阅读说明：本技术 一种微流量绿色高能单组元推力器结构 (A kind of micrometeor green high-capacity single group member thruster structure ) 是由 刘旭辉 付拓取 张伟 高晨光 官长斌 刘瀛龙 王梦 李永平 沈岩 陈君 王平 于 2019-05-28 设计创作，主要内容包括：本发明涉及一种微流量绿色高能单组元推力器结构,推进剂在催化床中催化剂作用下,实现催化分解,在燃烧室中进一步燃烧后经喷管喷出产生推力；热控组件安装在推力室催化床上,对催化床进行温度控制和监测。本发明提出了一种微流量绿色高能单组元推力器结构,通过导热片、毛细管导热丝等调控毛细管温度,抑制微流量下推进剂在毛细管中产生两相流,实现微流量绿色高能单组元推力器稳定工作。抑制微流量下推进剂在毛细管中产生两相流,从而实现微流量绿色高能单组元推力器稳定工作。微流量绿色高能单组元推力器具有高比冲、绿色无毒、质量轻、可预包装等特点,为微纳卫星轨道机动、快速响应等提供所需的力或力矩,极大的拓展了微纳卫星的应用空间。(The present invention relates to a kind of micrometeor green high-capacity single group member thruster structure, propellant under catalyst action, realizes catalytic decomposition in catalytic bed, further sprays after burning through jet pipe generate thrust in a combustion chamber；Thermal control component is mounted in thrust chamber catalytic bed, is carried out temperature to catalytic bed and is controled and monitored.The invention proposes a kind of micrometeor green high-capacity single group member thruster structures, regulate and control capillary temperature by thermally conductive sheet, capillary heat conductive filament etc., inhibit propellant under micrometeor to generate two phase flow in capillary, realizes micrometeor green high-capacity single group member thruster steady operation.Propellant under micrometeor is inhibited to generate two phase flow in capillary, to realize micrometeor green high-capacity single group member thruster steady operation.Micrometeor green high-capacity single group member thruster have the characteristics that high specific impulse, green non-poisonous, light weight, can be pre-packaged, provide required power or torque for micro-nano satellite orbit maneuver, quick response etc., greatly expand the application space of micro-nano satellite.)

1. a kind of micrometeor green high-capacity single group member thruster structure characterized by comprising miniature electromagnetic valve (1), ejector filler (2), thrust chamber (3) and thermal control component (4)；

The outlet of miniature electromagnetic valve (1) is connect with ejector filler (2) entrance, miniature electromagnetic valve (1) be used for the circulation of propellant into The control of row on-off；Ejector filler (2) outlet is connect with thrust chamber (3) entrance, and ejector filler (2) realizes that the conveying of propellant and barrier push away Conduction from the heat of power room (3) to miniature electromagnetic valve (1) direction and the heat of thrust chamber (3) can be conducted to outside；

Thrust chamber (3) is made of catalytic bed (31), combustion chamber (32) and jet pipe (33), catalysis of the propellant in catalytic bed (31) Under agent effect, catalytic decomposition is realized, spray after further burning in combustion chamber (32) through jet pipe (33) and generate thrust；Thermal control group Part (4) is mounted on thrust chamber (3) catalytic bed (31) outer wall, is carried out temperature to catalytic bed (31) and is controled and monitored.

2. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, which is characterized in that micro electric Magnet valve (1), including an entrance, make-and-break control switch and one outlet, the propellant that entrance is passed through pass through make-and-break control switch After control circulation and blocking, flowed out from outlet.

3. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: ejector filler (2) it is made of flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and capillary heat conductive filament (25), micro electric Magnet valve (1) is mounted on flange frame (21), and for connecting thrust chamber (3), capillary (22) both ends are respectively welded cup (24) On flange frame (21) and cup (24), cup (24) is welded on flange frame (21), and thermally conductive sheet (23) one end is mounted on On cup (24), the connection of thermally conductive sheet (23) other end is external (specifically referring to external satellite support plate), capillary heat conductive filament (25) one end is mounted on capillary (22) close to cup (24) side, and the connection of capillary heat conductive filament (25) other end is external.

4. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: thruster When work, thrust chamber (3) generates high temperature, and high temperature is conducted to ejector filler (2) direction, thermally conductive by thermally conductive sheet (23) and capillary Silk (25) reduces conduction of the heat to capillary (22) and the accumulation on capillary (22) for outside heat derives thruster；Hair The other end of the outlet of one end connection miniature electromagnetic valve (1) of tubule (22), capillary (22) connects thrust chamber (3) entrance, pushes away Enter into agent from one end of capillary (22), after flowing through capillary (22), sprays into thrust chamber from the other end of capillary (22) (3), capillary (22) temperature is regulated and controled by thermally conductive sheet (23), capillary heat conductive filament (25) etc., propellant under micrometeor is inhibited to exist Two phase flow is generated in capillary (22).

5. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: thermally conductive sheet (23) it is made of jointing and thermal conductive belt, is that copper material or silver-colored material, jointing are welded on cup (24), position is hair The outside of tubule (22) and cup (24) welding position, thermal conductive belt one end are fixed on jointing, and the other end is solid by tabletting It is scheduled in the support plate of satellite, increases a cup (24) and external passage of heat, thrust chamber (3) heat is conducted to outer Portion reduces conduction of thrust chamber (3) heat to capillary (22).

6. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: capillary Heat conductive filament (25) is that copper material or silver-colored material, one end are welded on capillary (22), is located proximate to capillary (22) and cup (24) welding position, the other end are fixed in the support plate of satellite by tabletting, form capillary (22) and the thermally conductive of outside is led to Road reduces temperature at capillary (22).

7. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: flange frame Frame (21) is divided into two parts of flange and frame, and flange is L-type structure, is the interconnecting piece of ejector filler (2) and miniature electromagnetic valve (1) Position and thruster and external connection mounting surface, miniature electromagnetic valve (1) is connected by screw on ejector filler (2) flange, and is passed through Aluminum gasket seal；Frame is hollow cylinder lateral opening hole type structure, realizes the heat of barrier thrust chamber (3) to micro electromagnetic The conduction in valve (1) direction.

8. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: thruster It is connect with external connection using screw, thruster and the thermally conductive installation of external satellite, ejector filler (2) heat is conducted to outside, drop In the low-thrust device course of work and thruster shutdown after ejector filler (2), miniature electromagnetic valve (1) temperature.

9. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: cup It (24) include ceramic connecting piece and metal connecting piece, ceramic connecting piece and metal connecting piece are welded to connect, and ceramic connecting piece is band The stepped shaft structure of center speaker hole is welded the one end of capillary (22) in the speaker hole of center, is welded in multi-diameter shaft taper end outside wall surface The jointing of thermally conductive sheet (23) is connect, the inner wall of welding metal connector, metal connecting piece two in multi-diameter shaft butt end outside wall surface End face, the frame of one end welded flange frame (21), the other end weld thrust chamber (3).

10. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: capillary The flow pressure drop control unit that (22) are ejector filler (2) is managed, ejector filler (2) is single capillary (22) spray structure.

Technical field

The present invention relates to a kind of micrometeor green high-capacity single group member thruster structures, belong to Push Technology field.

Background technique

With the development of green high-capacity monopropellant propulsion technology, such as ADN Push Technology, thruster performance is greatly mentioned Rise, but simultaneously because thrust room temperature raising so that thermal environment locating for thruster is more severe, to the design band of thruster Carry out great challenge, at the same time, for low thrust single group member thruster, thruster working flow is small, so that thruster is to thrust The raising of room temperature is more sensitive, will lead to propellant in thruster ejector filler capillary and generates two phase flow, forms gas and block up, cause Thrust is unstable, is unable to satisfy requirement.

