CN107620652A - A kind of multiple-pulse adjustable thrust Solid propeller - Google Patents
A kind of multiple-pulse adjustable thrust Solid propeller Download PDFInfo
- Publication number
- CN107620652A CN107620652A CN201610961515.7A CN201610961515A CN107620652A CN 107620652 A CN107620652 A CN 107620652A CN 201610961515 A CN201610961515 A CN 201610961515A CN 107620652 A CN107620652 A CN 107620652A
- Authority
- CN
- China
- Prior art keywords
- electrode
- external electrode
- automatically controlled
- thrust
- interior electrode
- 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.)
- Granted
Links
Landscapes
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
A kind of multiple-pulse adjustable thrust Solid propeller, including automatically controlled solid propellant unit, external electrode, interior electrode, insulating barrier, heat insulation layer, combustion chamber, jet pipe；External electrode is provided with the combustion chamber；The external electrode is on the basis of a bulk metal cylinder, is evenly arranged multiple circular hole spaces, for placing the automatically controlled solid propellant unit of multiple circular tube shapeds respectively；The interior electrode is made up of more metal cylinders, is respectively embedded into corresponding multiple automatically controlled solid propellant units of circular tube shaped, and each automatically controlled solid propellant unit contacts with external electrode and corresponding interior electrode seal respectively.Each interior electrode of the present invention is connected 1 control circuit of composition with external electrode, by controlling the break-make of each circuit, and then controls the igniting of each automatically controlled solid propellant unit, burns and stop working.The voltage swing inside and outside electrode both ends is made, and then controls the burn rate of each propellant unit so that in each working pulse, the thrust of propeller is adjustable.
Description
Technical field
The present invention relates to a kind of propeller using automatically controlled solid propellant, more particularly to multiple-pulse, thrust controllable are consolidated
Body propeller, belong to solid pulsed motor field.
Background technology
Solid propellant rocket is difficult to repeatedly start, and thrust is difficult to control.At present, start on adjustable thrust solid
Owner will start including the adjustable solid engines of nozzle throat area, decking prefabricated multistage trust engine, solid pulse
Machine and the solid engines that can stop working, but these engines can not realize that continuity repeatedly starts and thrust active STOCHASTIC CONTROL.
The content of the invention
The invention aims to overcome the above-mentioned deficiency of prior art, and provide a kind of multiple-pulse adjustable thrust solid
Propeller, easy to use, acquisition multiple-pulse, adjustable thrust.
The purpose of the present invention is achieved through the following technical solutions：Including automatically controlled solid propellant unit, external electrode, interior
Electrode, insulating barrier, heat insulation layer, combustion chamber, jet pipe；External electrode is provided with the combustion chamber；The external electrode is whole at one
On the basis of body metal cylinder, multiple circular hole spaces are evenly arranged, the automatically controlled solid for placing multiple circular tube shapeds respectively pushes away
Enter agent unit；The interior electrode is made up of more metal cylinders, is respectively embedded into corresponding multiple automatically controlled solid propellant propulsions of circular tube shaped
In agent unit, each automatically controlled solid propellant unit contacts with external electrode and corresponding interior electrode seal respectively.
The combustion chamber is a cylindrical shape, and the tube port position of combustion chamber one end is equipped with jet pipe, and the combustion chamber other end is provided with wire
Hole, the wire being connected with external power source, by wire guide, it is connected by aviation plug with external electrode and interior electrode.
The heat insulation layer, insulating barrier form adiabatic insulating barrier two, and adiabatic insulating barrier two is arranged at external electrode outer wall and burning
Between chamber interior walls, the heat insulation layer is located on the inside of insulating barrier.
The heat insulation layer, insulating barrier form adiabatic insulating barrier one, and adiabatic insulating barrier one is arranged at external electrode one end.
The adiabatic insulating barrier one is provided with multiple through holes corresponding with circular hole space, and through hole has formed with circular hole space
Whole interior electrode positioning hole, interior electrode are plugged at interior electrode positioning hole.
The external electrode both ends offset through baffle ring and combustion chamber.
Electrode sets lead cylinder, the centrally disposed stem of external electrode, using outside aviation plug each in each
Interior electrode connects into a control circuit with external electrode and external power source, and interior electrode sum is identical with control circuit sum, each
Connecting and disconnecting of the circuit and voltage swing corresponding to circuit control between interior electrode and external electrode, and then automatically controlled solid corresponding to control pushes away
Enter the fired state of agent unit.
