Water-cooling type electronic control solid micro-thruster
By designing a water-cooled, electrically controlled solid micro-thruster, the temperature of the propulsion unit and the outer shell is controlled by a liquid cooling chamber, which solves the controllability and safety issues of the electrically controlled solid thruster, and expands the thrust adjustment range and extends the working time.
Patent Information
- Application Number
- CN202520559330.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-27
- Publication Date
- 2025-12-16
- Estimated Expiration
- 2035-03-27
AI Technical Summary
Existing electrically controlled solid rocket motors suffer from problems such as limited combustion chamber diameter, small thrust adjustment range, short operating time, and difficulty in extinguishing self-sustaining combustion, resulting in a loss of controllability of the motor.
Design a water-cooled, electrically controlled solid micro-thruster, which consists of a thruster housing, a nozzle, and a propulsion unit. The temperature of the propulsion unit and housing is controlled by a liquid cooling chamber. The propulsion unit is composed of a cathode annular wall plate and an anode column, and efficient temperature management is achieved by combining the cooling medium.
It improves the controllability and safety of the thruster, achieves uniform cooling of multiple propulsion units, significantly enhances thrust and thrust adjustment range, extends working time, and avoids self-sustaining combustion.
Smart Images
Figure CN223676390U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the field of propeller, concretely relates to a water -cooling type electric control solid micro propeller. BACKGROUND
[0002] With the rapid development of space vehicles and missiles, the tasks to be performed by them are also increasingly diversified. In addition to implementing orbit transfer, docking, formation flight and flight attitude adjustment, they may also need to perform tasks such as damping compensation, orbit lifting and even emergency avoidance. Therefore, higher requirements are put forward for the propulsion system, which needs to have the ability of multiple start-ups and thrust regulation. At present, solid propellers and liquid propellers still dominate, but liquid propellers have the problem of many complex components such as pipelines and valves, and there is a risk of leakage of working medium. Although the traditional solid propeller has simple structure and high reliability, it is uncontrollable in combustion and difficult to re-ignite, and cannot meet the current demand in the context of multiple tasks.
[0003] The electric control solid propelling technology uses a solid propellant (ECSP) with special electrochemical properties. The ECSP will not burn under high-temperature flame, but can be ignited under the action of electric current. By adjusting the size of the applied voltage, the regulation of the propellant burning rate can be achieved. After power-off, the propellant is extinguished, and the propellant burns again after power-on again, thereby realizing the re-ignition of the thruster. In the field of microsatellite propulsion, it will have a broad application prospect. The electric control solid propeller has become one of the research hotspots in the propulsion field because of its simple and reliable structure, repeatable start-up and controllable thrust.
[0004] The commonly used electric control solid propeller has a coaxial electrode structure. The negative and positive electrodes are formed by a single electrode rod and a shell. Although the structure is simple, the diameter of the combustion chamber cannot be too large, otherwise it will lead to uneven distribution of current density, decrease of propellant combustion efficiency or difficulty in multiple ignition, thus existing problems of limited charge capacity, short working time and small thrust regulation range. At the same time, in the later stage of combustion, due to heat accumulation and enhanced combustion chamber pressure, the electric control solid propellant may occur self-sustaining combustion, the extinguishing delay time becomes longer, and the extinguishing becomes difficult, so that the thruster cannot stop working even if the power is off, and loses controllability. UTILITY MODEL CONTENTS
[0005] The utility model solves the technical problem to provide a stable and controllable water-cooled electric control solid micro propeller.
[0006] The utility model provides a water-cooled electric control solid micro propeller, including propeller shell, nozzle and at least one propelling unit;
[0007] The propeller shell includes an annular side wall and end plates arranged at both ends of the annular side wall, and the annular side wall and the two end plates enclose a containing cavity.
[0008] The propelling unit comprises a cathode annular wall plate, an insulating sealing cover and an anode column, the cathode annular wall plate is arranged in the accommodating cavity, and two ends of the cathode annular wall plate abut against two end plates respectively, and through holes penetrating the interior space of the cathode annular wall plate are arranged on the two end plates, the insulating sealing cover is sealingly arranged on the through hole on one side, and the anode column is arranged on the insulating sealing cover, and one end of the anode column extends into the cathode annular wall plate through the through hole, and the other end is located outside the accommodating cavity;
[0009] The nozzle is arranged on the side of the propeller shell away from the insulating sealing cover, and the inlet of the nozzle is communicated with the through hole on the side;
[0010] The outer side of the cathode annular wall plate and the inner wall of the accommodating cavity form a liquid cooling cavity, and the propeller shell is provided with a liquid inlet and a liquid outlet communicating with the liquid cooling cavity.
