RU2148180C1 - Method of supply of working gas to cavities of flying vehicle units and systems and system for realization of this method - Google Patents

Abstract

FIELD: flying vehicles launched from stationary and mobile sets including submarines. SUBSTANCE: high-pressure cavities are filled with working gas after which mains running to flying vehicle systems are opened; generation of working gas and filling of cavities shall be performed simultaneously. Both procedures are started immediately before launch. System contains high- pressure working gas sources connected with units and systems of flying vehicle by means of mains; system includes also flying vehicle launch control unit. Working gas source is made in form of solid propellant generator of cold pure nitrogen. Generators are located on separable members of flying vehicle; launching devices are connected with flying vehicle launch control unit. EFFECT: improved mass and dimensional characteristics; enhanced reliability and safety of operation due to avoidance of high-pressure bottles. 3 cl, 3 dwg

Description

 The invention relates to aircraft (LA), starting both from stationary and from mobile launchers, including from submarines.

A known method and power system for these aircraft, filling the units and systems from pre-pressurized nitrogen high-pressure cylinders up to 300-400 kg / cm ² for the orientation system of the rocket system "Agen" and spacecraft (see "Cosmonautics", ed. "Soviet Encyclopedia ", M., 1970, p. 16, 143).

 It is also known to use nitrogen pressurization from high pressure cylinders of thin-walled shells of fuel tanks to compensate for longitudinal compressive forces and increase their stability (see ibid., P. 310).

 In these systems, pre-filled high-pressure cylinders placed on the aircraft are used. During the entire period of storage and transportation of aircraft (up to 15-25 years) it is necessary to carry out periodic routine inspections in order to control high pressure on board the aircraft. If a pressure drop is found below the minimum allowable pressure during storage, it is necessary to pump the cylinders using additional ground equipment. To supply working gas from high-pressure cylinders to the units and systems of the aircraft, use additional reducing gears and starting valves.

 In addition, additional feedback is also directly entered into the launch launch sequence diagram to confirm the specified minimum allowable pressure level in the balloon. If the signal from the pressure sensor does not give out on the fulfillment of this requirement, the start is canceled.

 The closest analogue adopted for the prototype is the method and system for pressurizing compressed air of the annular gap between the rocket body and the container walls, followed by pressure equalization with the outboard before launching the rocket from a submarine (submarine) (see Soviet Military Encyclopedia, T. 6. - M., 1978, p. 379).

 In this system, pressurization is carried out from high-pressure air cylinders placed on a submarine carrier, which requires an increase in its dimensions.

 In addition, the use of air as a gas for boosting air leads to an increased danger at start-up, due to the presence of oxygen in it and its possible burning out when mixed with the combustion products of start-up power devices.

 The technical problem to which this invention is directed is to exclude the presence of high working gas pressure on board the rocket during the entire period of its storage and transportation before launch, with the exception of routine inspections.

 The problem is solved by the proposed method and system for supplying working gas to units and aircraft systems. The high-pressure cavities are filled with the produced gas, followed by the opening of the lines leading to the units and systems of the aircraft. In this case, the production of working gas and the filling of the cavities are carried out simultaneously. The beginning of gas production and filling the cavities is carried out immediately before the launch of the aircraft. In the working gas supply system for cavities and aggregates and aircraft systems containing high-pressure working gas sources connected by highways to the cavities of the aircraft aggregates and systems and the aircraft launch control unit, the working gas source is made in the form of solid-fuel cold pure nitrogen generators with their starting devices.

 Generators are placed on detachable elements of the aircraft, and their launch devices are connected to the launch control unit of the aircraft.

 In FIG. 1, 2, 3, a pre-launch pressurization system based on solid fuel generators of cold pure nitrogen is presented.

 The system includes four of the same type of nitrogen generator 1, with triggering devices 2.

