Thermal energy integrated management system suitable for hypersonic flight vehicle and air vehicle

A comprehensive management, hypersonic technology, applied in the cooling system of power plant, aircraft parts, air handling equipment, etc., can solve the problems of high thermal load of aircraft, high power consumption of aircraft system, and low safety of aircraft

Active Publication Date: 2018-11-06
BEIHANG UNIV
View PDF6 Cites 9 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In view of this, the first object of the present invention is to provide a thermal energy integrated management system suitable for hypersonic aircraft, to solve the problem of large power consumption of the internal system of the aircraft due to the high heat of the incoming airflow when the aircraft flies at hypersonic speed. The heat load of the aircraft is high, the performance cannot meet the requirements, the safety of the aircraft is low, and the proportion of the fuel volume caused by only using low-volume heat sink fuel as the heat sink is large, which causes the payload space of the aircraft small problem

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Thermal energy integrated management system suitable for hypersonic flight vehicle and air vehicle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] The invention discloses a thermal energy comprehensive management system suitable for hypersonic aircraft. Among them, the integrated thermal energy management system applicable to hypersonic vehicles includes cockpit 201 air system, fuel system, propulsion system 1, airborne equipment, coolant cooling system and closed cycle cooling system.

[0051] The cabin 201 air system comprises a cabin 201, a first turbine 202 and an air-inducing device 203, the air outlet of the cabin 201 and the first turbine 202 is connected, and the air-inducing device 203 can provide air to the first turbine 202, in order to avoid impurities in the air Entering the turbine and the cockpit 201, causing damage to the turbine and the cockpit 201, a filter can be set in the bleed air device 203 to effectively filter the incoming air.

[0052] The fuel system includes a fuel pump 301 and a fuel regulating valve 302. The outlet of the fuel pump 301 communicates with the inlet of the fuel regulatin...

Embodiment 2

[0071] Such as figure 1 As shown, in the second embodiment provided by the present invention, the thermal energy integrated management system applicable to hypersonic aircraft in this embodiment has a similar structure to the thermal energy integrated management system applicable to hypersonic aircraft in Embodiment 1. The similarities will not be repeated, only the differences will be introduced.

[0072] In this embodiment, it is specifically disclosed that the fuel includes hydrogen, methane, hydrocarbons, alcohols and aviation kerosene, and may also include other hydrocarbon fuels in the thermal energy integrated management system suitable for hypersonic aircraft.

[0073] Further, the present invention discloses an integrated heat energy management system suitable for hypersonic aircraft, the supercritical working medium is supercritical helium or supercritical carbon dioxide, and the supercritical working medium can also be a mixture of supercritical helium and supercrit...

Embodiment 3

[0080] The present invention provides an aircraft, including an integrated thermal energy management system suitable for a hypersonic aircraft as in any one of the above embodiments.

[0081] Since the aircraft disclosed in the present invention includes an integrated thermal energy management system applicable to hypersonic aircraft in any of the above-mentioned embodiments, the beneficial effects contained in the integrated thermal energy management system applicable to hypersonic aircraft are all the aircraft disclosed in the present invention. included.

[0082] In the present invention, "first", "second", etc. are for distinction in description, and have no other special meanings.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a thermal energy integrated management system suitable for a hypersonic flight vehicle and an air vehicle. The thermal energy integrated management system suitable for the hypersonic flight vehicle comprises a cockpit air system, a fuel system, a propulsion system, airborne equipment, a coolant cooling system and a closed circulating cooling system. When the flight Mach number of the air vehicle is a first preset range value, the coolant cooling system and the closed circulating cooling system both do not work; when the flight Mach number of the air vehicle reaches a second preset range value, the coolant cooling system does not work, and the closed circulating cooling system works; and when the flight Mach number of the air vehicle reaches a third preset range value, the coolant cooling system and the closed circulating cooling system both work. According to the thermal energy integrated management system suitable for the hypersonic flight vehicle and the air vehicle, by using the closed circulating cooling system and the coolant cooling system, the thermal of the air vehicle during hypersonic flight is effectively managed, the problems that the performanceof the air vehicle cannot meet requirements and the safety of the air vehicle is lower are solved, and the problem that the payload space of the air vehicle is small is solved.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft, in particular to a thermal energy integrated management system and an aircraft suitable for hypersonic aircraft within the flight Mach number range of 0 to 6. Background technique [0002] The development of hypersonic aircraft is an important direction of aircraft development. The hypersonic vehicle flies at a relatively fast speed. Due to the viscosity and aerodynamic effect on the surface of the body, the surface temperature will be as high as 900-1800K. The heat generated by this part cannot be underestimated. With the improvement of aircraft performance, more and more high-power on-board electronic equipment and advanced mission system support are required, which leads to more heat generated by on-board electromechanical equipment. However, the working environment temperature required by the cabin and airborne equipment cannot be too high. [0003] For hypersonic aircraft, pass...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
IPC IPC(8): B64D13/06B64D33/08
CPCB64D13/06B64D33/08B64D2013/0607
Inventor 邹正平梁科
Owner BEIHANG UNIV
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap