CN220909842U - Multi-electrode electric control solid micro-propeller - Google Patents
Multi-electrode electric control solid micro-propeller Download PDFInfo
- Publication number
- CN220909842U CN220909842U CN202322752353.4U CN202322752353U CN220909842U CN 220909842 U CN220909842 U CN 220909842U CN 202322752353 U CN202322752353 U CN 202322752353U CN 220909842 U CN220909842 U CN 220909842U
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- shell
- electrode rods
- power supply
- propeller
- electric control
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- 239000007787 solid Substances 0.000 title claims abstract description 18
- 239000004449 solid propellant Substances 0.000 claims abstract description 23
- 238000000576 coating method Methods 0.000 claims abstract description 15
- 239000011248 coating agent Substances 0.000 claims abstract description 13
- 239000000126 substance Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 7
- -1 polytetrafluoroethylene Polymers 0.000 claims description 5
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 5
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 5
- 229920001800 Shellac Polymers 0.000 claims description 4
- ZLGIYFNHBLSMPS-ATJNOEHPSA-N shellac Chemical compound OCCCCCC(O)C(O)CCCCCCCC(O)=O.C1C23[C@H](C(O)=O)CCC2[C@](C)(CO)[C@@H]1C(C(O)=O)=C[C@@H]3O ZLGIYFNHBLSMPS-ATJNOEHPSA-N 0.000 claims description 4
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- 235000013874 shellac Nutrition 0.000 claims description 4
- 239000004208 shellac Substances 0.000 claims description 4
- 108091092878 Microsatellite Proteins 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 25
- 239000003380 propellant Substances 0.000 description 11
- 239000002360 explosive Substances 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 230000001276 controlling effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000008033 biological extinction Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
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- 230000037431 insertion Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
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- 230000001105 regulatory effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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Abstract
The utility model belongs to the technical field of microsatellite propellers, and particularly relates to a multi-electrode electric control solid micro propeller. Comprises a shell, a nozzle, four internal electrode rods, an insulating coating, a base, an electric control solid propellant and a power supply control module; the bottom of the shell is connected with the base, the shell is connected with the anode of the external power supply control module, four internal electrode rods are cylindrical and are symmetrically and uniformly distributed in the shell, the positions of the four internal electrode rods are fixed through equal-diameter holes in the base, the four electrode rods are connected and then connected to the cathode of the power supply control module, an electric control solid propellant containing conductive substances is filled between the electrode rods and the shell, the other end of the shell is connected with a nozzle in a threaded manner, and the periphery of the electrode rods except for a section 1.5-2.5mm away from the nozzle is coated with an insulating coating. Compared with a single-electrode propeller, the utility model has a larger thrust adjusting range, and the adjustment and the accurate control of the thrust are realized by changing the power supply.
Description
Technical Field
The utility model belongs to the technical field of microsatellite propellers, and particularly relates to a multi-electrode electric control solid micro propeller.
Background
The rapid development of spacecraft and missiles places higher demands on their propulsion systems. The small space aircraft needs to implement orbit transfer, butt joint, formation flight and flight attitude adjustment, and the missile needs to have high maneuverability, rapid burst prevention and accurate interception. Thus, the propulsion system needs to have multiple start and thrust adjustment capabilities. At present, a solid engine and a liquid engine still dominate, but the solid engine has high maintenance cost, cannot flexibly control the thrust and cannot be started repeatedly, a liquid propeller pipeline is too complex, the safety is required to be high, the emission preparation time is long, and meanwhile, the problems of high fuel purity and proportioning requirements, difficult preservation and the like are also faced.
The traditional electric propulsion technology relies on electric energy to drive an accelerating working medium to generate thrust, has larger specific impulse and higher thrust adjustment precision, but has the defects of high power consumption, small thrust and the like. The electric control propulsion means that the electric energy is used for controlling the combustion of the solid propellant to generate thrust, and the electric control propulsion device has the advantages of simple structure, low power consumption, large thrust and the like, and has the characteristics of repeated starting, high reliability, low maintenance cost and the like. The electric control propulsion generally adopts solid propellant as fuel, and stepless adjustment of the burning speed and control of the burning out of the propellant are realized by changing the magnitude of the applied voltage. Compared with the traditional electric propulsion technology, the electric propulsion can provide higher thrust adjustment capability and precision, and the thrust size and direction can be quickly adjusted according to the needs.
