CN112377328B - Solid cold gas generator structure for space propulsion system - Google Patents
Solid cold gas generator structure for space propulsion system Download PDFInfo
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- CN112377328B CN112377328B CN202011127712.1A CN202011127712A CN112377328B CN 112377328 B CN112377328 B CN 112377328B CN 202011127712 A CN202011127712 A CN 202011127712A CN 112377328 B CN112377328 B CN 112377328B
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- 239000007787 solid Substances 0.000 title claims abstract description 33
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 38
- 239000002360 explosive Substances 0.000 claims abstract description 24
- 238000002485 combustion reaction Methods 0.000 claims description 16
- 229910001220 stainless steel Inorganic materials 0.000 claims description 9
- 239000010935 stainless steel Substances 0.000 claims description 5
- 230000004323 axial length Effects 0.000 claims description 3
- 238000005245 sintering Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 238000009472 formulation Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 239000011148 porous material Substances 0.000 claims 1
- 239000000843 powder Substances 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 76
- 238000000034 method Methods 0.000 description 6
- 238000003801 milling Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 239000002737 fuel gas Substances 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 4
- 239000003814 drug Substances 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052783 alkali metal Inorganic materials 0.000 description 2
- 229910001515 alkali metal fluoride Inorganic materials 0.000 description 2
- -1 alkali metal sodium azide Chemical class 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 229910001873 dinitrogen Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- PXIPVTKHYLBLMZ-UHFFFAOYSA-N sodium azide Substances [Na+].[N-]=[N+]=[N-] PXIPVTKHYLBLMZ-UHFFFAOYSA-N 0.000 description 2
- 229910000314 transition metal oxide Inorganic materials 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000002585 base Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000008187 granular material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Air Bags (AREA)
Abstract
A solid cold gas generator structure for a space propulsion system, comprising: igniter, backing ring, filter screen, supporting ring subassembly, powder column part, casing, U type bottom. One end of the igniter extends out of the interior of the shell to the top and is connected with the backing ring through threads; the outer wall of the igniter is sleeved with a filter screen; the powder column component, the support ring component and the shell are sequentially sleeved from inside to outside, and the U-shaped bottom cover and the inner wall of the shell are welded and fixed; a plurality of circular exhaust holes are uniformly distributed on the top of the shell in the circumferential direction; the outer wall of the explosive column part is not contacted with the inner wall of the shell, and gas is guided; a plurality of notches are processed inwards along the radial direction on the outer wall of the U-shaped bottom cover. The ignition end of the structure of the invention mainly exhausts gas, has good gas circulation, and maintains the work of other low-burning-rate gas producing agents by utilizing the heat generated by burning the high-burning-rate powder.
Description
Technical Field
The invention relates to a solid cold gas generator structure for a space propulsion system, and belongs to the technical field of propulsion.
Background
In order to meet the requirements of quick response and reduction of the cost in the satellite development process, the satellite develops towards the modularization direction, the space propulsion system is required to be capable of being used in a plug-and-play mode, the assembly coupling period is reduced, and the filling period of a base is reduced.
CN 1103921956B solid cold air micro-propulsion system, Ming Jing university of Richardson, proposes a solid cold air generator structure, the generator gas outlet is at the bottom, the gas producing agent adopts granule to charge, the charge density is low, the gas production is low, the passive quality is high, the porous charge is influenced by the vibration of transportation and rocket launching process and is easy to wear and pulverize, the structure is not suitable for the requirement of the generator with large length-diameter ratio. Negative qualities include the thickness of the combustion chamber housing and the quality of the gas treatment layer (fine sand layer, activated carbon layer) in the nitrogen gas generant.
The small solid engine is limited by the volume of a space propulsion system, the diameter of the generator is limited to a certain extent, under the condition of low length constraint, a cold gas generator with a large length-diameter ratio needs to be designed in order to improve the charge quantity, the length-diameter ratio of the gas generator is generally lower than 3:1, for a solid cold gas generator with a large length-diameter ratio of more than 4:1, columnar charge is generally adopted and is similar to the charge of a solid rocket engine, but the process that hot gas flows to a nozzle along a charge column can continuously heat the charge column, the combustion temperature of a gas generating agent is uncontrollable, a large amount of high-temperature and high-pressure gas is generated in a combustion chamber, serious negative effects are caused on the charge chamber, the wall thickness of a shell of the small solid engine is generally between 5mm and 10mm, the negative mass ratio is large, and the requirements of the space propulsion system cannot be met.
