CN105736182A - Antiproton rocket engine - Google Patents
Antiproton rocket engine Download PDFInfo
- Publication number
- CN105736182A CN105736182A CN201610090459.4A CN201610090459A CN105736182A CN 105736182 A CN105736182 A CN 105736182A CN 201610090459 A CN201610090459 A CN 201610090459A CN 105736182 A CN105736182 A CN 105736182A
- Authority
- CN
- China
- Prior art keywords
- antiproton
- rocket engine
- expansion box
- engine
- generator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Abstract
The invention discloses an antiproton rocket engine. The antiproton rocket engine comprises an engine shell, an antiproton generator is arranged at the front end of the engine shell, a spray pipe assembly is arranged on the tail portion of the engine shell, and a middle segment comprises an antiproton lead-out pipeline, an annihilation device, a heat conversion chamber and an air storage box; the air storage box is fixedly mounted on the inner wall face of the engine shell, the annihilation device is arranged on the outer wall of one side of the air storage box, one end of the annihilation device is connected with the antiproton generator through the antiproton lead-out pipeline, and the other end of the annihilation device is connected with the heat conversion chamber; and the engine shell and the spraying pipe assembly are connected in a sleeved manner. The antiproton rocket engine has the beneficial effects of being high in specific impulse, long in service life, high in speed, free of pollution, high in efficiency and the like and is used for attitude control of a deep space probe, and the effective load quality can be obviously improved.
Description
Technical field
The invention belongs to technical field of engines, particularly to a kind of antiproton rocket engine.
Background technology
Rocket engine is the important component part of aircraft, its major function be for missile armament, carrier rocket and satellite accelerate become rail and return land provide required power set.Although the rocket engine of present stage achieves more satisfactory effect in form, but still suffer from many problems in many aspects, exist basic problem have: one be tradition rocket engine specific impulse be restricted, all there is a bottleneck value in specific impulse produced by Conventional solid, liquid fuel；Two is that the use condition of electromotor is restricted, for solid rocket ramjet, Liquid fuel ramjet engine, certain air quantity of the catch must be provided by the external world, guarantee engine high-efficiency works reliably, and the working depth of electromotor, operating rate and the attitude in flight moment are proposed higher requirement by this；Three be at present overwhelming majority rocket engines combustion product all can to ambient atmosphere environmental effects, by discharge of poisonous waste to air.
Summary of the invention
The present invention solves above-mentioned technical problem, it is provided that a kind of structure is relatively simple, be prone to processing, installs easy to operate, and has the antiproton rocket engine of higher total punching.
For solving the problems referred to above, the present invention adopts the technical scheme that: a kind of antiproton rocket engine, including motor body 7, described motor body 7 front end is provided with antiproton generator 1, afterbody is provided with nozzle component 8, and interlude includes antiproton and draws pipeline 2, buries in oblivion device 3, heat switch room 5 and expansion box 6；Described expansion box 6 is fixedly mounted on the internal face of motor body 7；Described expansion box 6 side has bleed hole 4, and described bleed hole 4 is installed valve；Hydrogen is stored in described expansion box 6；Described expansion box 6 side outer wall is provided with buries in oblivion device 3, described in bury in oblivion device 3 one end by antiproton draw pipeline 2 be connected with described antiproton generator 1, the other end is connected with heat switch room 5；Described motor body 7 is socketed with described nozzle component 8.
Preferably, described bleed hole 4 is installed valve, opening and Guan Bi by valve, control hydrogen in expansion box 6 and enter the opportunity of heat switch room 5, improve capacity usage ratio, increase engine/motor specific impulse.
Preferably, described bleed hole 4 quantity is at least 1, is uniformly distributed,
Preferably, described bleed hole 4 quantity is 4, is uniformly distributed, and what make that meson and hydrogen blends is more uniform, improves energy conversion efficiency.
Preferably, described expansion box 6 contacts wall with heat switch room 5 and scribbles heat-barrier material, thus allowing higher fuel gas temperature, and avoiding dissipating outside heat, improving energy conversion efficiency.
Preferably, described nozzle component 8 upper end adopts sealing ring to seal, and makes system under the flowing environment of High Temperature High Pressure high-speed gas, and air-tightness is ensured.
Compared with prior art, the invention has the beneficial effects as follows:
A kind of antiproton rocket engine provided by the invention, compact conformation is simple, easily assembling；Space availability ratio is high, easy care；Security reliability is high, easily promotes.In each parts junction, adopt screw thread or alternate manner to be connected, decrease the lay day of antiproton rocket engine, add intensity and the rigidity of antiproton rocket engine.Adopting modularized design for each parts, can individually parts being safeguarded, thus reducing workload.Contact wall at expansion box with heat switch room and scribble heat-barrier material, thus allowing higher fuel gas temperature, and avoiding dissipating outside heat, improving energy conversion efficiency.Adopting in nozzle component upper end sealing ring to seal, make system under the flowing environment of High Temperature High Pressure high-speed gas, air-tightness is ensured.
A kind of antiproton rocket engine provided by the invention, has than leaping high, the life-span is long, speed is fast, pollution-free, efficiency advantages of higher, and the gesture stability for deep space probe can dramatically increase payload mass.
Accompanying drawing explanation
Fig. 1 is present configuration schematic diagram.
Drawing reference numeral: 1, antiproton generator；2, antiproton draws pipeline；3, device is buried in oblivion；4, bleed hole；5, heat switch room；6, expansion box；7, motor body；8, nozzle component.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiments of the present invention are done more detailed description.