The coaxial electric control solid micro-propeller adopts a single pole and a shell to form a negative pole and a positive pole, the thrust adjusting range is small, and the diameter of a combustion chamber cannot be too large, otherwise, uneven current density distribution, reduced combustion efficiency of the propellant or difficult ignition for multiple times can be caused. Due to structural limitations, multiple electrodes have higher propulsion efficiency and energy utilization than single electrodes coaxial.
Disclosure of utility model
The utility model aims to provide a multi-electrode electric control solid micro-propeller. The propeller designed by the utility model has the advantages that the shell is used as the positive electrode, the diameter of the propeller is larger than that of a traditional micro-propeller, four electrodes are symmetrically and uniformly distributed in the propeller to serve as the negative electrode, so that the current density is effectively increased, a larger-layer combustion surface can be provided, the phenomenon that the explosive is sunk and incompletely combusted can not occur when the explosive is used for a larger-area explosive, more gas is generated, the upper limit of the thrust can be effectively improved, the pushing range is correspondingly increased, and the charging process and the assembly process are simplified while the thrust performance is greatly enhanced.
The technical solution for realizing the purpose of the utility model is as follows: a multi-electrode electric control solid micro-propeller comprises a shell, a nozzle, four internal electrode rods, an insulating coating, a base, an electric control solid propellant and a power supply control module;
The bottom of the shell is connected with the base, the shell is connected with the anode of the external power supply control module, four internal electrode rods are cylindrical and are symmetrically and uniformly distributed in the shell, the positions of the four internal electrode rods are fixed through equal-diameter holes in the base, the four electrode rods are connected and then connected to the cathode of the power supply control module, an electric control solid propellant containing conductive substances is filled between the electrode rods and the shell, the other end of the shell is connected with a nozzle in a threaded manner, and the periphery of the electrode rods except for a section 1.5-2.5mm away from the nozzle is coated with an insulating coating.
Furthermore, the bottom of the shell and the base are in stepped compression joint.
Further, the four electrode bars are connected using wires or a PCB circuit board.
Further, the insulating coating (5) is shellac with the thickness of 0.05mm-0.1mm, and is coated by a needle tube.
Furthermore, the nozzle adopts a fireproof polytetrafluoroethylene material, and the nozzle adopts a structure that the nozzle converges before diverges.
Furthermore, the base is made of polytetrafluoroethylene materials.
The assembly method of the electric control solid micro-propeller comprises the following steps:
Step (1): coating insulating coatings on the peripheries of the four electrode bars;
Step (2): when the powder is charged, the bottom of the shell is connected with the base, meanwhile, the shell is connected with the anode of the external power supply control module, and a seal is assembled at one end of the shell to prevent the powder from being excessively charged;
Step (3): an electric control solid propellant is filled between the electrode and the shell, after the electric control solid propellant is filled, the electrode rod is inserted from the base while the electric control solid propellant is hot, the electric control solid propellant penetrates through the whole shell device and is inserted to the end of the shell, which is connected with the nozzle, to be level or exposed for 1-3mm, and the four electrode rods are connected to the negative electrode of the power supply control module by using a lead or a PCB circuit board;
step (4): the nozzle is adopted to replace the seal.
Compared with the prior art, the utility model has the remarkable advantages that:
(1) The four internal electrodes greatly increase the current density, the area of layer combustion is also increased, the thrust is far greater than that of a single-electrode propeller, the adjustable range of the thrust is increased, the thrust of each grain under different conditions can be clearly defined through calibration, the thrust is more easily adjusted, and meanwhile, the current density is increased, and the grain collapse caused by incomplete combustion of the medicine is also weakened.
(2) Compared with an array type micro-propeller, the utility model has the advantages of simple structure, convenient assembly, more concentrated thrust and larger effective volume.
(3) The components of the utility model are connected through the threaded ports, so that the connection is firmer, the high pressure impact can be born, and the sealing effect is better, so that the combustion effect of the combustion chamber is better, and the quick assembly and disassembly are facilitated.
(4) The electric control solid propellant used in the utility model contains conductive substances, has good conductivity, positive and negative electrodes and the electric control solid propellant directly form a closed loop, no wiring problem exists inside, and the related contents of the circuit are all concentrated in the control circuit board, so the whole propellant is simple and efficient.
Drawings
Fig. 1 is a front view, partly in section, of the overall structure of an electronically controlled solid micro-thruster with a spout according to the present utility model.
