CN111396276B

CN111396276B - Supersonic electric heating type stamping aerospace engine

Info

Publication number: CN111396276B
Application number: CN202010180264.5A
Authority: CN
Inventors: 陈宗; 夏广庆; 鹿畅
Original assignee: Dalian University of Technology
Current assignee: Dalian University of Technology
Priority date: 2020-03-16
Filing date: 2020-03-16
Publication date: 2022-04-08
Anticipated expiration: 2040-03-16
Also published as: CN111396276A

Abstract

The invention discloses a supersonic electric heating type stamping aerospace engine, and belongs to the technical field of adjacent space stamping engines and aerospace propulsion. The supersonic electric heating type stamping air-borne engine comprises an air passage, an ionization chamber, a flow guide cover, a plurality of support columns, a plurality of electrodes, a composite section, a spray pipe and a plurality of groups of magnetic rings. When the airflow circulates in the ionization chamber, the airflow is divided into two parts by the flow guide cover, and the airflow passing through the inside of the flow guide cover is ionized when contacting with the electrode to generate plasma, and meanwhile, the temperature is increased; and then, the plasma carries out convective heat exchange with the airflow passing through the outer part of the flow guide cover in the recombination section to be changed into supersonic airflow with higher temperature, and the supersonic airflow is further accelerated under the action of the nozzle to generate thrust. The invention uses the plasma to heat the airflow, can avoid the technical problems that the fuel is difficult to burn and is unstable in the adjacent space of the traditional ramjet, and can continuously provide the discharge power to improve the temperature of the airflow and increase the thrust.

Description

Supersonic electric heating type stamping aerospace engine

Technical Field

The invention belongs to the technical field of near space ramjet engines and space propulsion, and particularly relates to a supersonic electric heating type ramjet engine.

Background

The father of space ziolkovski said: the earth is a human cradle, but a human cannot always lie in the cradle. Soaring the blue sky and getting out of space are the way that people always go, and in order to complete the task, the predecessors propose various design schemes and ideas no matter in a SSTO (single stage orbit input) or TSTO (multi-stage orbit input) mode, wherein the ramjet becomes an indispensable core component in the task due to the advantages of simple structure, light weight, large thrust, easy production and the like. In the space mission, the general idea is to use a rocket engine to send a spacecraft to a stratosphere, then use a ramjet engine to provide thrust by using the atmosphere in the environment as an oxidant and a propellant, and finally use an electric thruster to finish space operation.

The use of the ramjet in this way not only presents a serious problem in the development of supersonic combustion technology, but also results in the ramjet not being fully utilized during the mission, resulting in a certain amount of waste. Firstly, the supersonic combustion technology requires that fuel is fully mixed with oxygen in the atmosphere to provide heat under the supersonic environment, and also requires a matched oil supply pipeline, a nozzle, an ignition device and the like, and the matched equipment not only prolongs the development period of the scramjet engine, but also easily causes other faults such as: potential safety hazards are caused by unstable oil injection, uneven combustion, airflow oscillation and the like of the nozzle; and the ramjet has a simple structure, and can not only send the spacecraft to the adjacent space boundary, but also have the capacity of operating in space by adding the design of other space motors in the ramjet. Aiming at the two problems, the invention modifies the punching engine at two places, uses electric arc to generate plasma to heat air flow, and uses the magnetic nozzle technology to realize that the engine can provide thrust in space.

The ramjet is an indispensable component of the TSTO (dual stage in-rail engine), and a scramjet is generally used. The scramjet engine is an air suction type near space engine, the existing scramjet engine provides heat through fuel oil combustion, but airflow flowing through the inside of the scramjet engine is supersonic airflow, and fuel is difficult to ignite under the working condition, so that the scramjet engine is a key technology. Furthermore, scramjet engines cannot work in space, but only to bring aircraft or mission units close to the boundaries of the space. To complete the TSTO mission, a rocket motor needs to be started to provide thrust.

Disclosure of Invention

The invention provides a supersonic electric heating type stamping air-space engine aiming at the problem of difficult supersonic combustion in the prior art and simultaneously aiming at maximizing the energy utilization of a stamping engine, so as to overcome the problems of difficult ignition, unstable combustion and the like of the stamping engine in an aerospace task and enable the stamping engine to have the capability of providing thrust in space.

In order to achieve the purpose, the invention adopts the technical scheme that:

a supersonic electrothermal type ram air engine, comprising: the device comprises an air passage 1, an ionization chamber 2, a flow guide cover 3, a plurality of support columns 4, a plurality of electrodes 5, a composite section 6, a spray pipe 7 and a plurality of magnetic rings 8.

