CN107620652B - Multi-pulse thrust-adjustable solid propeller - Google Patents
Multi-pulse thrust-adjustable solid propeller Download PDFInfo
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- CN107620652B CN107620652B CN201610961515.7A CN201610961515A CN107620652B CN 107620652 B CN107620652 B CN 107620652B CN 201610961515 A CN201610961515 A CN 201610961515A CN 107620652 B CN107620652 B CN 107620652B
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Abstract
A multi-pulse thrust adjustable solid propeller comprises an electric control solid propellant unit, an outer electrode, an inner electrode, an insulating layer, a heat insulating layer, a combustion chamber and a spray pipe; an outer electrode is arranged in the combustion chamber; the outer electrode is formed by uniformly arranging a plurality of circular hole spaces on the basis of an integral metal cylinder and is used for respectively placing a plurality of tubular electric control solid propellant units; the inner electrode is composed of a plurality of metal cylinders and is respectively embedded into a plurality of corresponding circular tubular electric control solid propellant units, and each electric control solid propellant unit is respectively in close contact with the outer electrode and the corresponding inner electrode. Each inner electrode and each outer electrode of the electric control solid propellant unit are connected to form 1 control circuit, and ignition, combustion and flameout of each electric control solid propellant unit are controlled by controlling the on-off of each circuit. And controlling the voltage of the two ends of the inner electrode and the outer electrode so as to control the combustion rate of each propellant unit, so that the thrust of the propeller is adjustable in each working pulse.
Description
Technical Field
The invention relates to a propeller adopting an electric control solid propellant, in particular to a multi-pulse thrust-controllable solid propeller, belonging to the field of solid pulse engines.
Background
The solid rocket engine is difficult to realize multiple starting and the thrust is difficult to control. At present, the thrust-adjustable solid engine mainly comprises a nozzle throat area-adjustable solid engine, a sectional charge prefabricated multistage thrust engine, a solid pulse engine and a flameout solid engine, but the engines cannot realize continuous multi-time starting and active thrust random control.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides a multi-pulse thrust-adjustable solid propeller which is convenient to use and can obtain multi-pulse thrust.
The purpose of the invention is realized by the following technical scheme: the device comprises an electric control solid propellant unit, an outer electrode, an inner electrode, an insulating layer, a heat insulating layer, a combustion chamber and a spray pipe; an outer electrode is arranged in the combustion chamber; the outer electrode is formed by uniformly arranging a plurality of circular hole spaces on the basis of an integral metal cylinder and is used for respectively placing a plurality of tubular electric control solid propellant units; the inner electrode is composed of a plurality of metal cylinders and is respectively embedded into a plurality of corresponding circular tubular electric control solid propellant units, and each electric control solid propellant unit is respectively in close contact with the outer electrode and the corresponding inner electrode.
The combustion chamber is cylindrical, a nozzle is arranged at the nozzle at one end of the combustion chamber, a wire hole is formed in the other end of the combustion chamber, and a wire connected with an external power supply passes through the wire hole and is connected with the outer electrode and the inner electrode through an aviation plug.
The heat insulation layer II is arranged between the outer wall of the outer electrode and the inner wall of the combustion chamber, and is located on the inner side of the insulation layer.
The heat insulation layer and the insulating layer form a first heat insulation layer, and the first heat insulation layer is arranged at one end of the outer electrode.
And the first heat insulation layer is provided with a plurality of through holes corresponding to the circular hole spaces, the through holes and the circular hole spaces form a complete inner electrode positioning hole, and the inner electrode is inserted in the inner electrode positioning hole.
And two ends of the outer electrode are abutted against the combustion chamber through the baffle ring.
Each inner electrode is provided with a lead column, the center of the outer electrode is provided with the lead column, each inner electrode, the outer electrode and an external power supply are connected into a control circuit by adopting an external aviation plug, the total number of the inner electrodes is the same as that of the control circuit, and each circuit controls the on-off and voltage of the circuit between the corresponding inner electrode and the outer electrode so as to control the combustion state of the corresponding electronic control solid propellant unit.
The working process of the invention is as follows: a certain control circuit is connected as required, a certain voltage is loaded between an outer electrode and an inner electrode controlled by the control circuit, an electric control solid propellant unit in contact with the inner electrode ignites and burns, and fuel gas expands and accelerates through a spray pipe to generate thrust; the burning speed of the propellant can be adjusted by changing the voltage in the burning process, so that the thrust can be changed; and sequentially connecting other control circuits according to the thrust requirement, and respectively controlling other electric control solid propellant units to burn so as to generate a plurality of groups of pulse thrust, wherein the thrust in each pulse is adjustable.
