CN108190048A - A kind of micromodule butane propulsion system structure and propulsion method - Google Patents

Abstract

A micro-modular butane propulsion system structure and propulsion method, the structure includes a module main structure, a discharge valve, a heating system, and a solenoid valve; the heating system is located at the center of the module main structure, and is used to determine the state and heat the propellant ;Solenoid valves are arranged side by side on the upper part of the main structure of the module, and are used for on-off management of the flow of propellant; Realize the charging and discharging of propellant. The invention adopts the concept of modular design to highly integrate each stand-alone in the traditional propulsion system, which is different from the split distribution structure of the stand-alone in the traditional propulsion system, and has the advantages of high integration, small size, light weight, convenient installation, rapid mass production, Low cost and other characteristics can meet the needs of micro-nano satellites for micro-propulsion systems.

Description

Structure and propulsion method of a micro-modular butane propulsion system

technical field

The invention relates to a micro modular butane propulsion system structure and a propulsion method.

Background technique

Recently, micro-nano satellites have risen rapidly, and in the future global satellite market, micro-nano satellites will have a clear advantage. Compared with traditional large satellites, micro-nano satellites have the characteristics of small size, light weight, quick response to user needs, short development cycle, low cost, and short service life. They have the ability to quickly assemble, test, and form space systems in batches. It is the future trend of military space technology to meet the temporary space mission requirements more quickly, and more importantly, they can complete the tasks of large satellites in the past by forming a distributed constellation. According to the characteristics of micro-nano satellites, the micro-propulsion system is required to have the characteristics of modularization, small size, and light weight. However, due to the different design ideas and processing technologies of the traditional propulsion system, it is difficult to realize the miniaturization of the propulsion system.

In order to meet the needs of micro-nano satellites for the propulsion system, the present invention proposes a butane liquefied gas micro-propulsion module. This micro-propulsion module is different from the split distribution structure of the traditional propulsion system, and has high integration, modularization, and low cost. , pre-packaged features, can meet the needs of micro-nano-satellites for micro-propulsion systems.

Chinese patent "Miniature Liquid Fuel Propulsion System for Micro-Nano Satellites" (Patent No.: CN200810220280.1) "Micro-Liquid Fuel Propulsion System for Micro-Nano Satellites" is a miniature design of traditional propulsion systems, including There are pressurized gas generators, micro-propellers, fuel storage tanks and pipelines to provide liquid fuel for micro-propulsion, all structures are distributed on a plane, and the volume is large, which is difficult to meet the needs of micro-nano satellites for the propulsion system. Size and weight requirements.

Chinese patent (patent number: CN201420562343.2) "a high-pressure gas propulsion system for micro-satellites" is characterized in that it includes: a high-pressure gas storage cylinder, which is a spherical aluminum alloy inner tank, and is placed outside the aluminum alloy inner tank Winding carbon fiber; a high-pressure self-locking cylinder valve, installed on the mouth of the high-pressure gas storage cylinder, used to control the entry and exit of gas in the high-pressure gas storage cylinder. This patent requires gas compression storage, and the system pressure is high, so the volume and weight of the storage tank are large, which cannot meet the volume and weight requirements of the micro-nano satellite for the propulsion system.

Contents of the invention

The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a structure of a micro-modular butane propulsion system. Tanks, gasification chambers and pipelines are highly integrated, and the space layout is compact and novel, realizing the modularization and miniaturization of the structure, and greatly reducing the volume of the micro-propulsion system on the premise of ensuring that the performance meets the needs of micro-nano satellites and weight.

The technical solution adopted in the present invention is: a micro-modularized butane propulsion system structure, including: a module main structure, a discharge valve, a heating system, and a solenoid valve; the heating system is located at the center of the module main structure and is used for The state of the propellant is determined and heated; the solenoid valve is arranged side by side on the upper part of the main structure of the module, and is used for on-off management of the circulation of the propellant; Connected to realize filling and discharging of propellant through filling and discharging valve.

It also includes a metal auxiliary bracket and a solenoid valve mounting bracket; the two ends of the solenoid valve are fixed by the solenoid valve mounting bracket, and then the solenoid valve bracket, the metal auxiliary bracket and the main structure of the module are connected and fixed by screws.

The main structure of the module is made of non-metallic materials through 3D printing; the main structure of the module is a cuboid structure, and the inside includes a storage tank, a gasification chamber, a circulation pipe and a nozzle structure.

The heating system includes a heater, a temperature sensor, and a pressure sensor; the heater is used to heat the propellant flowing into the gasification chamber, and the temperature sensor and pressure sensor are used to monitor the temperature and pressure of the propellant in the gasification chamber.

The heater includes a main heater and a sub-heater; the main heater and the sub-heater are located in the circulation pipeline and the vaporization chamber respectively; the main heater and the sub-heater are composed of a heat capacity and a heating wire, and the heating wire is wound on In terms of heat capacity, heat capacity is generally made of porous media materials

Metal auxiliary brackets are placed in the grooves on both sides of the module main structure, and the screws are passed through the solenoid valve bracket, the module main structure and the metal auxiliary bracket in turn to realize the connection between the solenoid valve bracket and the module main structure.