[0011] Further, the end plate arranged on one side of the nozzle is arranged on the inner side of the annular side wall, and the inner wall of the annular side wall protruding from the position of the end plate is provided with an internal thread;
[0012] The inlet end of the nozzle is provided with an external thread, and the nozzle is screwed on the propeller shell.
[0013] Further, the end plate arranged on one side of the insulating sealing cover is arranged on the end face of the annular side wall, and the outer side of the end plate extends outwardly and is provided with a flange plate;
[0014] The outer wall of the flange plate is provided with a mounting hole.
[0015] Further, when a plurality of propelling units are arranged, the plurality of through holes on one side of the nozzle are communicated with the inlet of the nozzle.
[0016] Further, when a plurality of propelling units are arranged, the plurality of cathode annular wall plates are spaced from each other.
[0017] Further, the insulating sealing cover comprises a plug body and a limiting plate arranged in pairs;
[0018] The plug body is sealingly matched with the through hole, and the limiting plate is abutted and arranged on the outer side of the end plate.
[0019] Further, the plug body and the limiting plate are bonded by glue between the outer wall of the plug body and the inner wall of the through hole, and between the limiting plate and the end plate.
[0020] Further, the insulating sealing cover is made of polytetrafluoroethylene material.
[0021] Further, the annular side wall, the cathode annular wall plate and the at least one end plate are made of electrically conductive material.
[0022] Further, the annular side wall and the cathode annular wall plate are both circular rings.
[0023] The propulsion units are arranged in a ring array around the annular side wall axis.
[0024] The water-cooled electric control solid micro-propeller has the advantages that the rational position distribution of the propeller shell and the cathode annular wall plate can realize efficient temperature control of the cooling medium on the propulsion units and the propeller shell, ensure the temperature of the electric control solid propellant and the outer side of the propeller, improve the controllability and safety of the propeller, when multiple propulsion units are arranged, uniform cooling of the multiple propulsion units can be ensured, and the thrust can be significantly improved. BRIEF DESCRIPTION OF DRAWINGS
[0025] FIG. 1 is a structural schematic diagram of the present utility model; Figure 1 FIG. 2 is a right view of the present utility model;
[0026] FIG. 3 is a sectional view along A-A direction of the present utility model; Figure 2 FIG. 4 is a sectional view along B-B direction of the present utility model;
[0027] FIG. 5 is a sectional view along C-C direction of the present utility model. Figure 3 FIG. 6 is a sectional view along D-D direction of the present utility model. Figure 2
[0028] FIG. 7 is a sectional view along E-E direction of the present utility model. Figure 4 FIG. 8 is a sectional view along F-F direction of the present utility model. Figure 2
[0029] FIG. 9 is a sectional view along G-G direction of the present utility model. Figure 5 FIG. 10 is a sectional view along H-H direction of the present utility model. Figure 3 FIG. 11 is a sectional view along I-I direction of the present utility model.
[0030] In the drawings, 1-propeller shell; 11-annular side wall; 111-internal thread; 12-end plate; 121-through hole; 122-flange; 123-mounting hole; 13-accommodation cavity; 14-liquid inlet; 15-liquid outlet; 2-nozzle; 21-external thread; 3-propulsion unit; 31-cathode annular wall plate; 32-insulating sealing cover; 321-plug body; 322-limiting plate; 33-anode column; 4-liquid cooling cavity. DETAILED DESCRIPTION
[0031] The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments in the present utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present utility model.
[0032] It should be noted that all directional indications, such as up, down, left, right, front, back, etc., are only used to explain the relative position relationship, movement condition, etc. between components in a certain specific posture (as shown in the drawings), and if the specific posture changes, the directional indications will also change accordingly.
[0033] In addition, the description of "first", "second" and the like in the present application is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can be explicitly or implicitly included at least one of the features. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise specifically limited.
[0034] In the present application, unless otherwise specifically defined and limited, the terms "connection", "fixing" and the like should be broadly understood, for example, "fixing" can be fixed connection, or detachable connection, or integral; can be mechanical connection, or electrical connection, or physical connection or wireless communication connection; can be directly connected, or indirectly connected through intermediate medium, can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise specifically limited. For ordinary skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.