As shown in fig. 6, the design that the ignition of the generator and the nozzle are in the same direction can eliminate the adverse effect of hot air flow on the gas generating agent, and the following problems are that when the gas generating agent is just ignited, the heat generated by the igniter and the booster can maintain the combustion of a certain gas generating agent, but with the continuous combustion of the gas generating agent, the tail part of the gas generating agent cannot receive the heat transferred by the fuel gas, and for the gas generating agent with large length-diameter ratio, the tail gas generating agent cannot obtain enough heat, cannot maintain the self-sustained combustion, and is easy to cause flameout.
Disclosure of Invention
The technical problem solved by the invention is as follows: overcomes the defects of the prior art and provides a novel solid cold gas generator structure for a space propulsion system. The exhaust port and the ignition face to the same end to form main exhaust of the ignition end, the gas producing agent adopts solid cylindrical charging, the filling density is increased, and the end face combustion of the charge is realized. Micropores are designed at the tail part of the generator in a flat milling mode to exhaust, part of hot gas is guided to form convection heating on a gas generating agent column, the tail part of the gas generating agent is ensured to be continuously combusted, and the problem of work flameout of a solid cold gas generator with a large length-diameter ratio is solved.
The technical scheme of the invention is as follows:
a solid cold gas generator structure for a space propulsion system, comprising: the igniter, the backing ring, the filter screen, the support ring component, the explosive column component, the shell and the U-shaped bottom cover;
one end of the igniter extends out of the shell from the inside to the top and is connected with the backing ring through threads, and the backing ring is positioned outside the shell;
the outer wall of the igniter is sleeved with a filter screen, and the filter screen is positioned inside the shell;
the explosive column component, the support ring component and the shell are sleeved in sequence from inside to outside, and the explosive column component is arranged below the igniter through the support ring component;
the U-shaped bottom cover is arranged below the grain part; the U-shaped bottom cover and the inner wall of the shell are welded and fixed;
a plurality of circular exhaust holes are uniformly distributed on the top of the shell in the circumferential direction;
the support ring assembly is used for preventing the outer wall of the medicine column component from contacting the inner wall of the shell, and a gap between the outer wall of the medicine column component and the inner wall of the shell is used for guiding gas;
a plurality of notches are processed on the outer wall of the U-shaped bottom cover along the radial direction, and the notches are used for enabling gas generated by combustion of the medicine column to flow out of the shell.
The length-diameter ratio of the grain part is more than 4: 1.
the filter screen is formed by sintering a plurality of layers of stainless steel wire meshes, and the axial length of the filter screen ranges from 1.5 mm to 2.5 mm.
The aperture of the stainless steel screen ranges from 20 mu m to 50 mu m.
The charge part is composed of 2 formulas, including: a high-burning-rate gas generating agent formula and a low-burning-rate gas generating agent formula; the mass ratio value range of the formula of the high-combustion-rate gas generating agent is 7-15%.
The density of the grain part is in the range of 2.1g/cm3～2.5g/cm3The temperature of the gas generated by igniting and burning the explosive column part is not higher than 350 ℃.
5 ~ 8 circular exhaust holes are evenly distributed in the circumference of casing top.
The shell is made of stainless steel, and the value range of the wall thickness of the shell is 1 mm-1.2 mm.
The radial dimension range of the notch on the outer wall of the U-shaped bottom cover is 0.1-0.4 mm;
the number range of the notches on the outer wall of the U-shaped bottom cover is 3-6.
The gap between the outer wall of the grain part and the inner wall of the shell ranges from 0.4mm to 0.8 mm.
Compared with the prior art, the invention has the advantages that:
1) the invention provides a solid cold gas generator with a main exhaust port at the head part and a milled flat exhaust hole at the tail part, wherein fuel gas can pass through a gas generating agent in a surrounding manner to form continuous convection heating of heat flow of the gas generating agent by the fuel gas, so that the gas generating agent can be completely combusted, and the problem of work flameout of the solid cold gas generator with a large length-diameter ratio is solved.
2) The invention provides an internal annular heat exchange channel structure of a generator, which is positioned between a gas generating agent and a shell, wherein fuel gas can be discharged from a tail auxiliary exhaust port through the channel, and the heating of the whole gas generating agent can be ensured by the fuel gas through the heat exchange channel.
3) The U-shaped end cover structure is connected with a shell of a generator through laser welding, and the U-shaped flanging structure can increase the connection strength, ensure the structural strength of the solid cold gas generator in the working process and prevent the end cover from falling off due to the internal pressure of the generator.
4) The invention provides a cylindrical charging mode, which improves the filling density of a gas generating agent, improves the gas generation rate of a solid cold gas generator in unit volume and is beneficial to reducing the volume of the whole generator.
5) The gas generating agent is positioned at the head of the generator through the main exhaust port, so that the gas generating agent can be stably combusted, and the generated gas can be discharged at a controllable speed.
6) According to the invention, the milling flat exhaust hole added at the tail part and the gas heat exchange channel in the generator can ensure that the whole generator works heavily, the gas generating agent (namely a charge column component) is continuously heated, and the unburned gas generating agent can obtain enough pre-combustion heat.
Drawings
FIG. 1 is a schematic view of a solid cold gas generator for a space propulsion system according to the present invention;
FIG. 2 is a schematic view of milling a bottom cover flat;
FIG. 3 is a schematic view of gas flow heat transfer;
FIG. 4 is a schematic structural view of a U-shaped bottom cover;
FIG. 5 is a typical P-t plot (23 deg.C) of the present invention after ignition in a 10L closed container;
fig. 6 is a prior art schematic.
Detailed Description
The invention relates to a solid cold gas generator structure for a space propulsion system, which is shown in figure 1 and comprises: igniter 1, backing ring 2, filter screen 3, support ring subassembly 4, powder column part 5, casing 6, U type bottom cap 7.
One end of the igniter 1 extends out of the interior of the shell 6 to the top and is connected with the backing ring 2 through threads, and the backing ring 2 is positioned outside the shell 6; the grommet 2 serves to fix the axial position of the igniter 1.
The outer wall of the igniter 1 is sleeved with a filter screen 3, and the filter screen 3 is positioned inside the shell 6;
the explosive column component 5, the support ring component 4 and the shell 6 are sleeved in sequence from inside to outside, and the explosive column component 5 is arranged below the igniter 1 through the support ring component 4;
the U-shaped bottom cover 7 is arranged below the grain part 5 and compresses the grain part 5 from bottom to top. The U-shaped bottom cover 7 is welded and fixed with the inner wall of the shell 6, and the U-shaped bottom cover 7 is used for fixing the axial position of the grain part 5, as shown in figure 4.
The gas vent of generator and the same end of ignition design orientation form the ignition end owner and exhaust, and 6 top circumference equipartitions of casing have 5 ~ 8 circular exhaust holes, and the quantity in preferred exhaust hole is 5. The diameter of the vent hole in this example is 2 mm. The material of the shell 6 is 0Cr18Ni9 stainless steel. The value range of the wall thickness of the shell 6 is 1 mm-1.2 mm.
A certain gap is left between the inner shell 6 of the generator and the explosive column part 5, so that the explosive column is prevented from expanding when being heated and extruding the shell 6 to deform. The support ring assembly 4 is used for keeping the outer wall of the grain part 5 and the inner wall of the shell 6 from contacting, a gap between the outer wall of the grain part 5 and the inner wall of the shell 6 is used for guiding hot gas, and the value range of the gap between the outer wall of the grain part 5 and the inner wall of the shell 6 is 0.4-0.8 mm.
Micropores are designed at the tail part of the generator in a flat milling mode to exhaust, part of hot gas is guided to form convection heating on the explosive column of the explosive column part 5, continuous combustion at the tail part of the explosive column part 5 is guaranteed, and the problem of work flameout of the solid cold gas generator with a large length-diameter ratio is solved. A plurality of notches are processed on the outer wall of the U-shaped bottom cover 7 along the radial direction, and the notches are used for enabling gas generated by combustion of the explosive column 5 to flow out of the shell 6 from the bottom of the shell 6. The numerical range of the notches on the outer wall of the U-shaped bottom cover 7 is 3-6. The preferred quantity of U type bottom 7 outer wall breach is 3. In the embodiment of the invention, the outer wall of the U-shaped bottom cover 7 is milled flat by 0.3mm along the radial direction to be used as a notch, the combustion time is controlled, the working time is 10-20 s, and the airflow impact is small.
The radial dimension range of the notch on the outer wall of the U-shaped bottom cover 7 is 0.1-0.4 mm. The embodiment of the invention is 0.3mm, as shown in FIG. 2.
The filter screen 3 is formed by sintering a plurality of layers of stainless steel wire meshes, so that the gas residue is filtered. The axial length of the filter screen 3 ranges from 1.5 mm to 2.5mm, in the embodiment of the invention, the number of the filter screen 3 layers is 5, and the thickness of the filter screen 3 is 1.8 mm. The aperture of the stainless steel screen ranges from 20 mu m to 50 mu m.