The present invention the course of work be：A certain control circuit is connected on demand, is controlled in external electrode and the control circuit
Certain voltage is loaded between interior electrode, the automatically controlled solid propellant unit ignition contacted with the interior electrode, combustion gas is through spray
Tube swelling accelerates to produce thrust；The burn rate of propellant can be adjusted in combustion process by changing voltage swing, and then changes and pushes away
Power size；Other control circuits are in turn switched on by thrust requirements, control other automatically controlled solid propellant unit burnings respectively, so as to
Multigroup impulse force is produced, thrust is adjustable in each pulse.
Automatically controlled solid propellant unit in the present invention is a kind of controllable solid propellant of burning that can be conductive, and automatically controlled solid pushes away
Enter agent unit under power on condition, load certain voltage, igniting can be realized；Pass through the big minor adjustment of control voltage in combustion process
The burn rate of propellant, propellant extinguishes when cutting off the electricity supply, and repeatedly igniting can be achieved and stop working.Beneficial effects of the present invention：
A kind of multiple-pulse adjustable thrust Solid propeller of the present invention, the thrust of propeller can be controlled by voltage, propeller
Whole work process can all be controlled by voltage.
A kind of multiple-pulse adjustable thrust Solid propeller of the present invention, by controlling the "on" position of each propellant unit,
So that different propellant unit burning work, can obtain multiple-pulse thrust.
A kind of multiple-pulse adjustable thrust Solid propeller of the present invention, in combustion, respectively pushed away by changing to be carried in
The voltage swing regulation burn rate entered on agent unit so that in each working pulse, the thrust of propeller is adjustable.
It is of the invention to can be used for moonlet, small-sized spacecraft to require that propeller has repeatedly startup, the power dress of adjustable thrust
Put.
Brief description of the drawings
Fig. 1 is a kind of sectional view of multiple-pulse adjustable thrust Solid propeller of the present invention.
Fig. 2 is a kind of powder charge end view drawing of multiple-pulse adjustable thrust Solid propeller of the present invention.
Embodiment
The present invention is described further for embodiment below in conjunction with the accompanying drawings.
In Fig. 1,2, a kind of multiple-pulse adjustable thrust Solid propeller disclosed by the invention, including 6 automatically controlled solid propellant propulsions
Agent unit 1a, 1b, 1c, 1d, 1e, 1f, external electrode（Also referred to as electrode base）2, interior electrode 3a, 3b, 3c, 3d, 3e, 3f, insulating barrier
4th, heat insulation layer 5, combustion chamber 6, jet pipe 7, rear baffle ring 8, preceding baffle ring 9.Combustion chamber 6 of the present invention is a cylindrical shape, the one end of combustion chamber 6
Tube port position is equipped with jet pipe 7, and the other end of combustion chamber 6 is provided with wire guide.The inner chamber of combustion chamber 6 is provided with external electrode 2, and external electrode 2 is circle
Cylindricality, 6 circular hole spaces is provided with external electrode 2, circular hole space is axially set in external electrode 2, and 6 circular hole space uniforms are set
It is placed on 2 same circumference of external electrode.Adiabatic insulating barrier one is stepped cylinder, and the left end of external electrode 2 is radially provided with exhausted with thermal insulation
Edge layer one coordinates the step locating slot of assembling, and adiabatic insulating barrier one is loaded on step locating slot along the radial direction of external electrode 2, absolutely
Thermal insulation layer one is provided with 6 through holes corresponding with circular hole space, and through hole positions with the complete interior electrode of circular hole space composition
Hole, interior electrode 3 are plugged at interior electrode positioning hole, automatically controlled solid propellant unit 1 be arranged at interior electrode 3 and circular hole space it
Between, adiabatic insulating barrier two is provided between the outer wall of external electrode 2 and the inwall of combustion chamber 6.Adiabatic insulating barrier two is axially set along external electrode 2
Put.The premenstrual baffle ring 9 in the both ends of external electrode 2, rear baffle ring 8 offset with combustion chamber 6.Insulating barrier 4 and heat insulation layer 5 form adiabatic insulating barrier.