The electric control solid propellant unit is a combustion controllable solid propellant capable of conducting electricity, and can realize ignition by loading a certain voltage under the electrified condition; during the combustion process, the burning speed of the propellant is adjusted by controlling the voltage, the propellant is extinguished when the power supply is cut off, and multiple times of ignition and flameout can be realized. The invention has the beneficial effects that:
the multi-pulse thrust-adjustable solid thruster can control the thrust of the thruster through voltage, and the whole working process of the thruster can be controlled through the voltage.
According to the multi-pulse thrust adjustable solid propeller, the power-on state of each propellant unit is controlled, so that different propellant units can be combusted and operated, and multi-pulse thrust can be obtained.
In the combustion process, the combustion rate is adjusted by changing the voltage loaded on each propellant unit, so that the thrust of the propeller is adjustable in each working pulse.
The invention can be used for small satellites and small spacecrafts and requires that the propeller has a power device with multiple starting and adjustable thrust.
Drawings
Fig. 1 is a cross-sectional view of a multi-pulse thrust modulated solid propellant of the present invention.
Fig. 2 is a charge end view of a multi-pulse thrust adjustable solid thruster of the invention.
Detailed Description
The invention is further described with reference to the following embodiments.
In fig. 1 and 2, the multi-pulse thrust-adjustable solid thruster disclosed by the invention comprises 6 electrically-controlled solid propellant units 1a, 1b, 1c, 1d, 1e and 1f, an outer electrode (also called an electrode base) 2, inner electrodes 3a, 3b, 3c, 3d, 3e and 3f, an insulating layer 4, a heat insulating layer 5, a combustion chamber 6, a nozzle 7, a rear baffle ring 8 and a front baffle ring 9. The combustion chamber 6 of the invention is a cylinder, a nozzle 7 is arranged at the nozzle at one end of the combustion chamber 6, and a wire guide hole is arranged at the other end of the combustion chamber 6. An inner cavity of the combustion chamber 6 is provided with an outer electrode 2, the outer electrode 2 is cylindrical, 6 circular hole spaces are arranged in the outer electrode 2, the circular hole spaces are axially arranged in the outer electrode 2, and the 6 circular hole spaces are uniformly arranged on the same circumference of the outer electrode 2. The first heat insulation insulating layer is a stepped cylinder, the left end of the outer electrode 2 is radially provided with a stepped positioning groove matched and assembled with the first heat insulation insulating layer, the first heat insulation insulating layer is arranged in the stepped positioning groove along the radial direction of the outer electrode 2, the first heat insulation insulating layer is provided with 6 through holes corresponding to the circular hole spaces, the through holes and the circular hole spaces form complete inner electrode positioning holes, the inner electrode 3 is inserted in the inner electrode positioning holes, the electric control solid propellant unit 1 is arranged between the inner electrode 3 and the circular hole spaces, and the second heat insulation insulating layer is arranged between the outer wall of the outer electrode 2 and the inner wall of the. The second heat insulation layer is arranged along the axial direction of the outer electrode 2. Two ends of the outer electrode 2 are abutted against the combustion chamber 6 through a front retaining ring 9 and a rear retaining ring 8. The insulating layer 4 and the heat insulating layer 5 constitute a heat insulating layer. In the present invention, both the first heat insulating layer and the second heat insulating layer are simply referred to as heat insulating layers.
