CN105756810A - High-efficiency solid hybrid power rocket engine method and device - Google Patents

Abstract

The invention discloses a high-efficiency solid hybrid power rocket engine method and device and belongs to the field of rocket engines.The operating method comprises the step of further adding an expanding agent to a combustion chamber (1) except gunpowder, wherein the expanding agent is a solid gasified expanding agent.The high-efficiency solid hybrid power rocket engine device adopting the method comprises the combustion chamber (1), a jet nozzle (2), a powder grain (3) and an expanding agent grain (4).The high-efficiency solid hybrid power rocket engine method and the device can effectively reduce working temperature, improve heat efficiency and improve infrared characteristics and avoid damage to a combustion chamber throat, the material and process requirements are reduced, the material processing cost is reduced, and the selected expanding agent is ammonium carbonate, ammonium bicarbonate, dry ices, ices and the like, is stable in store, easy to process and form, not high in decomposition temperature and few in decomposed solid matter, environmentally-friendly and pollution-free and is not likely to crack.

Description

A kind of high-performance solid hybrid power rocket engine method and device

Technical field

The present invention relates to rocket engine field, be specifically related to a kind of high-performance solid hybrid power rocket engine method and device.

Background technology

Rocket engine utilizes impulse principle exactly, and the jet carry propellant, being independent of outside air is started.Major part electromotor obtains thrust, solid or liquid propellant (by oxidant and fuel composition) high pressure (10 ~ 200bar) in a combustion chamber burning generation tail gas by discharging high temperature and high speed tail gas.No matter the fuel of rocket is solid or liquid, when burning, it is brought rapidly up, gasification, reaches 2,000 degree to 3,000 degree degrees Celsius, because expanded by heating, it is limited within the scope of combustor, forming very big pressure, when the waste gas of burning sprays backward, the tail gas of ejection speed after Laval nozzle has reached supersonic speed.Along with expansion, speed increases, and pressure reduces, and temperature is also in a slight decrease, and the gas finally sprayed and air mix, and amount of heat is wasted.

Summary of the invention

Instant invention overcomes above-mentioned shortcoming, and a kind of high-performance solid hybrid power rocket engine method and device are provided.

To achieve these goals, first purpose of the present invention is to provide a kind of high-performance solid hybrid power rocket engine method, and operational approach includes being also added with extender except gunpowder in combustion chamber expansion agent powder column；Described extender is solids gasification extender.

Preferably, described operational approach wraps up extender in gunpowder internal layer.

Preferably, in gunpowder outer layer covers extender in described operational approach.

Preferably, described operational approach is uniformly admixed extender fine particle in gunpowder.

Preferably, described solids gasification extender is any one or two kinds in ammonium carbonate, ammonium hydrogen carbonate, dry ice or ice.

Preferably, described gunpowder is tradition gunpowder.

Second purpose of the present invention is to provide the device of a kind of high-performance solid hybrid power rocket engine method, for Outsourcing-type, including combustion chamber expansion agent powder column, nozzle extender powder column, stick extender powder column and extender powder column extender powder column, the tail end of described combustion chamber expansion agent powder column installs nozzle extender powder column, the middle part level of combustion chamber expansion agent powder column installs stick extender powder column, and extender powder column extender powder column installed by the outer surface parcel of stick extender powder column；Described stick extender powder column and extender powder column extender powder column are arranged in combustion chamber expansion agent powder column and form confined space.

3rd purpose of the present invention is to provide the device of a kind of high-performance solid hybrid power rocket engine method,

For interior insert-type, including combustion chamber expansion agent powder column, nozzle extender powder column, stick extender powder column and extender powder column extender powder column, the tail end of described combustion chamber expansion agent powder column installs nozzle extender powder column, the middle part level of combustion chamber expansion agent powder column installs extender powder column extender powder column, and stick extender powder column installed by the outer surface parcel of extender powder column extender powder column；Described stick extender powder column and extender powder column extender powder column extender powder column are arranged in combustion chamber expansion agent powder column and form confined space.