Fig. 2 is a front view, partly in cross-section, of the whole structure of the electronically controlled solid micro-propeller with seal of the present utility model.
Fig. 3 is a side view of the overall structure of the electronically controlled solid state micro-mover of the present utility model.
Reference numerals illustrate:
1-shell, 2-seal, 3-spout, 4-internal electrode stick, 5-insulating coating, 6-base, 7-automatically controlled solid propellant, 8-power supply control module.
Detailed Description
The utility model is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1-3, the multi-electrode electric control intelligent propeller comprises a shell 1, a seal 2, a nozzle 3, an internal electrode rod 4, an insulating coating 5, a base 6, an electric control solid propellant 7 and a power supply control module 8;
the bottom of the shell 1 is tightly connected with the base 6 in a stepped manner, the top of the shell 1 is connected with the nozzle 3 by adopting a threaded structure, the base 6 is provided with four symmetrically distributed round holes for fixing the positions of internal electrodes, so that a relatively stable combustion chamber is formed, and the uniformity of experimental results is conveniently ensured;
The internal electrode rod 4 is connected with the negative electrode of the power supply control module 8 after being connected together, and the shell 1 is connected with the power supply control module 8 to serve as the positive electrode;
the threaded connection can ensure that the propellant in the combustion chamber burns stably while having a sealing effect, is not easy to disintegrate under high-pressure combustion, and is not easy to damage when the acting force is large.
The propellant grains used in the propeller all use the electric control solid propellant 7, the electric control solid propellant 7 can realize the power-on combustion, the power-off extinction, and the current density is large enough under the structure, so that the stable layer combustion performance can be realized.
The electric control solid propellant 7 is filled between the electrode rod 4 and the shell 1, and the electrode rod 4 is inserted when the electric control solid propellant 7 is still hot after the preparation of the electric control solid propellant 7 is completed in the assembly process, and the grains have plasticity at the moment, so that the grains can be in relatively tight contact after the insertion;
After the electrode rods 4 are inserted, the four holes of the base 6 are in interference fit with the electrode rods 4 with smaller tolerance, so that after the four electrode rods 4 are inserted, the diameter of the base 6 expands, and the connection with the shell 1 is more stable.
The insulating layer is coated on the electrode rod 4, and a mode of coating for multiple times and drying for multiple times is adopted. The mode can enable the coating of the insulating layer to be more uniform, the thickness meets the requirement, the insulating performance is stable, and the current breakdown is prevented; meanwhile, the selection and the thickness of the insulating layer are required to be adjusted according to the burning speed of the explosive column, so that the burning speed of the insulating layer is ensured to be consistent with the burning speed of the layer surface of the explosive column;
The shellac with good insulating property is selected as the insulating layer material, so that the propeller can realize uniform and proper burning speed;
the insulating layer coating process adopts a syringe needle with the diameter slightly larger than that of the electrode rod, the syringe needle is arranged in the syringe, the electrode rod is fixed after a proper amount of liquid shellac is arranged, and the syringe needle is inserted and slowly pushed into the syringe while the needle is taken out.
The propeller main body is made of a shell 1, an insulating layer and electrodes, wherein the four electrodes serve as cathodes, an insulating film layer is coated on the electrodes, then an electric control solid propellant 7 is filled into the shell 1, and then an electrode rod 4 is filled into the shell 1 to form the complete propeller. When the electrodes are supplied with current, the propellant ignites, and the combustion of the insulating film and the combustion of the explosive column are performed synchronously, so that each time the power is supplied again, ignition is ensured. When the power supply conditions are the same, the thrust generated by each combustion is relatively constant, when the power supply is stopped, the propellant stops burning, and the thrust is also stopped, and when the power supply is again performed, the propellant can burn again to generate the thrust.
The electrode is used for controlling ignition and combustion of the propellant, four electrode rods are used while a larger shell is used, so that the current density passing through the grain and the area of layer combustion are increased, and the ignition combustion is more stable.