The electric control solid propellant has good conductivity, can be ignited by loading a certain voltage, can adjust the burning rate of the propellant by changing the voltage, cuts off the power supply, and can be immediately flamed out. The electrically controlled solid propellant consists of 6 individual propellant units 1a, 1b, 1c, 1d, 1e, 1f and is constantly in contact with the inner electrode 3 and the outer electrode 2. The outer electrode 2 is uniformly provided with 6 circular hole spaces on the basis of an integral metal cylinder, and is used for placing the electric control solid propellant units 1a, 1b, 1c, 1d, 1e and 1f respectively. The inner electrode 3 is composed of a plurality of metal cylinders, 3a, 3b, 3c, 3d, 3e and 3f are respectively embedded into the electric control solid propellant units 1a, 1b, 1c, 1d, 1e and 1f, each inner electrode 3 is connected with the outer electrode 2 to form a control circuit, and ignition, combustion and flameout of each electric control solid propellant unit are controlled by controlling on-off of each circuit. The insulating layer 4 is used for isolating the outer electrode 2 from the combustion chamber 6 and preventing short circuit and electric leakage. The heat insulating layer 5 is used for isolating the outer electrode 2 from the combustion chamber 6, and preventing the combustion chamber from overheating when the propeller works. The combustion chamber 6 is used for placing the electric control solid propellant 1, the outer electrode 2, the inner electrode 3, the insulating layer 4, the heat insulating layer 5, the rear baffle ring 8 and the front baffle ring 9, and is connected with the convergent section of the spray pipe 7 to form a combustion chamber for propellant combustion when the propeller works. The nozzle 7 is used for accelerating the expansion of the combustion gas, thereby generating thrust. The spray pipe 7 is fixedly connected with the outer wall of the combustion chamber 6 through threads. The backstop ring 8 is used for fixing the electrode base and preventing the outer electrode 2 from moving to the tail part of the combustion chamber. The front baffle ring 9 is used for fixing the electrode base and preventing the outer electrode 2 from moving to the spray pipe part.
The working process of the multi-pulse thrust adjustable solid propeller comprises the following steps:
the electric control solid propellant consists of electric control solid propellant units 1a, 1b, 1c, 1d, 1e and 1f, and the outer electrode 2 is uniformly provided with a plurality of circular hole spaces for placing the electric control solid propellant units 1a, 1b, 1c, 1d, 1e and 1f on the basis of an integral metal cylinder. The inner electrodes 3a, 3b, 3c, 3d, 3e and 3f are composed of a plurality of metal cylinders and are respectively embedded into the electric control solid propellant units 1a, 1b, 1c, 1d, 1e and 1 f. Each inner electrode and the outer electrode are connected to form 1 control circuit, and ignition, combustion and flameout of each electric control solid propellant unit are controlled by controlling on-off of each circuit. The inner electrode 3a and the outer electrode 2 form a control circuit 1, the inner electrode 3b and the outer electrode 2 form a control circuit 2, the inner electrode 3c and the common outer electrode 2 form a control circuit 3, the inner electrode 3d and the outer electrode 2 form a control circuit 4, the inner electrode 3e and the outer electrode 2 form a control circuit 5, and the inner electrode 3f and the outer electrode 2 form a control circuit 6. The circuit 1 is connected as required, so that the corresponding electric control solid propellant unit 1a controlled by the circuit 1 is ignited and combusted, and the gas expands and accelerates through the spray pipe to generate thrust; in the combustion process, the burning speed of the propellant can be changed by changing the voltage, and then the thrust is changed, namely the circuit 1 controls the electric control solid propellant unit 1a to generate a group of pulse and adjustable thrust. And sequentially connecting the circuits 2, 3, 4, 5 and 6 according to the thrust requirement, and respectively controlling the electric control solid propellant units 1b, 1c, 1d, 1e and 1f to ignite and burn so as to generate 6 groups of pulse thrust, wherein the thrust in each pulse is adjustable.
The above embodiment is only one specific embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides an adjustable solid propeller of many pulse thrust which characterized in that: comprises an electric control solid propellant unit (1), an outer electrode (2), an inner electrode (3), an insulating layer (4), a heat insulating layer (5), a combustion chamber (6) and a spray pipe (7); an outer electrode (2) is arranged in the combustion chamber (6);
the outer electrode (2) is uniformly provided with a plurality of circular hole spaces on the basis of an integral metal cylinder and is used for respectively placing a plurality of tubular electric control solid propellant units (1);
the inner electrode (3) is composed of a plurality of metal cylinders and is respectively embedded into a plurality of corresponding circular tubular electric control solid propellant units, and each electric control solid propellant unit is respectively in close contact with the outer electrode and the corresponding inner electrode;
each inner electrode (3) is provided with a lead column, the center of each outer electrode (2) is provided with the lead column, each inner electrode (3), each outer electrode (2) and an external power supply are connected into a control circuit by adopting an external aviation plug, the total number of the inner electrodes is the same as that of the control circuits, and each circuit controls the on-off and the voltage of the circuit between the corresponding inner electrode and the corresponding outer electrode so as to control the combustion state of the corresponding electronic control solid propellant unit;
the electric control solid propellant unit is loaded with a certain voltage under the condition of electrification, so that ignition can be realized; during the combustion process, the burning speed of the propellant is adjusted by controlling the voltage, the propellant is extinguished when the power supply is cut off, and multiple times of ignition and flameout can be realized.
