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A Mechanism Modeling Method of Large Envelope and Wide Velocity Range Propulsion System of Combined Power Vehicle

A propulsion system and combined power technology, applied in the direction of instrumentation, electrical digital data processing, computer-aided design, etc., can solve problems such as the influence of engine thrust estimation

Active Publication Date: 2022-06-14
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] According to the information in open literature, the existing RBCC combined power system modeling methods, especially the quasi-one-dimensional flow model of the dual-mode scramjet engine, are established on the basis of ignoring some main physical quantities, such as the transonic velocity Such simplification leads to a large difference between the calculated results and the actual results, which has a great impact on the estimation of engine thrust

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  • A Mechanism Modeling Method of Large Envelope and Wide Velocity Range Propulsion System of Combined Power Vehicle
  • A Mechanism Modeling Method of Large Envelope and Wide Velocity Range Propulsion System of Combined Power Vehicle
  • A Mechanism Modeling Method of Large Envelope and Wide Velocity Range Propulsion System of Combined Power Vehicle

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Embodiment Construction

[0053] The present invention will now be further described in conjunction with the embodiments and accompanying drawings:

[0054] The purpose of the present invention is to propose a wide-speed-range propulsion system model considering ejector mode, dual-mode scramjet mode and rocket mode for the modeling of RBCC combined power system.

[0055] The object of the present invention is achieved by the following modeling methods:

[0056] The ejector modal model and pure rocket modal model are established by the ejector modal modeling method based on conservation law, which is characterized in that it can reflect the physical characteristics of ejector mode and the calculation speed is fast. Using the quasi-one-dimensional flow theory considering the specific heat ratio, boundary layer and transonic flow characteristics, a wide-speed domain dual-mode scramjet engine model is established, which can reflect the physical flow in the inner channel on the basis of ensuring a certain a...

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Abstract

The invention relates to a method for modeling the mechanism of a large-envelope wide-velocity domain propulsion system of a combined power aircraft, which adds transonic flow and core flow area changes caused by boundary layers to the existing RBCC combined power system modeling method. The main physical quantities are close to the actual model, which improves the modeling accuracy.

Description

technical field [0001] The invention belongs to the research field of combined power aircraft modeling technology, and in particular relates to the wide speed domain modeling technology field of an RBCC power system. The modeling method can be widely used in the design and performance analysis of various hypersonic vehicles based on RBCC power. Background technique [0002] RBCC (Rocket Based Combined Cycle) powered air-breathing hypersonic vehicle propulsion system internal flow channel modeling technology is one of the core key technologies of hypersonic vehicles. The RBCC engine not only retains the large thrust-to-weight ratio of rocket propulsion at low speed (ejector rocket mode, 0≤Ma≤2.5) and the applicability of dense outer atmosphere (pure rocket mode, 8~10≤Ma), but also has a ramjet engine high specific impulse and economy. Among them, the ejector rocket modal and pure rocket modal models can be established according to the traditional conservation theory, and th...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/28G06F119/08G06F119/14
CPCG06F30/15Y02T90/00
Inventor 张栋程锋唐硕
Owner NORTHWESTERN POLYTECHNICAL UNIV