The tightness between the explosive column and the main shell is not affected by the post-insertion of the electrode rod, and the explosive column has better plasticity when the electrode rod is inserted in the hot state, so that the electrode rod can be in relatively tight contact after the electrode rod is inserted, and the stable ignition and combustion of the propellant can be ensured;
the power supply control module starts combustion when supplying power, stops combustion when cutting off power, and can quickly generate a large amount of high-temperature gas to generate thrust, the thrust generated by the combustion of the propellant can be controlled by controlling the voltage and time of each power supply of the power supply module, namely, when the conditions such as time and the like are determined, the magnitude of the thrust is judged by measuring the voltage and the current so as to adjust;
The power supply can also supply quantitative charges through the discharging mode of the capacitor, and then the power supply is carried out through the quantitative charges, and the corresponding size of the charge quantity is adjusted according to the thrust requirement.
The nozzle 3 in the shell is made of a fireproof polytetrafluoroethylene material, and the material is high-temperature resistant and can prevent high-temperature gas and flame generated by combustion from melting or burning out the propeller component; the insulating property of the propeller can also block current, so that the safety of the propeller is improved by preventing the influence of external current: the nozzle adopts a structure that the nozzle converges before diverges, so that the gas expansion of the combustion chamber is accelerated to generate larger thrust. The spray pipe is connected with the shell through threads, and the cooperation is firm.
The working process of the device is as follows: the shell and the electrode rod are respectively connected with the anode and the cathode of the power supply, and the utility model connects the propeller with the control circuit board, then the circuit board is connected into the power supply, and the ignition and flameout of the propeller are controlled by controlling the power supply control module. The circuit is connected, the power supply is used for supplying current once, the electric control solid propellant and the insulating layer burn a part together, and a large amount of high-temperature gas is generated by burning, so that a certain thrust force is generated, the thrust force of the propeller can be accurately measured through calibration, and the required thrust force can be regulated in an auxiliary manner through the current and voltage detectors in the working process of the propeller. To change the thrust, this can be achieved by changing the magnitude of the voltage. When the power supply is stopped, the propeller is flameout, and after the power supply is performed again, the grain can burn together with the insulating layer, and the propeller can be ignited again to generate corresponding thrust. The whole working process is controllable in real time, and repeated ignition and flameout can be realized.
Finally, it should be noted that the above list is only a specific embodiment of the present utility model. Obviously, the utility model is not limited to the above embodiments, but many variations are possible. All modifications directly derived or suggested to one skilled in the art from the present disclosure should be considered as being within the scope of the present utility model.
Claims (5)
1. The multi-electrode electric control solid micro-propeller is characterized by comprising a shell (1), a nozzle (3), four internal electrode rods (4), an insulating coating (5), a base (6), an electric control solid propellant (7) and a power supply control module (8);
The bottom of the shell (1) is connected with the base (6), the shell (1) is connected with the anode of the external power supply control module (8), four internal electrode rods (4) are all cylinders and are symmetrically and uniformly distributed in the shell (1), the positions of the four internal electrode rods are fixed through equal-diameter holes in the base (6), the four electrode rods (4) are connected and then connected to the cathode of the power supply control module (8), an electric control solid propellant (7) containing conductive substances is filled between the electrode rods (4) and the shell (1), the other end of the shell (1) is connected with a nozzle (3) in a threaded mode, and the periphery of the electrode rods (4) except for a section 1.5-2.5mm away from the nozzle is coated with an insulating coating (5).
2. The electrically controlled solid micro-propeller according to claim 1, wherein the bottom of the housing (1) is crimped with the base (6) in a stepwise manner.
3. Electrically controlled solid micro-propeller according to claim 2, characterized in that four electrode rods (4) are connected using wires or PCB circuit boards.
4. An electrically controlled solid micro-propeller according to claim 3, characterized in that the insulating coating (5) is shellac with a thickness of 0.05mm-0.1mm, coated with a needle tube.
5. The electrically controlled solid micro-propeller according to claim 4, wherein the nozzle (3) is made of fireproof polytetrafluoroethylene material, and the nozzle (3) is of a convergent-divergent structure; the base (6) is made of polytetrafluoroethylene material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322752353.4U CN220909842U (en) | 2023-10-13 | 2023-10-13 | Multi-electrode electric control solid micro-propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322752353.4U CN220909842U (en) | 2023-10-13 | 2023-10-13 | Multi-electrode electric control solid micro-propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220909842U true CN220909842U (en) | 2024-05-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322752353.4U Active CN220909842U (en) | 2023-10-13 | 2023-10-13 | Multi-electrode electric control solid micro-propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220909842U (en) |
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2023
- 2023-10-13 CN CN202322752353.4U patent/CN220909842U/en active Active
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