4th purpose of the present invention is to provide the device of a kind of high-performance solid hybrid power rocket engine method, for alternate type, including combustion chamber expansion agent powder column, nozzle extender powder column, stick extender powder column and extender powder column extender powder column, the tail end of described combustion chamber expansion agent powder column installs nozzle extender powder column, and the middle part of combustion chamber expansion agent powder column replaces, level of intersecting installs stick extender powder column and extender powder column extender powder column；Described stick extender powder column and extender powder column extender powder column are arranged in combustion chamber expansion agent powder column and form confined space.

Preferably, the longitudinal cross-section of described combustor (1) is any one in circular, rectangle or rhombus.

The invention has the beneficial effects as follows: utilize gunpowder fuel heat to expand by extender heat absorption, thus providing bigger

Expulsion pressure.Compared with tradition rocket engine, first, can effectively reduce work temperature section, improve thermal effect

Rate, improves infrared characteristic, it is to avoid the damage to combustor venturi；Secondly, reduce material, technological requirement,

Materials processing cost reduces；Again, ammonium carbonate, ammonium hydrogen carbonate, dry ice and ice etc., stable storing, it is easy to

Machine-shaping, not easily broken, decomposition temperature is all not high, decomposes solid content few, and environmental protection is colourless, nontoxic,

Harmless.

Accompanying drawing explanation

Fig. 1 is the Outsourcing-type structural representation of high-performance solid hybrid power rocket motor machine in invention.

Fig. 2 is the interior insert-type structural representation of high-performance solid hybrid power rocket motor machine in invention.

Fig. 3 is the alternate type structural representation of high-performance solid hybrid power rocket motor machine in invention.

Wherein, 1, combustor, 2, nozzle, 3, stick, 4, extender powder column.

Detailed description of the invention

Referring to Fig. 1, one embodiment of the invention is to provide the device of a kind of high-performance solid hybrid power rocket engine method, for Outsourcing-type, including combustion chamber expansion agent powder column 1 extender powder column, nozzle extender powder column 2 extender powder column, stick extender powder column 3 extender powder column and extender powder column extender powder column 4 extender powder column, the tail end of combustion chamber expansion agent powder column 1 extender powder column installs nozzle extender powder column 2 extender powder column, the middle part level of combustion chamber expansion agent powder column 1 extender powder column installs stick extender powder column 3 extender powder column, extender powder column extender powder column 4 extender powder column installed by the outer surface parcel of stick extender powder column 3 extender powder column；Stick extender powder column 3 extender powder column and extender powder column extender powder column 4 extender powder column are arranged in combustion chamber expansion agent powder column 1 extender powder column and form confined space.

Referring to Fig. 2, the present invention provides the device of a kind of high-performance solid hybrid power rocket engine method for another embodiment of the present invention, for interior insert-type, including combustion chamber expansion agent powder column 1 extender powder column, nozzle extender powder column 2 extender powder column, stick extender powder column 3 extender powder column and extender powder column extender powder column 4 extender powder column, the tail end of combustion chamber expansion agent powder column 1 extender powder column installs nozzle extender powder column 2 extender powder column, the middle part level of combustion chamber expansion agent powder column 1 extender powder column installs extender powder column extender powder column 4 extender powder column, stick extender powder column 3 extender powder column installed by the outer surface parcel of extender powder column extender powder column 4 extender powder column；Stick extender powder column 3 extender powder column and extender powder column extender powder column extender powder column 4 extender powder column are arranged in combustion chamber expansion agent powder column 1 extender powder column and form confined space.

Referring to Fig. 3, one more embodiment of the present invention is to provide the device of a kind of high-performance solid hybrid power rocket engine method, for alternate type, including combustion chamber expansion agent powder column 1 extender powder column, nozzle extender powder column 2 extender powder column, stick extender powder column 3 extender powder column and extender powder column extender powder column 4 extender powder column, the tail end of combustion chamber expansion agent powder column 1 extender powder column installs nozzle extender powder column 2 extender powder column, the middle part of combustion chamber expansion agent powder column 1 extender powder column is alternately, intersection level installs stick extender powder column 3 extender powder column and extender powder column extender powder column 4 extender powder column；Stick extender powder column 3 extender powder column and extender powder column extender powder column 4 extender powder column are arranged in combustion chamber expansion agent powder column 1 extender powder column and form confined space.