The charge part 5 is composed of 2 formulas, including: a high-burning-rate gas generating agent formula and a low-burning-rate gas generating agent formula; the mass ratio of the formula of the high-combustion-rate gas generating agent is 7-15%. The ignition end adopts a high-burning-rate gas generating agent formula, and the mass ratio is as follows: 35-60% of alkali metal sodium azide, 25-35% of transition metal oxide, 10-30% of alkali metal fluoride and 5-20% of other oxides. The rest part adopts a low-burning-rate gas generating agent formula, and the mass ratio is as follows: 55-85% of alkali metal sodium azide, 15-25% of transition metal oxide, 5-15% of alkali metal fluoride and 5-20% of other oxides. In the embodiment of the invention, a high-burning-rate gas generating agent formula is adopted at the ignition end of 5-10 mm, a low-burning-rate gas generating agent formula is adopted at the rest part, the heat generated by the high-burning-rate gas generating agent in unit time is high, and the heat generated after burning can maintain the work of the rest low-burning-rate gas generating agent. Preferably, a high-burning-rate formula with the length of 5mm is adopted, and if the duration time of the low-temperature condition of the working environment is long and the requirement on low-temperature ignition is high, the length of the high-burning-rate formula can be selectively increased.
The length-diameter ratio of the grain part 5 is more than 4: 1. the aspect ratio in this example is 4.3: 1. the density of the grain part 5 is in the range of 2.1g/cm3～2.5g/cm3The explosive column part 5 adopts solid cylindrical explosive charge, so that the filling density is increased, the end face of the explosive column is combusted, and the temperature of gas generated by igniting and combusting the explosive column part 5 is not higher than 350 ℃.
The working process of the invention is as follows:
igniter 1 work back, produces the gas, lights gaseous charge part 5, and the burning of generator head charge part 5 produces nitrogen gas, and the gas is most discharged through the head exhaust hole, and little part gas passes through the gas channel between charge part 5 and the casing 6, mills flat micropore via the afterbody and discharges, and this part gas continuously preheats gaseous charge part 5, keeps it to have relatively higher temperature. The heat released in the reaction of the charge part 5 maintains the subsequent charge part 5 to be continuously combusted, and the necessary condition for the combustion to be continuously carried out is that enough heat is available. The heat transfer mode of the explosive column part 5 mainly comprises convection heat exchange and heat conduction. After the generator works, a part of heat generated by the explosive column part 5 heats the subsequent unburned explosive column part 5 through heat conduction; in the other part, because the tail end of the generator is not completely sealed, part of the airflow flows through the charge part 5, and the subsequent charge part 5 is preheated in a convection heat exchange mode. The heat transfer and gas flow process of the charge part 5 is shown in fig. 3.
The solid cold gas generator structure for the space propulsion system designed by the invention can solve the problem of combustion and flameout of the grain part 5 with large length-diameter ratio and realize complete combustion of the grain part 5.
Ignition tests were performed on generators with added exhaust ports and without milling flat bottom caps. Flameout occurs in 10 generators without exhaust holes, and flameout does not occur in 10 generators with milling amount of 0.2 mm. The solid cold gas generator with the milled flat exhaust holes is successfully applied in the rail, and the problem of flameout does not occur. FIG. 5 is a typical P-t plot (23 deg.C) of the present invention after ignition in a 10L closed container.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (10)
1. A solid cold gas generator structure for a space propulsion system, comprising: the device comprises an igniter (1), a backing ring (2), a filter screen (3), a support ring assembly (4), a grain part (5), a shell (6) and a U-shaped bottom cover (7);
one end of the igniter (1) extends out of the shell (6) to the top and is connected with the backing ring (2) through threads, and the backing ring (2) is positioned outside the shell (6);
a filter screen (3) is sleeved on the outer wall of the igniter (1), and the filter screen (3) is positioned inside the shell (6);
the explosive column component (5), the support ring component (4) and the shell (6) are sleeved in sequence from inside to outside, and the explosive column component (5) is arranged below the igniter (1) through the support ring component (4);
the U-shaped bottom cover (7) is arranged below the grain part (5); the U-shaped bottom cover (7) and the inner wall of the shell (6) are welded and fixed;
a plurality of circular vent holes are uniformly distributed on the top of the shell (6) in the circumferential direction;
the support ring assembly (4) is used for preventing the outer wall of the grain part (5) from contacting the inner wall of the shell (6), and a gap between the outer wall of the grain part (5) and the inner wall of the shell (6) is used for guiding gas;
a plurality of notches are processed on the outer wall of the U-shaped bottom cover (7) along the radial direction, and the notches are used for enabling gas generated by combustion of the explosive column (5) to flow out of the shell (6).
