Variable working condition type primary rocket system of rocket based combined cycle engine

A rocket engine and engine technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of complex servo mechanisms or power devices, poor controllability, low precision, etc., to achieve accurate flow and meet the needs of flow regulation , the effect of quick adjustment

Active Publication Date: 2015-02-04
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Generally, if the adjustment control technology used in the flow adjustment scheme has the advantages of quick response and precise control, it will generally have disadvantages such as req

Method used

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  • Variable working condition type primary rocket system of rocket based combined cycle engine
  • Variable working condition type primary rocket system of rocket based combined cycle engine
  • Variable working condition type primary rocket system of rocket based combined cycle engine

Examples

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Embodiment Construction

[0022] like figure 1 As shown, a primary rocket system of a rocket-based combined cycle engine with variable operating conditions includes a propellant supply system connected by pipelines and a primary rocket engine thrust chamber 18, and the propellant supply system includes an oxidant supply system A and a fuel supply system B The oxidant supply system A includes an oxygen flow control system, the oxygen flow control system includes a plurality of oxygen delivery pipelines, each oxygen delivery pipeline is provided with an oxygen pressure reducing valve 4 for opening and closing, and the outlet of the oxygen delivery pipeline is connected to Oxygen orifice 6 is arranged; fuel supply system B comprises pressure control system, and pressure control system comprises a plurality of fuel delivery pipelines, and the outlet of each described fuel delivery pipeline is all provided with cavitation venturi 15, and fuel delivery pipeline The inlet of is connected with the nitrogen pre...

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Abstract

The invention discloses a variable working condition type primary rocket system of a rocket based combined cycle engine. The variable working condition type primary rocket system comprises a propellant supply system and a primary rocket engine thrust chamber which are connected through a pipeline, wherein the propellant supply system comprises an oxidant supply system and a fuel supply system, the oxidant supply system comprises an oxygen flow rate control system, the oxygen flow rate control system comprises a plurality of oxygen conveying pipelines, each oxygen conveying pipeline is provided with an oxygen pressure relief valve for opening and closing the corresponding oxygen conveying pipeline, an outlet of each oxygen conveying pipeline is connected with an oxygen perforating plate, the fuel supply system comprises a plurality of fuel conveying pipelines, an outlet of each fuel conveying pipeline is provided with a cavitation venturi pipe, and an inlet of each fuel conveying pipeline is connected with a nitrogen pressure relief device. The variable working condition type primary rocket system of the rocket based combined cycle engine has the advantages that the flow rate of a propellant can be accurately, controllably, stably and quickly adjusted, the complexity is low, and the operation is simple.

Description

technical field [0001] The invention belongs to the technical field of rockets, and in particular relates to a primary rocket system of a rocket-based combined cycle engine with variable working conditions. Background technique [0002] In the RBCC (Rocket based combined cycle: Rocket based combined cycle) power system, the primary rocket (ie ejection rocket) is the core component of the engine. In the low-speed ejection mode, the aircraft needs to accelerate to the cruising state in a short time, which requires a lot of thrust. And at this time, due to the low flight Mach number of the aircraft (even 0 when taking off), the incoming ramming effect is very weak, and the main thrust can only be provided by a rocket. The primary rocket embedded in the flow channel works, through the ejection and suction of its high-speed airflow, it introduces the secondary air flow, and organizes secondary combustion in the combustion chamber of the flow channel to increase the energy of the...

Claims

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Application Information

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IPC IPC(8): F02K9/42F02K9/44F02K9/56F02K9/62
Inventor 魏祥庚刘阳阳何国强秦飞吕翔石磊陈剑张保庆
Owner NORTHWESTERN POLYTECHNICAL UNIV
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