2. The multipulse thrust tunable solid propulsor of claim 1, wherein: the combustion chamber (6) is cylindrical, a nozzle (7) is arranged at the opening at one end of the combustion chamber (6), and a wire guide hole is formed in the other end of the combustion chamber (6).
3. The multipulse thrust tunable solid propulsor of claim 1, wherein: and the heat insulation layer (5) and the insulation layer (4) form a second heat insulation layer, the second heat insulation layer is arranged between the outer wall of the outer electrode (2) and the inner wall of the combustion chamber (6), and the heat insulation layer (5) is positioned on the inner side of the insulation layer (4).
4. The multipulse thrust tunable solid propulsor of claim 1, wherein: the heat insulation layer (5) and the insulation layer (4) form a first heat insulation layer, and the first heat insulation layer is arranged at one end of the outer electrode (2).
5. The multipulse thrust tunable solid propulsor of claim 4, wherein: the first heat insulation layer is provided with a plurality of through holes corresponding to the circular hole spaces, the through holes and the circular hole spaces form a complete inner electrode positioning hole, and the inner electrode (3) is inserted in the inner electrode positioning hole.
6. The multipulse thrust tunable solid propulsor of claim 1, wherein: and two ends of the outer electrode (2) are abutted against the combustion chamber (6) through the baffle ring.
7. The multipulse thrust tunable solid propulsor of claim 1, wherein: the working process is as follows: a certain control circuit is connected as required, a certain voltage is loaded between an outer electrode (2) and an inner electrode (3) controlled by the control circuit, an electric control solid propellant unit in contact with the inner electrode ignites and burns, and fuel gas expands and accelerates through a spray pipe to generate thrust; the burning speed of the propellant can be adjusted by changing the voltage in the burning process, so that the thrust can be changed; and sequentially connecting other control circuits according to the thrust requirement, and respectively controlling other electric control solid propellant units to burn so as to generate a plurality of groups of pulse thrust, wherein the thrust in each pulse is adjustable.
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| CN201610961515.7A CN107620652B (en) | 2016-10-28 | 2016-10-28 | Multi-pulse thrust-adjustable solid propeller |
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| CN201610961515.7A CN107620652B (en) | 2016-10-28 | 2016-10-28 | Multi-pulse thrust-adjustable solid propeller |
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| CN107620652B true CN107620652B (en) | 2020-04-14 |
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| CN108488005B (en) * | 2018-02-13 | 2020-02-07 | 重庆大学 | Thrust-controllable multi-pulse solid rocket engine |
| 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 |
| CN110259602B (en) * | 2019-06-21 | 2020-06-05 | 北京理工大学 | Multi-pulse solid rocket engine capable of being filled |
| 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 |
| CN112196692B (en) * | 2020-10-14 | 2021-11-12 | 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 |
| CN114278461B (en) * | 2021-11-15 | 2024-04-12 | 惠州学院 | Disconnect-type T type pulse thruster group suitable for vertical launch aircraft |
| CN114658564B (en) * | 2022-04-21 | 2022-09-23 | 哈尔滨工业大学 | Wide-range thrust-adjusting electric control solid thruster |
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| WO2009140635A1 (en) * | 2008-05-16 | 2009-11-19 | Digital Solid State Propulsion Llc | Electrode ignition and control of electrically ignitable materials |
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| WO2008060255A2 (en) * | 2002-01-16 | 2008-05-22 | W.E. Research, Llc | Electrically controlled extinguishable solid propellant motors |
| US7302792B2 (en) * | 2003-10-16 | 2007-12-04 | The Johns Hopkins University | 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 |
| CN201902267U (en) * | 2010-12-23 | 2011-07-20 | 西北工业大学 | Detonation tube structure of multi-tube pulse detonation engine |
| CN102869181B (en) * | 2012-09-05 | 2016-04-13 | 北京交通大学 | For electrode structure and the electrode fixing structure of plasma propeller |
| CN104696180B (en) * | 2014-12-29 | 2017-07-28 | 中国空间技术研究院 | Magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster |
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| WO2009140635A1 (en) * | 2008-05-16 | 2009-11-19 | Digital Solid State Propulsion Llc | Electrode ignition and control of electrically ignitable materials |
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