2. A solid cold gas generator structure for space propulsion systems according to claim 1, characterized by the fact that the length/diameter ratio of the charge column part (5) is greater than 4: 1.
3. the solid cold gas generator structure for the space propulsion system as claimed in claim 2, wherein the filter screen (3) is formed by sintering a plurality of layers of stainless steel wire meshes, and the axial length of the filter screen (3) ranges from 1.5 mm to 2.5 mm.
4. The structure of claim 3, wherein the stainless steel wire mesh has a pore size ranging from 20 μm to 50 μm.
5. A solid cold gas generator structure for space propulsion system according to any of claims 2 to 4, characterized in that the cartridge part (5) is composed of 2 formulations including: a high-burning-rate gas generating agent formula and a low-burning-rate gas generating agent formula; the mass ratio value range of the formula of the high-combustion-rate gas generating agent in the grain part (5) is 7-15%.
6. A solid cold gas generator structure for space propulsion system according to claim 5, characterized in that the density of the column part (5) ranges from 2.1g/cm3～2.5g/cm3The temperature of the gas generated by igniting and burning the explosive column part (5) is not higher than 350 ℃.
7. The structure of solid cold gas generator for space propulsion system as claimed in any one of claims 2 to 4, wherein 5 to 8 circular exhaust holes are uniformly distributed on the top of the shell (6) in circumference.
8. The structure of solid cold gas generator for space propulsion system as claimed in claim 7, characterized in that the material of the shell (6) is stainless steel, and the wall thickness of the shell (6) ranges from 1mm to 1.2 mm.
9. The structure of the solid cold gas generator for the space propulsion system as claimed in claim 8, wherein the radial dimension of the gap of the outer wall of the U-shaped bottom cover (7) ranges from 0.1 mm to 0.4 mm;
the number of the notches on the outer wall of the U-shaped bottom cover (7) ranges from 3 to 6.
10. The structure of solid cold gas generator for space propulsion system as claimed in claim 9, wherein the gap between the outer wall of the column part (5) and the inner wall of the housing (6) has a value ranging from 0.4mm to 0.8 mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011127712.1A CN112377328B (en) | 2020-10-20 | 2020-10-20 | Solid cold gas generator structure for space propulsion system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011127712.1A CN112377328B (en) | 2020-10-20 | 2020-10-20 | Solid cold gas generator structure for space propulsion system |
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| CN112377328B true CN112377328B (en) | 2021-09-07 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4771601A (en) * | 1986-05-30 | 1988-09-20 | Erno Raumfahrttechnik Gmbh | Rocket drive with air intake |
| US7503165B2 (en) * | 2004-09-29 | 2009-03-17 | Spacedev, Inc. | Hybrid propulsion system |
| CN103921956A (en) * | 2014-04-16 | 2014-07-16 | 南京理工大学 | Solid cool air micro-propelling system |
| CN106246411A (en) * | 2016-07-22 | 2016-12-21 | 北京控制工程研究所 | A kind of height always rushes solid cold gas micro propulsion device |
| CN107514320A (en) * | 2017-07-10 | 2017-12-26 | 北京控制工程研究所 | A kind of micromass culture modular structure based on high pressure frontier technology |
-
2020
- 2020-10-20 CN CN202011127712.1A patent/CN112377328B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4771601A (en) * | 1986-05-30 | 1988-09-20 | Erno Raumfahrttechnik Gmbh | Rocket drive with air intake |
| US7503165B2 (en) * | 2004-09-29 | 2009-03-17 | Spacedev, Inc. | Hybrid propulsion system |
| CN103921956A (en) * | 2014-04-16 | 2014-07-16 | 南京理工大学 | Solid cool air micro-propelling system |
| CN106246411A (en) * | 2016-07-22 | 2016-12-21 | 北京控制工程研究所 | A kind of height always rushes solid cold gas micro propulsion device |
| CN107514320A (en) * | 2017-07-10 | 2017-12-26 | 北京控制工程研究所 | A kind of micromass culture modular structure based on high pressure frontier technology |
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| CN112377328A (en) | 2021-02-19 |
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