (pos. 8), secured nnogo on the stand and work in real-mode during the flight of the aircraft. Then establish the permissible (maximum) mass of individual particles (DO) charge for a particular type of aircraft HELL.

In the course of the experiments, it was found that the permissible maximum mass of discarded individual particles (degressive charge residues from ballistic fuel) is in the range 1.3 ... 2.0 g, depending on the type of blood pressure of the carrier rocket.

A positive result of the invention is to increase the safety of launching rockets from under the fuselage of a carrier aircraft due to the justified designation of the permissible mass of solid rocket propellant charge particles ejected from a rocket engine with the provision of normalized particles with the required charge structure.

Claims (1)

A method of experimental safety assessment of launching an aircraft rocket with an additional charge of solid fuel, including flight testing of a rocket from a ground launcher in a firing range, selection of unburned fuel particles - degressive residues over the active section of a rocket’s flight, particle sorting by mass and subsequent throwing of degressive fuel particles into air intake of a fixed-wing aircraft engine operating in the real flight mode of the aircraft, after which they measure the depth of the face n on the blades of the turbine wheels of the compressor of an aircraft engine, evaluate their values and assign in the technical documentation for a charge the permissible norms for the mass of degressive particles of fuel.

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