Summary of the invention

Present invention solves the technical problem that are as follows: overcome the deficiencies of the prior art and provide a kind of micrometeor green high-capacity list Constituent element thruster structure reduces conduction of the thrust chamber heat to capillary, by leading by ceramics and metal composite structure cup Backing, capillary heat conductive filament etc. increase thrust chamber, capillary and extraneous passage of heat, reduce capillary in the thruster course of work The temperature of pipe inhibits propellant under micrometeor to generate two phase flow in capillary, to realize micrometeor green high-capacity single group member Thruster working thrust is stablized.

A kind of technical solution that the present invention solves are as follows: micrometeor green high-capacity single group member thruster structure, comprising: micro electric Magnet valve (1), ejector filler (2), thrust chamber (3) and thermal control component (4)；The outlet of miniature electromagnetic valve (1) and ejector filler (2) entrance connect It connects, miniature electromagnetic valve (1) is used for the circulation to propellant and carries out on-off control；Ejector filler (2) outlet connects with thrust chamber (3) entrance Connect, ejector filler (2) realize propellant conveying and obstruct thrust chamber (3) conduction from heat to miniature electromagnetic valve (1) direction simultaneously The heat of thrust chamber (3) can be conducted to outside；Thrust chamber (3) is by catalytic bed (31), combustion chamber (32) and jet pipe (33) group At propellant realizes catalytic decomposition under the catalyst action in catalytic bed (31), after further burning in combustion chamber (32) It is sprayed through jet pipe (33) and generates thrust；Thermal control component (4) is mounted on thrust chamber (3) catalytic bed (31) outer wall, to catalytic bed (31) temperature is carried out to control and monitor.

Miniature electromagnetic valve (1), including an entrance, make-and-break control switch and one outlet, the propellant warp that entrance is passed through After crossing make-and-break control switch control circulation and blocking, flowed out from outlet.

Ejector filler (2) is by flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and capillary heat conductive filament (25) it forms, miniature electromagnetic valve (1) is mounted on flange frame (21), and cup (24) is for connecting thrust chamber (3), capillary (22) both ends are respectively welded on flange frame (21) and cup (24), and cup (24) is welded on flange frame (21), thermally conductive Piece (23) one end is mounted on cup (24), and the connection of thermally conductive sheet (23) other end is external (to specifically refer to external satellite support Plate), capillary heat conductive filament (25) one end is mounted on capillary (22) close to cup (24) side, and capillary heat conductive filament (25) is another One end connection is external (specifically referring to external satellite support plate).

When thruster works, thrust chamber (3) generates high temperature, and high temperature conducts to ejector filler (2) direction, passes through thermally conductive sheet (23) And capillary heat conductive filament (25), heat outside heat derives thruster, will be reduced to the conduction of capillary (22) and in capillary (22) accumulation on；The other end connection of the outlet of one end connection miniature electromagnetic valve (1) of capillary (22), capillary (22) pushes away Power room (3) entrance, propellant enters from one end of capillary (22), after flowing through capillary (22), from the another of capillary (22) End sprays into thrust chamber (3), regulates and controls capillary (22) temperature by thermally conductive sheet (23), capillary heat conductive filament (25) etc., inhibits miniflow It measures lower propellant and generates two phase flow in capillary (22).

Thermally conductive sheet (23) is made of jointing and thermal conductive belt, is that copper material or silver-colored material, jointing are welded on cup (24) on, position is the outside of capillary (22) and cup (24) welding position, and thermal conductive belt one end is fixed on jointing, separately One end is fixed in the support plate of satellite by tabletting, increases a cup (24) and external passage of heat, by thrust chamber (3) Heat is conducted to outside, reduces conduction of thrust chamber (3) heat to capillary (22).

Capillary heat conductive filament (25) is that copper material or silver-colored material, one end are welded on capillary (22), is located proximate to capillary Manage (22) and cup (24) welding position, the other end is fixed in the support plate of satellite by tabletting, formed capillary (22) and External passage of heat reduces temperature at capillary (22).

Flange frame (21) is divided into two parts of flange and frame, and flange is L-type structure, is ejector filler (2) and micro electric The connecting portion and thruster and external connection mounting surface of magnet valve (1), miniature electromagnetic valve (1) are connected by screw in ejector filler (2) on flange, and pass through aluminum gasket seal；Frame is hollow cylinder lateral opening hole type structure, realizes barrier thrust chamber (3) Conduction of the heat to miniature electromagnetic valve (1) direction.