Wherein, the longitudinal cross-section of the combustion chamber expansion agent powder column 1 extender powder column of above three embodiment is any one in circular, rectangle or rhombus.

In above three embodiment, its high-performance solid hybrid power rocket engine method, operational approach includes being also added with extender except gunpowder in combustion chamber expansion agent powder column 1 extender powder column；Described extender is solids gasification extender；Operational approach wraps up extender in gunpowder internal layer；In gunpowder outer layer covers extender in operational approach；Operational approach is uniformly admixed extender fine particle in gunpowder；Solids gasification extender is any one or two kinds in ammonium carbonate, ammonium hydrogen carbonate, dry ice or ice；Gunpowder is tradition gunpowder.After lighting gunpowder, powder burning, release heat, this heat is transferred to extender with photothermal form, and extender gasifies and is converted into pressure and promotes rocket to run, in this process, reach to obtain bigger pressure with the means of heat transmission, thus causing the purpose that jet velocity is accelerated.

Comparing tradition rocket engine, system stagnation temperature section is reduced, and apparatus surface temperature reduces, and requires to reduce to equipment and materials, and while Financial cost also obtains reduction, invented solid gas agent is environment friendly and pollution-free, more meets sustainable development requirement.

The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; described in above-described embodiment and description is that principles of the invention is described; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within the claimed scope of the invention.Claimed scope is defined by appending claims and equivalent thereof.

Claims (10)

1. a high-performance solid hybrid power rocket engine method, it is characterised in that operational approach includes being also added with extender except gunpowder in combustor (1)；Described extender is solids gasification extender.

2. high-performance solid hybrid power rocket engine method according to claim 1, it is characterised in that wrap up extender in gunpowder internal layer in described operational approach.

3. high-performance solid hybrid power rocket engine method according to claim 1 and 2, it is characterised in that in gunpowder outer layer covers extender in described operational approach.

4. high-performance solid hybrid power rocket engine method according to claim 1, it is characterised in that uniformly admix extender fine particle in described operational approach in gunpowder.

5. high-performance solid hybrid power rocket engine method according to claim 1, it is characterised in that described solids gasification extender is any one or two kinds in ammonium carbonate, ammonium hydrogen carbonate, dry ice or ice.

6. high-performance solid hybrid power rocket engine method according to claim 1, it is characterised in that described gunpowder is tradition gunpowder.

7. the device of high-performance solid hybrid power rocket engine method as claimed in claim 1, it is characterized in that, it is Outsourcing-type, including combustor (1), nozzle (2), stick (3) and extender powder column (4), the tail end of described combustor (1) installs nozzle (2), the middle part level of combustor (1) installs stick (3), and extender powder column (4) installed by the outer surface parcel of stick (3)；Described stick (3) and extender powder column (4) are arranged in combustor (1) and form confined space.

8. the device of high-performance solid hybrid power rocket engine method as claimed in claim 1, it is characterized in that, for interior insert-type, including combustor (1), nozzle (2), stick (3) and extender powder column (4), the tail end of described combustor (1) installs nozzle (2), the middle part level of combustor (1) installs extender powder column (4), and stick (3) installed by the outer surface parcel of extender powder column (4)；Described stick (3) and extender powder column extender powder column (4) are arranged in combustor (1) and form confined space.

9. the device of high-performance solid hybrid power rocket engine method as claimed in claim 1, it is characterized in that, for alternate type, including combustor (1), nozzle (2), stick (3) and extender powder column (4), the tail end of described combustor (1) installs nozzle (2), and the middle part of combustor (1) replaces, level of intersecting installs stick (3) and extender powder column (4)；Described stick (3) and extender powder column (4) are arranged in combustor (1) and form confined space.

10. the device of high-performance solid hybrid power rocket engine method according to claim 9, it is characterised in that the longitudinal cross-section of described combustor (1) is any one in circular, rectangle or rhombus.