In the present invention, adiabatic insulating barrier one and adiabatic insulating barrier two are referred to as adiabatic insulating barrier.
The automatically controlled solid propellant of the present invention has good electric conductivity, and loading certain voltage propellant can light a fire, change
Time variant voltage is sized to adjust propellant combustion speed, cuts off the electricity supply, propellant can stop working immediately.Automatically controlled solid propellant by
6 independent propellant unit 1a, 1b, 1c, 1d, 1e, 1f compositions, and keep contacting with interior electrode 3 and the moment of external electrode 2.Outside
Electrode 2 is evenly arranged 6 circular hole spaces on the basis of a bulk metal cylinder, is pushed away for placing automatically controlled solid respectively
Enter agent unit 1a, 1b, 1c, 1d, 1e, 1f.Interior electrode 3 is made up of more metal cylinders, 3a, 3b, 3c, 3d, 3e, 3f, respectively
In embedded automatically controlled solid propellant unit 1a, 1b, 1c, 1d, 1e, 1f, each interior electrode 3 is connected one control of composition with external electrode 2
Circuit processed, by controlling the break-make of each circuit, and then the igniting of each automatically controlled solid propellant unit is controlled, burns and stops working.
Insulating barrier 4 is used to completely cut off external electrode 2 and combustion chamber 6, prevents short circuit, electric leakage.Heat insulation layer 5 is used to completely cut off external electrode 2 and combustion chamber
6, prevent that combustion chamber overheats when propeller from working.Combustion chamber 6 be used for place automatically controlled solid propellant 1, external electrode 2, interior electrode 3,
Insulating barrier 4, heat insulation layer 5, rear baffle ring 8 and preceding baffle ring 9, and the propellant to be formed when propeller works is connected with the converging portion of jet pipe 7
The combustion chamber of burning.The expansion that jet pipe 7 is used for burning gases accelerates, and then produces thrust.Jet pipe 7 passes through screw thread and combustion chamber 6
Outer wall is fixedly connected.Baffle ring 8 is used for fixed electrode pedestal afterwards, prevents external electrode 2 from being moved to combustor tail.Preceding baffle ring 9 is used for
Fixed electrode pedestal, prevent external electrode 2 from being moved to spout portion displacement.
A kind of course of work of multiple-pulse adjustable thrust Solid propeller of the present invention is：
Automatically controlled solid propellant is made up of automatically controlled solid propellant unit 1a, 1b, 1c, 1d, 1e, 1f, and described external electrode 2 is one
On the basis of individual bulk metal cylinder, be evenly arranged multiple circular hole spaces, for place automatically controlled solid propellant unit 1a,
1b、1c、1d、1e、1f.Described interior electrode 3a, 3b, 3c, 3d, 3e, 3f is made up of more metal cylinders, is respectively embedded into electricity
Control in solid propellant unit 1a, 1b, 1c, 1d, 1e, 1f.Electrode is connected 1 control circuit of composition with external electrode in each, leads to
The break-make for controlling each circuit is crossed, and then controls the igniting of each automatically controlled solid propellant unit, burn and stop working.Interior electrode 3a
With 2 groups of the composition control circuit 1 of external electrode 2, the interior composition control circuit 2 of electrode 3b and external electrode 2, interior electrode 3c and shared external electrode
Into control circuit 3, the interior composition control circuit 4 of electrode 3d and external electrode 2, the interior composition control circuit 5 of electrode 3e and external electrode 2 is interior
Electrode 3f and the composition control circuit 6 of external electrode 2.Circuit 1 is connected on demand so that the corresponding automatically controlled solid that circuit 1 controls pushes away
Enter agent unit 1a ignition, combustion gas accelerates to produce thrust through nozzle expansion；It can be changed in combustion process by changing voltage
The burn rate of propellant, and then change thrust, i.e. circuit 1 controls automatically controlled solid propellant unit 1a, produces a set of pulses, adjustable pushes away
Power.Each circuit 2,3,4,5,6 is in turn switched on by thrust requirements, controls automatically controlled solid propellant unit 1b, 1c, 1d, 1e, 1f respectively
Igniting and burning, so as to produce 6 group pulse thrusts, thrust is adjustable in each pulse.
Above example is only the specific embodiment of the present invention, is not intended to limit the protection model of the present invention
Enclose.Within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc., should be included in the present invention
Protection domain within.