[0035] In addition, the technical solutions of each embodiment of the present application can be combined with each other, but it must be based on the realization of ordinary skilled in the art, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, also not within the scope of protection required by the present application.
[0036] As shown in the accompanying drawings Figure 1 -attached Figure 5 The utility model provides a water -cooling type electric control solid micro -propeller, including propeller shell 1, nozzle 2 and at least one propelling unit 3;
[0037] The propeller shell 1 includes annular side wall 11 and the end plate 12 of setting at annular side wall 11 both ends, the annular side wall 11 and two end plates 12 enclose and form the accommodation cavity 13;
[0038] The propelling unit 3 comprises a cathode annular wall plate 31, an insulating sealing cover 32 and an anode column 33, the cathode annular wall plate 31 is arranged in the accommodating cavity 13, and the two ends of the cathode annular wall plate 31 abut against the two end plates 12 respectively, and the two end plates 12 are provided with through holes 121 penetrating the internal space of the cathode annular wall plate 31, the insulating sealing cover 32 is sealingly arranged on one of the through holes 121, and the anode column 33 penetrates the insulating sealing cover 32, and one end of the anode column 33 extends into the cathode annular wall plate 31 through the through hole 121, that is, the through hole 121 on this side is used for mounting the insulating sealing cover 32 and the anode column 33.
[0039] The nozzle 2 is arranged on the side of the propeller shell 1 away from the insulating sealing cover 32, and the inlet of the nozzle 2 communicates with the through hole 121 on this side, and the through hole 121 on this side is used for jetting the flame generated by the propelling unit 3, that is, as the jetting port of the propelling unit 3.
[0040] The outer side of the cathode annular wall plate 31 and the inner wall of the accommodating cavity 13 form a liquid cooling cavity 4, at this time, the accommodating cavity 13 is covered by the liquid cooling cavity 4 and the cathode annular wall plate 31, the propeller shell 1 is provided with an inlet 14 and an outlet 15 communicating with the liquid cooling cavity 4, and the cooling medium is injected into the liquid cooling cavity 4 from the inlet 14, and the cooling medium in the liquid cooling cavity 4 exchanges heat with the cathode annular wall plate 31 and then flows out from the outlet 15, so that the temperature control of the propelling unit 3 and the propeller shell 1 can be realized, and the self-sustaining combustion caused by the high temperature of the electrically controlled solid propellant can be effectively prevented, and the controllability of the propeller in the later stage can be ensured.
[0041] The water-cooled electrically controlled solid micro-propeller can realize efficient temperature control of the propelling unit 3 and the propeller shell 1 by the reasonable position distribution of the propeller shell 1 and the cathode annular wall plate 31, can ensure the temperature of the electrically controlled solid propellant and the outer side of the propeller, and can improve the controllability and safety of the propeller, and when a plurality of propelling units 3 are arranged, the uniform cooling of the plurality of propelling units 3 can be ensured, and the thrust can be significantly improved.
[0042] In one of the embodiments, the end plate 12 arranged on one side of the nozzle 2 is arranged on the inner side of the annular side wall 11, that is, the end plate 12 is away from the end face of the annular side wall 11 by a certain distance, and the inner wall of the annular side wall 11 protruding from the position of the end plate 12 is provided with an internal thread 111.
[0043] The inlet end of the nozzle 2 is provided with an external thread 21, and the nozzle 2 is threadedly arranged on the propeller shell 1.
[0044] In the embodiment, the threaded connection is convenient to disassemble and assemble, can play a sealing effect, can ensure stable combustion of the propellant in the combustion chamber, and is not easy to disintegrate under high-pressure combustion and is not easy to be damaged when the force is large.
[0045] In one of the embodiments, the end plate 12 arranged on one side of the insulation sealing cover 32 is arranged on the end surface of the annular side wall 11, and the outer side of the end plate 12 is outwardly extended and provided with a flange plate 122;
[0046] The outer wall of the flange plate 122 is provided with a mounting hole 123, which is used to fix the water-cooled type electric control solid micro-propeller on the mounting position, thereby ensuring the stability of the device during work.
[0047] Preferably, the annular side wall 11 and the two end plates 12 are integrally formed, or can be assembled and welded, so as to ensure the structural stability of the propeller shell 1.
