Patent Application
20150210406
The invention relates to the field of the spacecraft propulsion and the use of the space environment, and more particularly relates to a non-fuel rail spacecraft propulsion system based on the space atomic oxygen and a method to propel the rail spacecraft continuous movement based on the system.
The propulsion technique can be divided into the chemical propulsion and electric propulsion, as well as some other propulsion technique (such as solar sail, tethered propulsion and the like). At present, most main thrusters of spacecraft employ the chemical propulsion. But as an advanced propulsion technique, the electric propulsion is getting more and more attention.
The chemical propulsion is a propulsion technique using the chemical energy to send the spacecraft into the reserved space rail and realizes the orbit maneuver. The most prominent feature of the chemical propulsion is high propulsion, which is the most used technique in the space field. The chemical engine is used in the present long-life tri-axial attitude control stabilized satellite and spin satellite as a controlling and executing assembly. There are two work modes of the chemical engine: pulsating work and stability work. The pulsating work is most used in the satellite attitude-adjusting and position-retaining; the stability work is most used in the satellite-orbit maneuver.
Electric propulsion provides energy to the propellant using the electricity generated and produced by the solar panel and nuclear reactor, to make the propellant producing the jet velocity far more than the common chemical thruster. High specific impulse of electric propulsion can reduce the system quality, save the propellant, improve the life and increase the payload. Besides applying in the long-life communication satellite to improve the performance of the satellite platform, the electric propulsion can complete the tasks which the common propulsion system is unable to do.
Both the chemical propulsion and electric propulsion need to carry certain propellant, which not only occupy the weight of the spacecraft platform but also greatly increase the launch costs. Meanwhile the orbit-maneuver life of the spacecraft depends on the carried fuel quantity. The propulsion mode depends on the carried fuel and seriously restricts the spacecraft platform function extension and service life prolongation. So, the present international space field is actively developing all kinds of propulsion techniques based on the use of space environment. All the new techniques, including the solar sail, magnetic sail, magnetic engine or the like, are developed based on the use of the space environment of light, electric, magnetic and the like.
The invention solves the problem that the propulsion method of the present spacecraft carrying fuel has the high-cost launch. The spacecraft orbit life depends on the amount of the carried fuel resulting in the restriction of the spacecraft orbit life. The invention uses space atomic oxygen as the propellant, making the in-orbit maneuver of the spacecraft in the space environment a continuous space-rotating movement without the influence by the tiny resistance in the space environment.
To solve the aforementioned problem, the invention adopts the following technical protocols.
A fuel-free spacecraft propulsion system based on the space atomic oxygen, comprises an outer cylinder of the propulsion device with both open ends, an atomic oxygen collecting device inside the outer cylinder of the propulsion device, an RF generating device and the ion cyclotron wave heating device. The atomic oxygen collecting device is arranged at the front end of the outer cylinder of the propulsion device for propelling forwardly, and in turn is hermetically connected with the RF generating device and the iron cyclotron wave heating device through the magnetic confinement device. The inlet and outlet of a spiral wave discharge oxygen plasma in the ion cyclotron wave heating device are respectively provided with another magnetic confinement device. The atomic oxygen collecting device is used for pressurizing the space atomic oxygen entering the front end of the outer cylinder of the propulsion device during the time the spacecraft is moving forward. The pressurized space atomic oxygen is ionized in a spiral wave discharge mode in the RF generation device. The oxygen ions of the ionized oxygen plasma in the ion cyclotron wave heating device absorbs the energy of the cyclotron wave resulting in the kinetic energy increase. Magnetic field configuration (the shape and distribution of the magnetic flux) of a sprayer is changed by adjusting the magnetic confinement device inside the ion cyclotron wave heating device. Circumferential motion of the oxygen ions is transformed into parallel motion, and propulsion force is provided for the spacecraft after the oxygen ions are sprayed out of the sprayer.
Further, the aforementioned atomic oxygen collecting device has gradually diminished sectional area, preferably trumpet-type atomic oxygen collecting device.
Further, the spiral wave discharge mode of the RF generating device is produced by the RF discharging, and the ion cyclotron wave of the ion cyclotron wave heating device produced by the RF device.
Further, the aforementioned adjusting of the magnetic field is changing the magnetic field into the divergent magnetic field.
In an application of the aforementioned propulsion system, the propulsion system is arranged at both sides of the spacecraft. The atomic oxygen in the rail space environment is used as the propellant, ionized in spiral wave mode, heated by ion cyclotron, then sprayed after accelerated to propel the in-orbit maneuver of the spacecraft.
In comparison with the traditional electric propulsion technique, the propulsion of the invention does not need to carry the propellant, which greatly reduces the launch costs, enables a spacecraft to work on an orbit in the whole life circle work and is advantageous.
In
Embodiments of the fuel-free spacecraft propulsion system based on the space atomic oxygen of the invention now will be described more fully with reference to the accompanying drawings. These embodiments are provided for example, the invention should not be construed as limited to the embodiments.
In
A fuel-free spacecraft propulsion system based on the space atomic oxygen of the invention specially applies to propel the in-orbit maneuver of the spacecraft in the space environment. When using the propulsion system, the propulsion system is arranged at both sides of the spacecraft. The atomic oxygen in the rail space environment is used as the propellant, ionized in a spiral wave mode, heated by an ion cyclotron, then sprayed after acceleration to propel the in-orbit maneuver of the spacecraft.
To simply explain the process of the fuel-free spacecraft propulsion. system, the system is a cylindrical space particles collecting device, arranged at the special position of the spacecraft, to collect the atomic oxygen of the rail space environment as the spacecraft is moving. The 300 km rail space environment exists about the atomic oxygen density of 1015/m3, of which average thermal motion speed can be ignored compared with speed of the spacecraft, so the atomic oxygen in the rail can be regarded as static. The relative speed of the two is the speed of the spacecraft, about 8 km/s (the first cosmic speed).
Atomic oxygen is discharged as ion oxygen, if its kinetic energy is increased to 1 KeV by the RF heating mode, frow Ft=Δ(mv),
we can see that:
Ft=√{square root over (2m5)}
An O+ can gain the impulse of about 0.3×10−2(N·S).
Supposing that the spacecraft carries an AO collecting device with 1m2 sectional area, the collecting atomic oxygen amount per unit time is:
N=nV=nSvt
Wherein the n is the rail atomic oxygen density (1015/m3), the S is the collecting sectional area (1m2), and the v is the spacecraft motion speed (about 8 km/s), the collecting atomic oxygen amount per unit time is 8×1018.
From Ft=Δ(M
The fuel-free spacecraft propulsion is based on the space atomic oxygen. The gained propulsion force is proportional to the collecting atomic oxygen flux density per unit time, the ionization rate and the ion heating energy. If the radii of the collecting device is 1 m, the atomic oxygen is 100% ionized per unit time, and the oxygen ions are heated to 1 KeV, and the gained propulsion force is 70 mN. Even when the ionization rate is 50%, the gained propulsion force is 35 mN.
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
| Number | Date | Country | Kind |
|---|---|---|---|
| 201210159715.2 | May 2012 | CN | national |
| 201210270034.3 | Aug 2012 | CN | national |
The present invention is a U.S. national phase of PCT/CN2013/075242 filed May 7, 2013, and claims priority from Chinese patent application Serial No. 201210159715.2 filed May 22, 2012 and Chinese patent application Serial No. 201210270034.3 filed Aug. 1, 2012, the subject matter of which are incorporated herein by reference.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/CN2013/075242 | 5/7/2013 | WO | 00 |