Claims (8)
- A kind of 1. multiple-pulse adjustable thrust Solid propeller, it is characterised in that：Including automatically controlled solid propellant unit（1）, dispatch from foreign news agency Pole（2）, interior electrode（3）, insulating barrier（4）, heat insulation layer（5）, combustion chamber（6）, jet pipe（7）；The combustion chamber（6）Inside it is provided with outer Electrode（2）；The external electrode（2）It is on the basis of a bulk metal cylinder, is evenly arranged multiple circular hole spaces, for respectively Place the automatically controlled solid propellant unit of multiple circular tube shapeds（1）；The interior electrode（3）It is made up of more metal cylinders, is respectively embedded into corresponding multiple automatically controlled solid propellants of circular tube shaped In unit, each automatically controlled solid propellant unit contacts with external electrode and corresponding interior electrode seal respectively.
- 2. multiple-pulse adjustable thrust Solid propeller according to claim 1, it is characterised in that：The combustion chamber（6）For One cylindrical shape, combustion chamber（6）The tube port position of one end is equipped with jet pipe（7）, combustion chamber（6）The other end is provided with wire guide.
- 3. multiple-pulse adjustable thrust Solid propeller according to claim 1, it is characterised in that：The heat insulation layer（5）, absolutely Edge layer（4）Adiabatic insulating barrier two is formed, adiabatic insulating barrier two is arranged at external electrode（2）Outer wall and combustion chamber（6）Between inwall, institute State heat insulation layer（5）Positioned at insulating barrier（4）Inner side.
- 4. multiple-pulse adjustable thrust Solid propeller according to claim 1, it is characterised in that：The heat insulation layer（5）, absolutely Edge layer（4）Adiabatic insulating barrier one is formed, adiabatic insulating barrier one is arranged at external electrode（2）One end.
- 5. multiple-pulse adjustable thrust Solid propeller according to claim 4, it is characterised in that：The adiabatic insulating barrier one It is provided with multiple through holes corresponding with circular hole space, through hole and the complete interior electrode positioning hole of circular hole space composition, interior electrode （3）It is plugged at interior electrode positioning hole.
- 6. multiple-pulse adjustable thrust Solid propeller according to claim 1, it is characterised in that：The external electrode（2）Two End is through baffle ring and combustion chamber（6）Offset.
- 7. multiple-pulse adjustable thrust Solid propeller according to claim 1, it is characterised in that：Electrode in each（3）All Lead cylinder, external electrode are set（2）Centrally disposed stem, using outside aviation plug each interior electrode（3）With external electrode （2）A control circuit is connected into external power source, interior electrode sum is identical with control circuit sum, and each circuit control is corresponding Interior electrode and external electrode between connecting and disconnecting of the circuit and voltage swing, and then control corresponding to automatically controlled solid propellant unit combustion Burning state.
- 8. multiple-pulse adjustable thrust Solid propeller according to claim 7, it is characterised in that：The course of work is：On demand Ask and connect a certain control circuit, in external electrode（2）With the interior electrode of control circuit control（3）Between load certain voltage, The automatically controlled solid propellant unit ignition contacted with the interior electrode, combustion gas accelerate to produce thrust through nozzle expansion；It is burned The burn rate of propellant can be adjusted in journey by changing voltage swing, and then changes thrust size；In turn switched on by thrust requirements Other control circuits, other automatically controlled solid propellant unit burnings are controlled respectively, so as to produce multigroup impulse force, each pulse Interior thrust is adjustable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610961515.7A CN107620652B (en) | 2016-10-28 | 2016-10-28 | Multi-pulse thrust-adjustable solid propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610961515.7A CN107620652B (en) | 2016-10-28 | 2016-10-28 | Multi-pulse thrust-adjustable solid propeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107620652A true CN107620652A (en) | 2018-01-23 |