Referring to accompanying drawing 1, a kind of antiproton rocket engine, including motor body 7, described motor body 7 front end is provided with antiproton generator 1, afterbody is provided with nozzle component 8, and interlude includes antiproton and draws pipeline 2, buries in oblivion device 3, heat switch room 5 and expansion box 6；Described expansion box 6 is fixedly mounted on the internal face of motor body 7；Described expansion box 6 side has bleed hole 4, and described bleed hole 4 is installed valve；Hydrogen is stored in described expansion box 6；Described expansion box 6 side outer wall is provided with buries in oblivion device 3, described in bury in oblivion device 3 one end by antiproton draw pipeline 2 be connected with described antiproton generator 1, the other end is connected with heat switch room 5；Described motor body 7 is socketed with described nozzle component 8.
Further, described bleed hole 4 is installed valve, opening and Guan Bi by valve, control hydrogen in expansion box 6 and enter the opportunity of heat switch room 5.When only occurring annihilation reaction to produce a large amount of meson in burying in oblivion device 3, just open valve, valve is closed at ordinary times, if meson does not carry out energy with hydrogen in heat switch room 5, conversion directly sprays from nozzle component 8, the energy of meeting large losses, capacity usage ratio is very low, and engine/motor specific impulse will be substantially reduced, and namely produced thrust also greatly reduces.
Further, described bleed hole 4 quantity is at least 1, is uniformly distributed.
Further, described bleed hole 4 quantity is 4, is uniformly distributed, and what make that meson and hydrogen blends is more uniform, improves energy conversion efficiency.
Further, described expansion box 6 contacts wall with heat switch room 5 and scribbles heat-barrier material, thus allowing higher fuel gas temperature, and avoiding dissipating outside heat, improving energy conversion efficiency.
Further, described nozzle component 8 upper end adopts sealing ring to seal, and makes system under the flowing environment of High Temperature High Pressure high-speed gas, and air-tightness is ensured.
By the effect in magnetic field, antiproton in antiproton generator 1 draws pipeline 2 by antiproton, clash into and bury in oblivion the positive material generation annihilation reaction in device 3 and produce a large amount of meson, the valve on expansion box 6 is opened while carrying out annihilation reaction, cold hydrogen is discharged in heat switch room 5, meson carries a large amount of heat energy and carries out energy conversion in heat switch room with hydrogen, and final hydrogen sprays through nozzle component 8 place after being heated to high temperature, thus producing thrust.
Listed above is only specific embodiments of the invention.It is clear that the invention is not restricted to above example, it is also possible to there are many similar reshapings.All deformation that those of ordinary skill in the art can directly derive from present disclosure or associate, are all considered as invention which is intended to be protected.
Claims (4)
1. an antiproton rocket engine, it is characterized in that: include motor body (7), described motor body (7) front end is provided with antiproton generator (1), afterbody is provided with nozzle component (8), and interlude includes antiproton and draws pipeline (2), buries in oblivion device (3), heat switch room (5) and expansion box (6)；Described expansion box (6) is fixedly mounted on the internal face of motor body (7)；Described expansion box (6) side has bleed hole (4), and described bleed hole (4) installs valve；Hydrogen is stored in described expansion box (6)；Described expansion box (6) side outer wall is provided with buries in oblivion device (3), described in bury in oblivion device (3) one end and draw pipeline (2) by antiproton and be connected with described antiproton generator (1), the other end is connected with heat switch room (5)；Described motor body (7) and described nozzle component (8) socket.
2. a kind of antiproton rocket engine according to claim 1, it is characterised in that: described bleed hole (4) quantity is at least 1, is uniformly distributed.
3. a kind of antiproton rocket engine according to claim 2, it is characterised in that: described bleed hole (4) quantity is 4, is uniformly distributed.
4. a kind of antiproton rocket engine according to claim 1, it is characterised in that: described expansion box (6) contacts wall with heat switch room (5) and scribbles heat-barrier material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090459.4A CN105736182A (en) | 2016-02-18 | 2016-02-18 | Antiproton rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090459.4A CN105736182A (en) | 2016-02-18 | 2016-02-18 | Antiproton rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105736182A true CN105736182A (en) | 2016-07-06 |
Family
ID=56246044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610090459.4A Pending CN105736182A (en) | 2016-02-18 | 2016-02-18 | Antiproton rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105736182A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3423665A1 (en) * | 1984-06-27 | 1986-01-09 | geb. Wegener Regina Dipl.-Volksw. 6270 Idstein Koch | Proton engine for rocket engines |
| WO2002086317A1 (en) * | 2001-04-25 | 2002-10-31 | De La Pena Llaca Fernando | Antimatter engine |
| CN101839207A (en) * | 2009-03-20 | 2010-09-22 | 李贵祥 | Atomic motion simulator |
| CN105209340A (en) * | 2013-03-15 | 2015-12-30 | 帕尔默实验室有限责任公司 | Launch vehicle and system and method for economically efficient launch thereof |
-
2016
- 2016-02-18 CN CN201610090459.4A patent/CN105736182A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3423665A1 (en) * | 1984-06-27 | 1986-01-09 | geb. Wegener Regina Dipl.-Volksw. 6270 Idstein Koch | Proton engine for rocket engines |
| WO2002086317A1 (en) * | 2001-04-25 | 2002-10-31 | De La Pena Llaca Fernando | Antimatter engine |
| CN101839207A (en) * | 2009-03-20 | 2010-09-22 | 李贵祥 | Atomic motion simulator |
| CN105209340A (en) * | 2013-03-15 | 2015-12-30 | 帕尔默实验室有限责任公司 | Launch vehicle and system and method for economically efficient launch thereof |
Non-Patent Citations (1)
| Title |
|---|
| 杨乐、吴建军: "反物质湮灭推进", 《万方数据 企业知识服务平台》 * |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160706 |