Thruster is connect with external connection using screw, thruster and the thermally conductive installation of external satellite, by ejector filler (2) heat Conduction to outside, reduce in the thruster course of work and thruster shutdown after ejector filler (2), miniature electromagnetic valve (1) temperature.

Cup (24) includes ceramic connecting piece and metal connecting piece, and ceramic connecting piece and metal connecting piece are welded to connect, pottery Porcelain connector is the stepped shaft structure with center speaker hole, and the one end of capillary (22) is welded in the speaker hole of center, and multi-diameter shaft is thin The jointing that thermally conductive sheet (23) are welded in outside wall surface is held, the inner wall of welding metal connector in multi-diameter shaft butt end outside wall surface, Metal connecting piece both ends of the surface, the frame of one end welded flange frame (21), the other end weld thrust chamber (3).

Capillary (22) is the flow pressure drop control unit of ejector filler (2), and ejector filler (2) is single capillary (22) spray Structure.

The advantages of the present invention over the prior art are that:

(1) the invention proposes a kind of micrometeor green high-capacity single group member thruster structure, by thermally conductive sheet on ejector filler, Capillary heat conductive filament etc. increases ejector filler, capillary and extraneous passage of heat, reduces capillary in the thruster course of work Temperature.

(2) present invention increases heat transfer resistance of the thrust chamber to capillary by ceramics and metal composite structure cup scheme, Thrust chamber is reduced to conduct to the heat of capillary.

(3) present invention realizes barrier thrust chamber heat and conducts heat to thruster installation by flange frame structure Conduction of the heat to miniature electromagnetic valve direction is weakened in face.

(4) present invention inhibits propellant under micrometeor to generate two phase flow in capillary by regulation capillary temperature, real Existing micrometeor green high-capacity single group member thruster steady operation.

(5) present invention realizes that mounting structure is compact by L-type ejector filler flange and external connection, is suitable for being applied to vertical The micromass culture system of square magnitude micro-nano satellite.

Detailed description of the invention

Fig. 1 is micrometeor green high-capacity single group member thruster structural schematic diagram of the present invention；

Fig. 2 is ejector filler structural schematic diagram；

Fig. 3 is flange circuit theory schematic diagram；

Fig. 4 is cup structural schematic diagram；

Fig. 5 is thrust chamber structural schematic diagram.

Specific embodiment

The present invention relates to a kind of micrometeor green high-capacity single group member thruster structures, including miniature electromagnetic valve (1), ejector filler (2), thrust chamber (3) and thermal control component (4)；Miniature electromagnetic valve (1) outlet is connect with ejector filler (2) entrance, for propellant Circulation carry out on-off management；Ejector filler (2) outlet is connect with thrust chamber (3) entrance, by flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and capillary heat conductive filament (25) composition, ejector filler (2) flange frame (21) realize barrier Conduction of the heat to miniature electromagnetic valve (1) direction in thrust chamber (3) course of work, thermally conductive sheet (23) reduce thrust chamber (3) to hair The heat transfer of tubule (22), capillary heat conductive filament (25) are mounted on capillary (22) close to thrust chamber (3) side, reduce capillary (22) temperature, capillary (22) realize the conveying of propellant；Thrust chamber (3) is by catalytic bed (31), combustion chamber (32) and jet pipe (33) it forms, propellant under catalyst action, is realized catalytic decomposition, further fired in combustion chamber (32) in catalytic bed (31) It is sprayed after burning through jet pipe (33) and generates thrust；Thermal control component (4) is mounted in thrust chamber (3) catalytic bed (31), to catalytic bed (31) temperature is carried out to control and monitor.The invention proposes a kind of micrometeor green high-capacity single group member thruster structures, by leading Backing (23), capillary heat conductive filament (25) etc. regulate and control capillary (22) temperature, and propellant is in capillary (22) under inhibition micrometeor Middle generation two phase flow realizes micrometeor green high-capacity single group member thruster steady operation.