[0048] In one of the embodiments, when a plurality of propelling units 3 are arranged, the plurality of through holes 121 arranged on one side of the nozzle 2 are in communication with the inlet of the nozzle 2. In this way, the propelling flames of the plurality of propelling units 3 are concentrated in the nozzle 2 for injection, so as to ensure more concentrated thrust and improve the thrust. When a plurality of propelling units 3 are arranged, the charge amount can be increased, the propeller thrust adjustment range can be increased, the propeller working time can be increased, and the problem of uneven current distribution and low combustion efficiency caused by the too large diameter of the combustion chamber of the coaxial type electric control solid propeller can be avoided.
[0049] In one of the embodiments, when a plurality of propelling units 3 are arranged, the plurality of cathode annular wall plates 31 are spaced from each other, so that the cooling medium in the liquid cooling cavity 4 can uniformly contact the cathode annular wall plate 31 of each propelling unit 3, thereby ensuring the cooling effect of each propelling unit 3.
[0050] In one of the embodiments, the insulation sealing cover 32 comprises a plug body 321 and a limiting plate 322 arranged in each other, the outer size of the limiting plate 322 is greater than the outer size of the plug body 321, so that the insulation sealing cover 32 has a stepped structure, the limiting plate 322 can not only improve the sealing effect, but also improve the insulation effect, and can be used for position limiting during installation, thereby simplifying the installation difficulty;
[0051] The plug body 321 is sealingly matched with the through hole 121, and the limiting plate 322 is abuttingly arranged on the outer side of the end plate 12, that is, the insulation sealing cover 32 and the through hole 121 are in stepped compression, so as to further ensure the sealing effect.
[0052] In one of the embodiments, the outer wall of the plug body 321 and the inner wall of the through hole 121, and the limiting plate 322 and the end plate 12 are bonded by glue, which can further improve the fixing stability of the insulating sealing cover 32 and the through hole 121. Preferably, the insulating sealing cover 32 and the through hole 121 are bonded by AB glue.
[0053] In one of the embodiments, the insulating sealing cover 32 is made of polytetrafluoroethylene material, thereby realizing the insulation between the anode column 33 and the cathode annular wall plate 31.
[0054] In one of the embodiments, the annular side wall 11, the cathode annular wall plate 31 and the at least one end plate 12 are made of conductive material, that is, the negative electrode connection of the cathode annular wall plate 31 can be realized by connecting the power negative electrode through the annular side wall 11. Preferably, the annular side wall 11, the cathode annular wall plate 31 and the end plate 12 are all made of stainless steel material.
[0055] In one of the embodiments, the annular side wall 11 and the cathode annular wall plate 31 are both circular ring type.
[0056] The three propelling units 3 are arranged in a ring array around the axis of the annular side wall 11, which can protect the uniform injection of the flame, ensure the propelling effect, and uniformly distribute the weight. In other embodiments, the propelling unit 3 can also be more than three.
[0057] In this embodiment, the thruster is internally composed of three coaxial electrically controlled solid propelling units 3, which can effectively improve the working time and thrust adjustment range of the thruster, and at the same time will not affect the combustion efficiency of each propelling unit 3. The liquid cooling cavity 4 can take away the heat generated by combustion to prevent the temperature of the electrically controlled solid propellant from being too high to cause self-sustaining combustion, resulting in the loss of controllable performance of the thruster.
[0058] In specific use, the three anode columns 33 are connected to the positive electrode of the power supply, and the outer side of the anode column 33 is wrapped with a polyethylene film. Specifically, the anode column 33 extends into the position of the cathode annular wall plate 31, and the outer periphery of the segment 1.5-2.5mm away from the end is wrapped with a polyethylene film, and the other end is located outside the accommodating cavity 13 for connecting the positive electrode of the power supply. The electrically controlled solid propellant is arranged in the cathode annular wall plate 31, and the height of the electrically controlled solid propellant needs to be higher than the polyethylene film, and at the same time should not be higher than the end of the anode column 33. The cathode annular wall plate 31 is connected to the negative electrode of the power supply, and the electrically controlled solid propellant is arranged in the cathode annular wall plate 31 and wrapped with a polyethylene film.