| CN107620652B CN107620652B (en) | 2020-04-14 |
Family
ID=61087641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610961515.7A Active CN107620652B (en) | 2016-10-28 | 2016-10-28 | Multi-pulse thrust-adjustable solid propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107620652B (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488005A (en) * | 2018-02-13 | 2018-09-04 | 重庆大学 | A kind of multiple-pulse solid propellant rocket of thrust controllable |
| CN109237517A (en) * | 2018-08-12 | 2019-01-18 | 梁智斌 | Annular jet propeller |
| CN110259602A (en) * | 2019-06-21 | 2019-09-20 | 北京理工大学 | One kind can loading type multiple-pulse solid propellant rocket |
| CN110566365A (en) * | 2019-09-29 | 2019-12-13 | 中国人民解放军国防科技大学 | Mode-switchable solid combined engine and missile |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
| CN110779398A (en) * | 2019-10-30 | 2020-02-11 | 湖南宏大日晟航天动力技术有限公司 | Firework launching device and method |
| CN111169659A (en) * | 2020-01-16 | 2020-05-19 | 南京理工大学 | Intelligent controllable supercharging device for cold air propulsion |
| CN111365145A (en) * | 2020-04-02 | 2020-07-03 | 中国人民解放军国防科技大学 | Reusable igniter for rocket engine |
| CN112196692A (en) * | 2020-10-14 | 2021-01-08 | 中国人民解放军国防科技大学 | Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet |
| CN113091089A (en) * | 2021-04-14 | 2021-07-09 | 中国航空发动机研究院 | Aero-engine for controlling combustion in blending region by electric field |
| CN114278461A (en) * | 2021-11-15 | 2022-04-05 | 惠州学院 | Disconnect-type T type impulse thrust unit suitable for vertical launching aircraft |
| CN114658564A (en) * | 2022-04-21 | 2022-06-24 | 哈尔滨工业大学 | Wide-range thrust-adjusting electric control solid thruster |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050217238A1 (en) * | 2003-10-16 | 2005-10-06 | Land H B Iii | Pulsed plasma thruster and method of making |
| WO2008060255A2 (en) * | 2002-01-16 | 2008-05-22 | W.E. Research, Llc | Electrically controlled extinguishable solid propellant motors |
| CN201162635Y (en) * | 2008-03-27 | 2008-12-10 | 复旦大学 | Dual-electrode solid pulsed plasma thruster |
| WO2009140635A1 (en) * | 2008-05-16 | 2009-11-19 | Digital Solid State Propulsion Llc | Electrode ignition and control of electrically ignitable materials |
| CN201902267U (en) * | 2010-12-23 | 2011-07-20 | 西北工业大学 | Detonation tube structure of multi-tube pulse detonation engine |
| CN102869181A (en) * | 2012-09-05 | 2013-01-09 | 北京交通大学 | Electrode structure and electrode fixing structure for plasma thruster |
| CN104696180A (en) * | 2014-12-29 | 2015-06-10 | 中国空间技术研究院 | Magnetic field regulation type large-area microcavity discharge plasma micro-thruster for liquid working substances |
-
2016
- 2016-10-28 CN CN201610961515.7A patent/CN107620652B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008060255A2 (en) * | 2002-01-16 | 2008-05-22 | W.E. Research, Llc | Electrically controlled extinguishable solid propellant motors |
| US20050217238A1 (en) * | 2003-10-16 | 2005-10-06 | Land H B Iii | Pulsed plasma thruster and method of making |
| CN201162635Y (en) * | 2008-03-27 | 2008-12-10 | 复旦大学 | Dual-electrode solid pulsed plasma thruster |
| WO2009140635A1 (en) * | 2008-05-16 | 2009-11-19 | Digital Solid State Propulsion Llc | Electrode ignition and control of electrically ignitable materials |
| CN201902267U (en) * | 2010-12-23 | 2011-07-20 | 西北工业大学 | Detonation tube structure of multi-tube pulse detonation engine |
| CN102869181A (en) * | 2012-09-05 | 2013-01-09 | 北京交通大学 | Electrode structure and electrode fixing structure for plasma thruster |
| CN104696180A (en) * | 2014-12-29 | 2015-06-10 | 中国空间技术研究院 | Magnetic field regulation type large-area microcavity discharge plasma micro-thruster for liquid working substances |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488005A (en) * | 2018-02-13 | 2018-09-04 | 重庆大学 | A kind of multiple-pulse solid propellant rocket of thrust controllable |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