A kind of micrometeor green high-capacity single group member thruster structure of the invention, inhibit micrometeor under propellant in capillary Middle generation two phase flow, to realize micrometeor green high-capacity single group member thruster steady operation.Micrometeor green high-capacity single group member Thruster have the characteristics that high specific impulse, green non-poisonous, light weight, can be pre-packaged, be micro-nano satellite orbit maneuver, quick response etc. Power or torque needed for providing, greatly expand the application space of micro-nano satellite.

As shown in Figure 1, a kind of micrometeor green high-capacity single group member thruster structure, comprising: miniature electromagnetic valve (1), spray Device (2), thrust chamber (3) and thermal control component (4).Miniature electromagnetic valve (1) carries out on-off control, packet for the circulation to propellant Include an entrance, make-and-break control switch and one outlet, the propellant that entrance is passed through by make-and-break control switch control circulation and It after blocking, is flowed out from outlet, the outlet of miniature electromagnetic valve (1) is connect with ejector filler (2) entrance screw, aluminium backing sealing.

As shown in Fig. 2, ejector filler (2) is by flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and hair Tubule heat conductive filament (25) composition, ejector filler (2) outlet are connect with thrust chamber (3) entrance electron beam welding, and ejector filler (2), which is realized, to be promoted The conveying of agent and the heat of thrust chamber (3) is obstructed to the conduction in miniature electromagnetic valve (1) direction and can be by the heat of thrust chamber (3) It conducts to outside.

Flange frame (21), as shown in figure 3, being divided into two parts of flange and frame, flange is L-type structure, is ejector filler (2) with the connecting portion of miniature electromagnetic valve (1) and thruster and external connection mounting surface, the outlet of miniature electromagnetic valve (1) passes through Screw is connected on ejector filler (2) flange, and by aluminum gasket seal, thruster is connect using screw with external connection, pushed away Power device and the thermally conductive installation of external satellite conduct ejector filler (2) heat to outside, reduce in the thruster course of work and thruster Ejector filler (2), miniature electromagnetic valve (1) temperature after shutdown.Frame is hollow cylinder lateral opening hole type structure, realizes barrier thrust Conduction of the heat of room (3) to miniature electromagnetic valve (1) direction.

Cup (24), as shown in figure 4, for ejector filler (2) electron beam welding connection thrust chamber (3), including ceramic connecting piece And metal connecting piece, on the outside, for ceramic connecting piece in inside, ceramic connecting piece is the ladder with center speaker hole to metal connecting piece Axle construction, the inner wall of welding metal connector, metal connecting piece both ends of the surface, one end welded flange in multi-diameter shaft butt end outside wall surface The frame of frame (21), other end electron beam welding thrust chamber (3) weld capillary (22) in the speaker hole of ceramic connecting piece center One end, capillary (22) be ejector filler (2) flow pressure drop control unit, ejector filler (2) be single capillary (22) spray Structure, capillary (22) other end are welded on flange frame (21), are welded and are led in ceramic connecting piece multi-diameter shaft taper end outside wall surface The jointing of backing (23), thermally conductive sheet (23) are made of jointing and thermal conductive belt, are copper material or silver-colored material, jointing It is welded on cup (24), position is the outside of capillary (22) and cup (24) welding position, and thermal conductive belt one end is fixed on company On connector, the other end is fixed in the support plate of satellite by tabletting, increases a cup (24) and external passage of heat, Thrust chamber (3) heat is conducted to outside, conduction of thrust chamber (3) heat to capillary (22) is reduced.

Capillary heat conductive filament (25) are welded on capillary (22), capillary heat conductive filament (25) is copper material or silver-colored material, one End is welded on capillary (22), is located proximate to capillary (22) and cup (24) welding position, the other end is fixed by tabletting In the support plate of satellite, capillary (22) and external passage of heat are formed, reduce temperature at capillary (22).