[0059] The working process of the thruster is as follows: the anode column 33 and the thruster shell 1 are respectively connected to the positive and negative poles of a power supply, a circuit is turned on, the three propulsion units 3 are connected in parallel in the circuit and work simultaneously, the electrically-controlled solid propellant starts to burn to generate a large amount of high-temperature gas, three high-temperature gas jets are gathered in the nozzle 2 and are jetted out, so that a thrust is generated, the polyethylene film covered by the anode column 33 is propelled together with the propellant surface along with the burning of the propellant, and the thrust adjustment of the thruster can be realized by changing the size of the voltage. When the power supply is stopped, the thruster is extinguished, and after the power supply is supplied again, the electrically-controlled solid propellant can be burned together with the polyethylene film again, the thruster can be ignited again, and a corresponding thrust is generated. The whole working process is real-time controllable, and repeated ignition and extinguishing can be realized.
[0060] The above is only the embodiment of the present application, and does not limit the present application. Any person skilled in the art can make many possible changes, modifications or modifications to the technical scheme of the present application without departing from the scope of the technical scheme of the present application, and the equivalent embodiments of equivalent changes. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application shall fall within the scope of protection of the technical scheme of the present application.
Claims
1. A water-cooled electrically controlled solid microthruster, characterized by, The thruster shell (1) comprises an annular side wall (11) and end plates (12) arranged at both ends of the annular side wall (11), and the annular side wall (11) and the two end plates (12) enclose a receiving cavity (13); The thruster shell (1) comprises an annular side wall (11) and end plates (12) arranged at both ends of the annular side wall (11), and the annular side wall (11) and the two end plates (12) enclose a receiving cavity (13); The thruster shell (1) comprises an annular side wall (11) and end plates (12) arranged at both ends of the annular side wall (11), and the annular side wall (11) and the two end plates (12) enclose a receiving cavity (13); The nozzle (2) is arranged on the side of the thruster shell (1) away from the insulating sealing cover (32), and the inlet of the nozzle (2) is in communication with the through hole (121) on the side. The outside of the cathode annular wall plate (31) and the inner wall of the receiving cavity (13) form a liquid cooling cavity (4), and the thruster shell (1) is provided with a liquid inlet (14) and a liquid outlet (15) in communication with the liquid cooling cavity (4).
2. The water-cooled electrically controlled solid microthruster according to claim 1, wherein The end plate (12) arranged on the side of the nozzle (2) is arranged inside the annular side wall (11), and the inner wall of the annular side wall (11) at the position of the end plate (12) is provided with an internal thread (111); The inlet end of the nozzle (2) is provided with an external thread (21), and the nozzle (2) is threadedly arranged on the thruster shell (1).
3. The water-cooled electrically controlled solid microthruster as claimed in claim 1, wherein The end plate (12) arranged on the side of the insulating sealing cover (32) is arranged on the end face of the annular side wall (11), and the outside of the end plate (12) extends outwardly and is provided with a flange plate (122); The outer wall of the flange plate (122) is provided with a mounting hole (123).
4. The water-cooled electrically controlled solid microthruster as claimed in claim 1, wherein the water-cooled electrically controlled solid microthruster is characterized by comprising: When the thruster unit (3) is provided with a plurality of thruster units, the plurality of through holes (121) arranged on the side of the nozzle (2) are in communication with the inlet of the nozzle (2).
5. The water-cooled electrically controlled solid microthruster of claim 1, wherein the at least one of the first and second electrodes is formed of a material selected from the group consisting of: aluminum, copper, silver, gold, platinum, and alloys thereof. When the thruster unit (3) is provided with a plurality of thruster units, the plurality of cathode annular wall plates (31) are spaced apart from each other.
6. The water-cooled electrically controlled solid microthruster of claim 1 wherein, The insulating sealing cover (32) comprises a plug body (321) and a limiting plate (322) arranged opposite to each other; The plug body (321) is sealingly fitted with the through hole (121), and the limiting plate (322) is abuttingly arranged on the outside of the end plate (12).
7. The water-cooled electrically controlled solid microthruster according to claim 6, wherein The outer wall of the plug body (321) and the inner wall of the through hole (121), and the limiting plate (322) and the end plate (12) are bonded by glue.
8. The water-cooled electrically controlled solid microthruster as claimed in claim 6, wherein The insulating sealing cover (32) is made of polytetrafluoroethylene material.
9. The water-cooled electrically controlled solid microthruster according to any one of claims 1 to 8, wherein The annular side wall (11), the cathode annular wall plate (31) and the at least one end plate (12) are made of conductive material.
10. The water-cooled electrically controlled solid microthruster according to any one of claims 1 to 8, wherein The annular side wall (11) and the cathode annular wall plate (31) are both circular rings; The propulsion units (3) are arranged in a ring array with the annular side wall (11) axis as the center.