The air inlet 1 is a convergent channel, that is, the cross-sectional area of the air inlet is larger than that of the air outlet, and the air inlet 1 is used for decelerating and stabilizing the supersonic airflow of the incoming flow, so that various parameters (such as pressure intensity, speed and the like) of the incoming flow airflow are stable.

Ionization chamber 2 and compound section 6 are the constant cross section passageway, and the exit at intake duct 1 is installed to the front end of ionization chamber 2, and the end at ionization chamber 2 is installed to the front end of compound section 6.

The spray pipe 7 is an expanding channel, namely the cross sectional area of the airflow inlet is smaller than that of the airflow outlet; the inlet of the lance 7 is mounted at the end of the compounding section 6.

The air guide sleeve 3 is cylindrical, the air guide sleeve 3 is fixed inside the ionization chamber 2 through a plurality of support columns 4, and the axial direction of the air guide sleeve 3 is parallel to the flowing direction of gas in the support columns 4; a plurality of elongate electrodes 5 are mounted at equally spaced intervals at the downstream end face of the pod 3, and a power supply line for supplying power is passed through the support column 4 to supply power to the electrodes 5.

The ionization chamber 2, the composite section 6 and the nozzle 7 are all provided with a magnetic ring 8 on the outer side.

Furthermore, the cross section of the air guide sleeve 3 is supersonic streamline, so that the influence on supersonic airflow is reduced.

Furthermore, the magnetic ring 8 is a permanent magnet, the inner diameter of the magnetic ring 8 is slightly larger than the outer diameter of the supersonic electric heating type stamping aerospace engine, and thermal protection is adopted, so that the phenomenon that the service life of the supersonic electric heating type stamping aerospace engine is shortened due to the fact that the magnetic ring loses magnetism due to high-temperature air flow in the supersonic electric heating type stamping aerospace engine is avoided.

Furthermore, the magnetic field generated by the magnetic ring 8 at the front ends of the ionization chamber 2, the composite section 6 and the spray pipe 7 has uniform strength in the axial direction, and the axial strength of the magnetic field is weakened in the direction from the inlet to the outlet of the spray pipe 7, so that the acceleration of high-temperature plasma can be realized.

The invention has the beneficial effects that: the invention provides thrust by heating airflow in a way of ionizing the airflow by the electrodes to generate plasma in the adjacent space, and ionizes propellant working media into the plasma in the outer space and accelerates the plasma to be discharged through the magnetic nozzle to generate the thrust. The technical problems that fuel is difficult to ignite, combustion is unstable, fuel oil is blocked, injection is difficult and the like in an adjacent space of a traditional ramjet can be solved by using the plasma to heat the air flow, the plasma generated by ionization has no high-temperature upper limit, the temperature-increased thrust of discharging power and improving the air flow can be continuously provided, in addition, the kind of the working medium can be ignored when the plasma generated by the electrode, and the complex problems of considering the fuel oil supply proportion and the like can be avoided; in addition, in the outer space, the plasma is accelerated by installing the magnetic ring outside the divergent nozzle, so that the addition of a new aerospace engine is avoided to realize the capability of completing multiple tasks in multiple working modes of one engine.

Drawings

FIG. 1 is a three-view diagram of a supersonic electrothermal type ram air-borne engine according to the present invention;

FIG. 2 is a three-dimensional cross-sectional view of a supersonic electrothermal type ram air-borne engine according to the present invention;

FIG. 3 is a detailed view of the ionization chamber of the supersonic electrothermal type impact aerospace engine.

In the figure: 1. an air inlet channel; 2. an ionization chamber; 3. a pod; 4. a support pillar; 5. an electrode; 6. a compounding section; 7. a nozzle; 8. a magnetic ring.

Detailed Description

The present invention will be described in further detail with reference to specific embodiments.

A supersonic electrothermal type ram air engine, comprising: the device comprises an air inlet channel 1, an ionization chamber 2, a flow guide cover 3, a plurality of support columns 4, a plurality of electrodes 5, a composite section 6, a spray pipe 7 and a plurality of magnetic rings 8.

As shown in fig. 1, the inlet 1 is a convergent channel, that is, the cross-sectional area at the inlet of the airflow is larger than the cross-sectional area at the outlet of the airflow, and the inlet 1 is used to decelerate and stabilize the supersonic airflow of the incoming flow, so that various parameters (such as pressure, velocity, etc.) of the incoming flow are stable.

As shown in fig. 2/3, the air guide sleeve 3 is cylindrical, the air guide sleeve 3 is fixed inside the ionization chamber 2 through a plurality of support columns 4, and the axial direction of the air guide sleeve 3 is parallel to the flowing direction of the gas in the support columns 4; in order to reduce the influence on the supersonic airflow, the air guide sleeve 3 with the supersonic streamline cross section is selected and used in the embodiment.

A plurality of elongate electrodes 5 are mounted at equally spaced intervals at the downstream end face of the pod 3, and a power supply line for supplying power is passed through the support column 4 to supply power to the electrodes 5.

When the airflow circulates in the ionization chamber 2, the airflow is divided into two parts by the air guide sleeve 3, one part passes through the inside of the air guide sleeve 3, and the other part passes through the outside of the air guide sleeve 3. The gas flow passing through the inside of the air guide sleeve 3 is ionized when contacting with the electrode 5, plasma is generated, and the temperature is increased; subsequently, the plasma is convected in the recombination zone 6 with the gas flow passing through the outside of the dome 3 into a supersonic gas flow with a higher temperature, which is further accelerated by the nozzle 7 to generate thrust.

The magnetic ring 8 is respectively arranged at the outer sides of the air inlet 1, the compound section 6 and the spray pipe 7, the magnetic ring 8 is a permanent magnet, the inner diameter of the magnetic ring 8 is slightly larger than the outer diameter of the supersonic electric heating type stamping air-borne engine, and thermal protection is adopted, so that the phenomenon that the service life of the supersonic electric heating type stamping air-borne engine is shortened due to the fact that the magnetic ring loses magnetism due to high-temperature air flow inside the supersonic electric heating type stamping air-borne engine is avoided.

An axial magnetic field is formed in the composite section 6, and a magnetic field with axial and radial gradients is generated on the inner side of the spray pipe 7; the magnetic field is used for restraining the radial motion of plasma, so that the plasma is prevented from etching the composite section 6 and the pipe wall of the divergent nozzle 7; meanwhile, the magnetic ring 8 arranged on the outer side of the spray pipe 7 generates a divergent magnetic field in the plume region, so that the plasma flow can be accelerated to generate thrust.

Claims

1. The supersonic electric heating type stamping aerospace engine is characterized by comprising an air inlet (1), an ionization chamber (2), a flow guide cover (3), a plurality of support columns (4), a plurality of electrodes (5), a composite section (6), a spray pipe (7) and a plurality of magnetic rings (8);

the air inlet channel (1) is a convergent channel, namely the cross-sectional area of an air inlet is larger than that of an air outlet;

the ionization chamber (2) and the composite section (6) are both fixed-section channels, the front end of the ionization chamber (2) is installed at the outlet of the air inlet channel (1), and the front end of the composite section (6) is installed at the tail end of the ionization chamber (2);

the spray pipe (7) is an expansion-shaped channel, namely the cross sectional area of the airflow inlet is smaller than that of the airflow outlet; the inlet of the spray pipe (7) is arranged at the tail end of the composite section (6);

the air guide sleeve (3) is cylindrical, the air guide sleeve (3) is fixed inside the ionization chamber (2) through a plurality of support columns (4), and the axial direction of the air guide sleeve (3) is parallel to the flowing direction of gas in the support columns (4); a plurality of slender electrodes (5) are arranged at the downstream end face of the air guide sleeve (3) at equal intervals, and power supply wires for supplying power penetrate through the supporting columns (4) to supply power to the electrodes (5);

when the airflow circulates in the ionization chamber (2), the airflow is divided into two parts by the air guide sleeve (3), one part passes through the inside of the air guide sleeve (3), and the other part passes through the outside of the air guide sleeve (3); when the airflow passing through the inside of the air guide sleeve (3) is contacted with the electrode (5), the airflow is ionized to generate plasma, and the temperature is increased; then, the plasma carries out convective heat exchange with the airflow passing through the outside of the air guide sleeve (3) in the composite section (6) to change into supersonic airflow with higher temperature, and the supersonic airflow is further accelerated under the action of the nozzle (7) to generate thrust;

magnetic rings (8) are arranged on the outer sides of the ionization chamber (2), the composite section (6) and the spray pipe (7); an axial magnetic field is formed in the composite section (6), and a magnetic field with axial and radial gradient is generated at the inner side of the spray pipe (7).

2. A supersonic electrothermal ram air-to-air engine according to claim 1, characterized in that the cross-section of the fairings (3) is supersonic streamline.

3. The supersonic electrothermal type stamping air-cooled generator as defined in claim 1, wherein the magnetic ring (8) is a permanent magnet, and the inner diameter of the magnetic ring (8) is slightly larger than the outer diameter of the supersonic electrothermal type stamping air-cooled generator, and is protected by heat.