Thrust chamber (3) electron beam welding is connected on ejector filler (2) cup (24), as shown in figure 5, by catalytic bed (31), burning Room (32) and jet pipe (33) composition, combustion chamber (32) and jet pipe (33) be structure as a whole, catalytic bed (31) and combustion chamber (32) and Jet pipe (33) electron beam welding, in catalytic bed (31) after loading catalyst with ejector filler (2) cup (24) electron beam welding.It promotes Agent realizes catalytic decomposition under the catalyst action in catalytic bed (31), through jet pipe after further burning in combustion chamber (32) (33) it sprays and generates thrust.

Thermal control component (4) is mounted on thrust chamber (3) catalytic bed (31) outer wall, to catalytic bed (31) carry out temperature control and Monitoring.

When thruster works, thrust chamber (3) generates high temperature, and high temperature conducts to ejector filler (2) direction, passes through thermally conductive sheet (23) And capillary heat conductive filament (25), heat outside heat derives thruster, will be reduced to the conduction of capillary (22) and in capillary (22) accumulation on.The heat convection power P of propellant in capillary (22)_qThe heat conducted with thrust chamber (3) to ejector filler (2) Power P_t, thermal power P derived from thermally conductive sheet (23)_d, thermal power P derived from capillary heat conductive filament (25)_mIt preferably satisfies such as ShiShimonoseki System: P_q> P_t-P_d-P_m.Wherein, P_m=f_m*C_p*T_m, f_m* propellant flow rate, C are indicated_pFor the specific heat capacity of propellant, T_mFor capillary The variation mean temperature difference of propellant at 3~5mm of downstream.

The other end of the outlet of one end connection miniature electromagnetic valve (1) of capillary (22), capillary (22) connects thrust chamber (3) entrance, propellant enters from one end of capillary (22), after flowing through capillary (22), sprays from the other end of capillary (22) Enter thrust chamber (3), capillary (22) temperature is regulated and controled by thermally conductive sheet (23), capillary heat conductive filament (25) etc., is inhibited under micrometeor Propellant generates two phase flow in capillary (22).

The heat convection power P of propellant in capillary (22)_qThe thermal power conducted with thrust chamber (3) to ejector filler (2) P_t, thermal power P derived from thermally conductive sheet (23)_d, thermal power P derived from capillary heat conductive filament (25)_mThe matching for needing to have certain Property, which is suitable for the low energy flow characteristic propellants such as hydrazine, is also applied for ADN, HAN base green high-capacity propellant.Preferred embodiment Are as follows: when propellant is ADN base propellant, if P_tFor 20W, flow f_mWhen for 100mg/s, heat convection power is 14W, it is desirable that Radiator structure heat-conducting section product >=2.5mm², capillary inner diameter≤0.3mm, thermally conductive power P_d+P_d>=6W, ensure in small flow, Do not occur two phase flow in capillary, to ensure T_mLower than a certain range, then thermally conductive power is required further to be promoted.For heat dissipation Structure and power determination need further to be determined by certain experiment.Micrometeor green designed by the invention is high Energy single group member thruster structure inhibits propellant in capillary to generate two phase flow, realizes micrometeor green high-capacity single group member thrust Device working thrust is stablized.

The invention proposes a kind of micrometeor green high-capacity single group member thruster structures, pass through thermally conductive sheet, hair on ejector filler Tubule heat conductive filament etc. increases ejector filler, capillary and extraneous passage of heat, reduces the temperature of capillary in the thruster course of work Degree.By ceramics and metal composite structure cup scheme, increase heat transfer resistance of the thrust chamber to capillary, reduces thrust chamber to hair The heat of tubule conducts.By flange frame structure, realizes barrier thrust chamber heat and conducts heat to thruster mounting surface, Weaken conduction of the heat to miniature electromagnetic valve direction.

The present invention is inhibited propellant under micrometeor to generate two phase flow in capillary, is realized by regulation capillary temperature Micrometeor green high-capacity single group member thruster steady operation.By L-type ejector filler flange and external connection, realize that mounting structure is tight It gathers, suitable for being applied to the micromass culture system of cube magnitude micro-nano satellite.

The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.