 The first nitrogen generator pressurizes a thin-walled solid propellant march stage 3 of a rocket 4, starting from a submarine container 5, using an underwater engine (DPH) 6.

 The second nitrogen generator 1 provides the operation of the missile orientation system in flight by supplying high pressure nitrogen to the control nozzles at pitch 7, course 8 and roll 9.

 The third and fourth nitrogen generators 1 through a single collector 10 provide prelaunch boost cavity 11 of the annular gap between the rocket and the container.

 To reduce the mass of the march stage, the first nitrogen generator is installed on the front bottom of the detachable DPH6, and the second, third and fourth on the detachable nose fairing 12.

 The nozzle plug 13 of the solid propellant sustainer stage 3 is equipped with a breakthrough membrane 14 that overlaps the pressurized cavity 15. Launch control unit 16 is installed on the aircraft.

 The system is as follows.

Immediately before the start (in 5-10 seconds), an electric command is sent from the start control unit 16 to activate the start-up devices 2 of the nitrogen generators 1. As a result of the ignition of solid fuel charges of the nitrogen generators, high-temperature nitrogen (450-500 ^o C) is released, which, passing through the critical section nitrogen generators, enters their cooling units, where its temperature drops to 60 ^o C, and is filtered from the condensed phase. The purity of the resulting nitrogen is 99.9%.

 As a result of the operation of the first nitrogen generator 1, the nitrogen pressure in the cavity increases between the front bottom of the DPH 6 and the rear bottom of the march stage 3. A continuously increasing nitrogen pressure breaks through the membrane 14 of the nozzle plug 13, and nitrogen begins to flow and pressurize the thin-walled solid propellant march stage.

 As a result of the operation of the second nitrogen generator 1, high pressure on line 17 through a detachable connection 18 and a normally open pyrovalve 19 is supplied to the control nozzles at pitch 7, course 8 and roll 9. These nozzles are equipped with electro-pneumatic valves that can be opened and closed by commands of the aircraft control system. Before separation of the nose fairing, a command is issued to close the pyrovalve 19, and a high nitrogen pressure remains in the orientation system, sufficient to ensure stabilization and control of the aircraft.

 As a result of the operation of the third and fourth nitrogen generator 1 through the collector 10, the cavity 11 of the annular gap between the aircraft and the container is pressurized. Supercharging of all the above cavities is carried out simultaneously, after which the aircraft is ready to start.

 The proposed method and the working gas supply system for the aircraft cavities allows to improve overall mass characteristics, to increase the reliability and safety of operation by eliminating high-pressure cylinders during prelaunch storage and transportation of aircraft, reaching 15-25 years.

The use of cold pure nitrogen generators with a temperature of ≤ 60 ^o C and a purity of 99.9% allows for pre-launch boost of solid fuel stages and aircraft orientation systems.

 This system can also be used for pre-launch pressurization of cylinders of the aircraft fuel and hydraulic systems, including for pressurizing the annular gap cavity between the aircraft and the container when starting from a submarine.

 In the national economy, this invention can be used to pressurize emergency rescue bags of cars, pontoons, float chassis, as well as in fire extinguishing systems.

Claims (2)

 1. The method of supplying working gas to the cavities of units and systems of aircraft (LA), which consists in the development of working gas, filling in the high-pressure cavities of the device with the subsequent opening of the lines leading to the units and systems of the aircraft at start-up, characterized in that the production of working gas and the cavities are filled at the same time, while the start of gas production and filling the cavities is carried out immediately before the launch of the aircraft.  2. The working gas supply system for the cavities of the units and systems of the aircraft, containing sources of high-pressure working gas connected to the cavities of the cavities of the units and systems of the aircraft, as well as the control unit for the launch of the aircraft, characterized in that the sources of high-pressure working gas are made in the form of solid fuel cold generators pure nitrogen with devices for their launch and are located on the detachable elements of the aircraft, while the device for launching solid-fuel generators is connected to the control unit for the launch of the aircraft.

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