CN103696919A - Electrostatic propeller - Google Patents
Electrostatic propeller Download PDFInfo
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- CN103696919A CN103696919A CN201310727788.1A CN201310727788A CN103696919A CN 103696919 A CN103696919 A CN 103696919A CN 201310727788 A CN201310727788 A CN 201310727788A CN 103696919 A CN103696919 A CN 103696919A
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- lead
- heat
- cooled fast
- propulsion device
- steam
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Abstract
The invention provides an electrostatic propeller which comprises a lead-cooled fast reactor, a direct-current generator, a booster, a cargo bay, a fairing, a circulating booster pump, heat transfer fins and positive ionization nets. The lead-cooled fast reactor provides high-temperature lead steam to drive the direct-current generator to generate power, a positive pole of direct current is connected with the positive ionization nets, a negative pole of the direct current is connected with heat transfer fins, the lead steam finishing acting is cooled via the heat transfer fins into liquid, and then the liquid is pushed into the lead-cooled fast reactor via the circulating booster pump to absorb heat again to become steam for circulation. In the way, atomic energy is taken as an energy source, then atmosphere in space is taken as a working substance, and ionization and heating modes are used for driving, so that dead weight is reduced, high thrust is obtained, and the electrostatic propeller can be used for rocket launching operation in multiple travels.
Description
Affiliated technical field
The present invention relates to a kind of propulsion device, a kind of especially rocket propulsion.
Background technique
Current rocket propulsion is self-contained fuel and oxygenant substantially, like this because oxygenant weight is large, so container volume super large, mainly that chemical propellant is substantially all disposable, such fuel cost is also very high, has greatly improved launch cost, makes aerospace industry be difficult to civil nature.
In addition, electric propulsion device claims again electrical rocket, and the U.S. rocket pioneer Ge Dade of 20 beginnings of the century has just proposed the imagination of electric propulsion device, but due to technical capability problem, until electric propulsion device just starts progressively to become a reality after the 1950's.Press propellant agent accelerated mode different, it can be divided into three kinds of main Types such as electric heating type propulsion device, electrostatic propulsion device and electromagnetic type propulsion device.Electrothermal propeller also can be further subdivided into the types such as arc heating, resistance heating and microwave heating, wherein resistance heating propulsion device is that early stage most widely used a kind of electricity pushes away type, its current resistance heating propulsion device simple in structure specific impulse was brought up to about 900 seconds, the angle of rake high specific impulse of arc heating is equally in this rank, because the lower current electrothermal propeller of specific impulse has exited the ranks of main flow electric propulsion device.The electric heating type propulsion device relatively fading out, relies on the electromagnetic type propulsion device of electromagnetic field Lorentz force acceleration still mainly in the development stage, not yet on military or civil spacecraft, is applied, and the main flow of electric propulsion device is electrostatic propulsion device at present.Typical electrostatic propulsion device comprises Hall effect propulsion device and ion propeller, and this is also the main Types in current electric propulsion device.
But these angle of rake propelling powers are all very little, can only use when orbital motion, be not enough to use when transmitting.
summary of the invention
For the problems referred to above, the object of the present invention is to provide a kind of rocket propulsion of high thrust.
The technical solution adopted for the present invention to solve the technical problems is:
An electrostatic propulsion device, is characterized in that by Lead cooled fast breeder reactor DC generator, booster, cargo compartment, cowling, circulation compression pump, heat-exchange fin, anodal ionization net forms, and provides high temperature lead steam to promote DC generator generate electricity by Lead cooled fast breeder reactor, the direct current of sending out is anodal connects anodal ionization net, negative pole connects heat-exchange fin, and the lead steam of finishing merit is liquid through dispelling the heat into through heat-exchange fin, then through circulation compression pump, is pressed into Lead cooled fast breeder reactor and again absorbs heat and become steam and circulate.
Beneficial effect of the present invention is: adopt atomic power to originate as ability, then using the atmosphere in space as operation material, by the mode of ionization and heating, drive, thereby reduce deadweight and obtain high thrust.
Accompanying drawing explanation
Accompanying drawing is schematic diagram of the present invention.
Wherein: 1, cowling; 2, cargo compartment; 3, punching press pressure regulation core; 4, anodal ionization net; 5, circulation compression pump; 6, Lead cooled fast breeder reactor; 7, DC generator; 8, heat-exchange fin.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described:
A kind of electrostatic propulsion device, it is characterized in that by Lead cooled fast breeder reactor 6, DC generator 7, booster, cargo compartment 2, cowling 1, circulation compression pump 5, heat-exchange fin 8, anodal ionization net 4 forms, and by Lead cooled fast breeder reactor 6, provides high temperature lead steam to promote DC generator 7 generatings, the direct current of sending out is anodal connects anodal ionization net 4, negative pole connects heat-exchange fin 8, and the lead steam of finishing merit is liquid through dispelling the heat into through heat-exchange fin, then through circulation compression pump, is pressed into Lead cooled fast breeder reactor and again absorbs heat and become steam and circulate.
In concrete enforcement, there is a lot of enforcement and optimize details:
Optimized project one, direct current, after boosting, reaches 30000～55000V.
Optimized project two, can suitably carry a small amount of liquid water, exchange heat drop heat, and the operation material in vacuum environment is provided.
Optimized project three, reaches adjustment thrust by adjusting voltage after rocket launching, after 10-50KM reaches the first cosmic velocity with interior atmospheric layer, becomes rail to outer space.
Electrostatic propulsion device of the present invention, can be for repeatedly round rocket launching operation.
Claims (3)
1. an electrostatic propulsion device, is characterized in that by Lead cooled fast breeder reactor DC generator, booster, cargo compartment, cowling, circulation compression pump, heat-exchange fin, anodal ionization net forms, and provides high temperature lead steam to promote DC generator generate electricity by Lead cooled fast breeder reactor, the direct current of sending out is anodal connects anodal ionization net, negative pole connects heat-exchange fin, and the lead steam of finishing merit is liquid through dispelling the heat into through heat-exchange fin, then through circulation compression pump, is pressed into Lead cooled fast breeder reactor and again absorbs heat and become steam and circulate.
2. electrostatic propulsion device according to claim 1, is characterized in that direct current, after boosting, reaches 30000～55000V.
3. electrostatic propulsion device according to claim 1, is characterized in that carrying a small amount of liquid water, exchange heat drop heat, and the operation material in vacuum environment is provided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310727788.1A CN103696919A (en) | 2013-12-26 | 2013-12-26 | Electrostatic propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310727788.1A CN103696919A (en) | 2013-12-26 | 2013-12-26 | Electrostatic propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103696919A true CN103696919A (en) | 2014-04-02 |
Family
ID=50358561
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310727788.1A Pending CN103696919A (en) | 2013-12-26 | 2013-12-26 | Electrostatic propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103696919A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108533469A (en) * | 2018-03-09 | 2018-09-14 | 中国科学院微电子研究所 | Self-heating type electric propulsion device working substance supply device and electric propulsion device |
-
2013
- 2013-12-26 CN CN201310727788.1A patent/CN103696919A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108533469A (en) * | 2018-03-09 | 2018-09-14 | 中国科学院微电子研究所 | Self-heating type electric propulsion device working substance supply device and electric propulsion device |
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Legal Events
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140402 |