| CN110714855B (en) * | 2018-07-12 | 2022-04-08 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
| CN109237517B (en) * | 2018-08-12 | 2021-03-26 | 梁智斌 | Annular nozzle propeller |
| CN109237517A (en) * | 2018-08-12 | 2019-01-18 | 梁智斌 | Annular jet propeller |
| CN110259602A (en) * | 2019-06-21 | 2019-09-20 | 北京理工大学 | One kind can loading type multiple-pulse solid propellant rocket |
| CN110566365A (en) * | 2019-09-29 | 2019-12-13 | 中国人民解放军国防科技大学 | Mode-switchable solid combined engine and missile |
| CN110566365B (en) * | 2019-09-29 | 2021-01-08 | 中国人民解放军国防科技大学 | Mode-switchable solid combined engine and missile |
| CN110779398A (en) * | 2019-10-30 | 2020-02-11 | 湖南宏大日晟航天动力技术有限公司 | Firework launching device and method |
| CN111169659A (en) * | 2020-01-16 | 2020-05-19 | 南京理工大学 | Intelligent controllable supercharging device for cold air propulsion |
| CN111365145B (en) * | 2020-04-02 | 2020-12-18 | 中国人民解放军国防科技大学 | Reusable igniter for rocket engine |
| CN111365145A (en) * | 2020-04-02 | 2020-07-03 | 中国人民解放军国防科技大学 | Reusable igniter for rocket engine |
| CN112196692A (en) * | 2020-10-14 | 2021-01-08 | 中国人民解放军国防科技大学 | Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet |
| CN113091089A (en) * | 2021-04-14 | 2021-07-09 | 中国航空发动机研究院 | Aero-engine for controlling combustion in blending region by electric field |
| CN114278461A (en) * | 2021-11-15 | 2022-04-05 | 惠州学院 | Disconnect-type T type impulse thrust unit suitable for vertical launching aircraft |
| CN114278461B (en) * | 2021-11-15 | 2024-04-12 | 惠州学院 | Disconnect-type T type pulse thruster group suitable for vertical launch aircraft |
| CN114658564A (en) * | 2022-04-21 | 2022-06-24 | 哈尔滨工业大学 | Wide-range thrust-adjusting electric control solid thruster |
| CN114658564B (en) * | 2022-04-21 | 2022-09-23 | 哈尔滨工业大学 | Wide-range thrust-adjusting electric control solid thruster |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107620652B (en) | 2020-04-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107620652A (en) | A kind of multiple-pulse adjustable thrust Solid propeller | |
| CN107642435A (en) | A kind of adjustable thrust, it can repeatedly start automatically controlled solid engine | |
| CN106134417B (en) | Low-thrust rocket | |
| CN107842427B (en) | A kind of preheating type plasma igniter and ignition method | |
| CN109595100B (en) | Electric ignition green unit liquid rocket engine structure | |
| CN107893711B (en) | A kind of gas hydrogen-oxygen torch type electric ignition device | |
| CN108488005A (en) | A kind of multiple-pulse solid propellant rocket of thrust controllable | |
| CN109154441A (en) | Toroidal combustion chamber with continuous detonation wave | |
| CN106050476B (en) | A kind of liquid-propellant rocket engine igniter and its ignition method | |
| JP4155706B2 (en) | Gas supply system for detonation spray gun | |
| CN109798202A (en) | A kind of liquid-propellant rocket engine ejector filler integrating electric igniter | |
| CN109653903A (en) | A kind of repeatable igniter for solid-liquid rocket | |
| CN112196692B (en) | Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet | |
| CN112211749A (en) | Small solid rocket engine | |
| CN108151062B (en) | A kind of engine supersonic speed combustion chamber based on embedded central plasma torch | |
| CN110195665A (en) | A kind of air storing type solid propellant power device of reloading | |
| CN111577483A (en) | Multi-pulse solid rocket engine | |
| CN104791135A (en) | Hybrid rocket engine igniter | |
| CN110145412B (en) | Gate type solid rocket engine | |
| CN103216317A (en) | Supersonic combustion method actuated by combination plasma | |
| CN101852146A (en) | Novel small hydrogen-oxygen engine head | |
| CN102877985A (en) | Boron-based solid fuel propeller igniting through plasma generator | |
| CN103133183A (en) | Safe processing device of low-temperature hydrogen in rocket engine thrust chamber | |
| CN102074897B (en) | Step type spark plug | |
| JPS57179338A (en) | Igniting apparatus for gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |