CN102797656A - Air breathing type helicon wave electric propulsion device - Google Patents

Abstract

The invention discloses an air breathing type helicon wave plasma electric propulsion device. Space atmosphere encountered by the air breathing type helicon wave plasma electric propulsion device during orbital running is collected through a space atmosphere collection device arranged at the front end of the air breathing type helicon wave plasma electric propulsion device, wherein the rear end of the space atmosphere collection device is in sealed connection with a discharge cavity; the space atmosphere collected by the space atmosphere collection device enters the discharge cavity and is ionized by using a helicon wave discharge manner, so as to form helicon wave plasma; and meanwhile, the helicon wave plasma is affected by a magnetic confinement device, and kinetic energy of circumferential motion of the helicon wave plasma is gradually transformed to kinetic energy of parallel motion and sprayed out at a device spray nozzle at the rear end of the discharge cavity, so as to provide propulsion force for a spacecraft. Compared with a traditional electric propulsion technology carrying fuel, the air breathing type helicon wave plasma electric propulsion device does not need to carry working media, so that the weight of a platform of the spacecraft can be lightened and on-orbit whole life-cycle operation of the spacecraft can be realized.

Description

Air-breathing helical wave electric propulsion

technical field

The invention relates to the technical field of spacecraft propulsion and space environment utilization, in particular to an air-breathing helical wave electric propulsion device.

Background technique

As an advanced space propulsion technology, the research and application of electric propulsion technology has achieved great success. The most famous application of electric propulsion technology, such as: NASA used a xenon ion engine on the "Deep Space One" probe, and the SMART-1 probe launched by the European Space Agency successfully sent the spacecraft into the lunar orbit. Currently, Hall thrusters and ion thrusters are typical representatives of electric thrusters. In recent years, helicon wave plasma electric propulsion has attracted people's attention.

Helicon wave plasma electric propulsion has the characteristics of small size, light weight, high efficiency, economical and durable. In 2009, researchers from the Massachusetts Institute of Technology and the Australian National University independently proposed the concept of helical wave plasma electric propulsion. The Australian National University also developed a helical wave electric double-layer plasma thruster in 2009. The helical wave electric double-layer plasma thruster has no moving parts, no discharge electrodes and other parts that may degrade their functions. In contact with the plasma jet is glass or ceramic, which can withstand high temperatures without problems. The European Astrom company has funded the cooperation between the University of Surrey and the Australian National University to test the propulsion performance of the helicon plasma electric thruster on the LEO orbit for the first time in recent years.

The helical wave plasma electric thruster ejects the plasma at a speed of about 40km/s through the magnetic nozzle, which is nearly an order of magnitude higher than the specific impulse of the chemical thruster. The helical wave plasma thruster was born out of the American astronaut Zhang Fulin (astronaut Franklin Chang-Diaz)'s variable specific impulse magnetized plasma rocket concept (VASIMR). The small helicon plasma thruster is the first electric thruster using nitrogen as the working fluid. Nitrogen gas is pumped into a quartz glass tube wrapped around a coil antenna and magnet, and RF power is transmitted through the antenna into the nitrogen gas and ionizes the nitrogen gas. Magnets increase the density of the ionized plasma and guide and accelerate the plasma out of the thrusters.

Although helicon wave plasma electric propulsion has many advantages, it needs to carry a certain amount of working fluid just like traditional chemical propulsion and electric propulsion. This will occupy the platform weight of the spacecraft, increase the launch cost, and restrict the operational life of the spacecraft at the same time.

Therefore, the current international aerospace community is actively developing various propulsion technologies based on the utilization of the space environment. Including solar sails, magnetic sails, and magnetic motors are all new technologies developed on the basis of light, electricity, and magnetism in the space environment.

Contents of the invention

Therefore, the present invention solves the problem that the existing helical wave plasma electric propulsion needs to carry fuel, and carrying fuel will increase the launch weight of the spacecraft and increase the launch cost. The problem of limited on-orbit life of the device. The present invention proposes an air-breathing helical wave plasma electric propulsion device. From the perspective of space environment utilization, a space atmosphere collection device is installed at the front end of the existing helical wave electric propulsion device, and the space atmosphere replaces the existing spiral wave electric propulsion device. The gas working fluid carried by the wave electric thruster itself.

In order to solve the above technical problems, the present invention adopts the following technical solutions.

An air-breathing helical wave plasma electric propulsion device, including a space atmosphere collection device, a discharge chamber, a radio frequency antenna, a magnetic confinement device, a radio frequency generator and a nozzle, the space atmosphere collection device is arranged on the forward position of the spacecraft in orbit The front end of the propelling device collects the space atmosphere along with the forward movement of the spacecraft in orbit. The space atmosphere collection device is sealed and connected with one end of the discharge chamber. The space atmosphere collected by the space atmosphere collection device enters the discharge chamber and is subjected to radio frequency generation. The radio frequency discharge device composed of a device and a radio frequency antenna is ionized in the form of a helicon wave discharge to form a helicon wave plasma. The nozzle at the end of the discharge chamber is ejected to provide propulsion for the spacecraft.

Further, the above-mentioned space air collection device is a space air collection device with gradually reduced cross-sectional area, preferably a trumpet-shaped space air collection device.

Furthermore, the radio frequency discharge device ionizes the space atmosphere in the form of helicon wave discharge.

A use of the above-mentioned propulsion system, wherein the propulsion system is arranged on the side of the spacecraft, using the atmosphere in the orbital space environment as a working medium, ionized in a helical wave manner, and then accelerating the ejection of a magnetic confinement device to propel the spaceflight The in-orbit movement of the device.

Compared with the existing helicon wave electric propulsion device, the air-breathing helicon wave plasma electric propulsion device does not need to carry working fluid, can significantly reduce the weight of the propulsion device, and can realize the full life cycle of the spacecraft on orbit, which has great advantages.

Description of drawings

FIG. 1 is a schematic diagram of an air-breathing helicon wave plasma electric propulsion device of the present invention.

In the figure: 1-space atmosphere collection device; 2-discharge cavity; 3-radio frequency antenna; 4-magnetic confinement device; 5-radio frequency generator; 6-nozzle.

Detailed ways

The air-breathing helicon wave plasma electric propulsion device of the present invention will be described in detail below in conjunction with the accompanying drawings. The specific implementation is only for the purpose of illustration and is not intended to limit the protection scope of the present invention.

Referring to FIG. 1 , the air-breathing helicon wave plasma electric propulsion device of the present invention includes a space atmosphere collection device 1 , a discharge chamber 2 , a radio frequency antenna 3 , a magnetic confinement device 4 , a radio frequency generator 5 and a nozzle 6 . The space atmosphere collection device 1 is arranged at the front end of the propulsion device propelling forward with the orbiting spacecraft, and the space atmosphere rushes into the space atmosphere collection device 1 along with the forward motion of the on-orbit spacecraft. The space atmosphere collection device 1 and the discharge chamber 2 is sealed at one end. The cross-sectional area of the space atmosphere collecting device 1 is gradually reduced, such as a trumpet-shaped space atmosphere collecting device. The space atmosphere collected by the space atmosphere collection device 1 during the forward movement of the spacecraft, after entering the discharge chamber 2, will be ionized by the radio frequency generator 5 and the radio frequency antenna 3 in the form of helical wave discharge, the helical wave The discharge oxygen plasma is affected by the magnetic confinement device 4 and moves toward the nozzle 6 at the end of the device. The circumferential motion of the plasma is gradually transformed into a parallel motion, and finally ejected from the nozzle to provide propulsion for the spacecraft.

The air-breathing helical wave plasma electric propulsion device of the present invention is particularly suitable for propelling spacecraft moving in orbit in a space environment. When using the propulsion system, the propulsion system is arranged on the side of the spacecraft to utilize the The atmosphere in the atmosphere is used as the working medium, ionized by helical waves, heated by ion gyrations, and then ejected by acceleration to propel the orbital motion of the spacecraft.

Although the specific embodiments of the present invention have been described and illustrated in detail above, it should be pointed out that we can make various changes and modifications to the above embodiments, but these do not depart from the spirit of the present invention and the appended rights. Request the range described.

Claims (5)

1. the Helicon wave plasma electric propulsion device of an air-inlet type; Comprise space atmosphere gathering-device (1), discharge cavity (2), radio-frequency antenna (3), magnetic confinement device (4), radio-frequency signal generator (5) and spout (6); Space atmosphere gathering-device (1) is arranged on along with the advancing means front end of pushing ahead at the rail astrovehicle and along with in the progressive motion of rail astrovehicle and the collection space atmosphere; Space atmosphere gathering-device (1) is tightly connected with an end of discharge cavity (2), and the collected space atmosphere of space atmosphere gathering-device (1) enters into discharge cavity (2), receives the radio frequency discharge device effect that radio-frequency signal generator (5) and radio-frequency antenna (3) are formed; Mode ionization with the helicon discharge; Form Helicon wave plasma, Helicon wave plasma receives the effect of magnetic confinement device simultaneously, and its circumferential movement kinetic energy changes parallel motion kinetic energy gradually into; Locate ejection at the terminal spout (6) of discharge cavity, for astrovehicle provides propelling force.

2. electric propulsion device as claimed in claim 1, wherein, said space atmosphere gathering-device is the diminishing space of a sectional area atmosphere gathering-device.

3. electric propulsion device as claimed in claim 2, wherein, space atmosphere gathering-device is the space atmosphere gathering-device of horn shape.

4. electric propulsion device as claimed in claim 1, wherein, the radio frequency discharge device is with helicon discharge mode ionization space atmosphere.

5. the purposes of each said propulsion system of claim 1-4; Wherein, Said propulsion system is arranged on the side of astrovehicle, utilizes atmosphere in the orbit space environment as working medium, through the ionization of helicon mode; Helicon wave plasma advances moving at rail of astrovehicle through the ejection of magnetic confinement device modulates.

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