The internal storage tank of the main structure of the module is an annular main structure, and the gasification chamber is located in the middle of the storage tank, which is used to completely vaporize the liquid propellant or gas-liquid mixed propellant flowing out of the storage tank. The circulation pipe is located in the storage tank The gap between the gasification chamber and the gasification chamber is a propellant circulation channel. The number of nozzles can be N according to requirements, and their distribution positions can also be arranged according to requirements. The gaseous propellant is ejected through the nozzles to generate thrust.

There are N+1 circulation channels in total, one of which is connected to the storage tank and the gasification chamber, and the remaining N channels are connected to the gasification chamber and the nozzle.

A total of N+1 solenoid valves are arranged side by side on the main structure of the module, and both ends are fixed by solenoid valve brackets.

A micro-modular butane propulsion method, the steps are as follows:

1) Install the solenoid valve on the main structure through the metal auxiliary bracket and the solenoid valve mounting bracket;

2) Fill the propellant into the storage tank through the filling and discharging valve;

3) The solenoid valve located between the storage tank and the gasification chamber is in an open state, and the propellant can enter the gasification chamber through the flow pipe;

4) Keep the heater in the gasification chamber in working condition, and the heating system starts to work at the same time;

5) The electromagnetic valve located between the gasification chamber and the nozzle is in an open state, and the heated gaseous propellant is ejected from the nozzle.

The advantage of the present invention compared with prior art is:

(1) The modular structure of the miniature propulsion system proposed by the present invention completes the structure of the storage tank, gasification chamber, pipeline, and thruster through 3D printing technology, which breaks through the limitations of the traditional processing technology on the structural layout, and realizes various The single machine is highly integrated, no special pipeline connection is required, the space layout is compact and novel, the storage tank is designed as a circular structure, the middle of the storage tank is a gasification chamber, and the pipelines are distributed in the gap part, making full use of the space to realize the Connection. This feature greatly reduces the volume and weight of the micro propulsion system.

(2) In the present invention, the heater is directly arranged in the pipeline and the gasification chamber. The heater can heat the propellant in two ways: convective heat exchange and conduction heat exchange. Under the premise of limited space and heating power, the heating rate can be greatly improved. heating efficiency.

(3) In the present invention, the mounting bracket of the electromagnetic valve and the discharge valve are connected with the main body of the non-metallic module by screws. In order to improve the reliability and lifespan of the connection between the metal screw and the non-metallic material, the structure of the metal auxiliary bracket is designed. The structure of the metal auxiliary bracket is embedded in the groove of the main structure of the non-metallic module, so that the direct connection between the metal screw and the metal auxiliary bracket is realized, and the reliability and life of the connection are improved.

Description of drawings

Fig. 1 is the structural diagram of miniature modular butane propulsion system of the present invention;

Fig. 2 is a schematic diagram of the main structure of the non-metallic 3D printing module of the present invention;

Fig. 3 is the structural representation of storage tank of the present invention;

Fig. 4 is a schematic structural diagram of the heater of the present invention.

Detailed ways

As shown in Fig. 1, a kind of micro-butane propulsion system structure of the present invention comprises: module body structure 1, add discharge valve 2, heating system, electromagnetic valve 8; Heating system is positioned at the central position of module body structure 1, is used for The state of the propellant is determined and heated; the solenoid valve 8 is arranged side by side on the upper part of the module main structure 1 for on-off management of the flow of the propellant; the discharge valve 2 is located in the groove on one side of the module main structure 1, and through The screw is connected with the module main structure 1, and the filling and discharging of the propellant is realized through the filling and discharging valve 2.

It also includes a metal auxiliary bracket 6 and a solenoid valve mounting bracket 7; the two ends of the solenoid valve 8 are fixed by the solenoid valve mounting bracket 7, and then the solenoid valve bracket 7 and the metal auxiliary bracket 6 are connected and fixed to the module main structure 1 by screws.

The module main structure 1 is made of non-metallic materials through 3D printing; the module main structure 1 is a rectangular parallelepiped structure, which includes a storage tank 9, a gasification chamber 10, a circulation pipe 11 and a nozzle 12 structure.

The heating system includes a heater 3, a temperature sensor 4, and a pressure sensor 5; wherein the heater 3 is used to heat the propellant flowing into the gasification chamber 10, and the temperature sensor 4 and the pressure sensor 5 are used to monitor the propellant in the gasification chamber 10. Propellant temperature and pressure values.

The heater 3 includes a main heater and a sub-heater; the main heater and the sub-heater are respectively located in the circulation pipeline 11 and the vaporization chamber 10; the main heater and the sub-heater are both composed of a heat capacity 13 and a heating wire 14 , the heating wire 14 is wound on the heat capacity 13, and the heat capacity 13 is generally made of a porous dielectric material

The metal auxiliary bracket 6 is placed in the grooves on both sides of the module main structure 1, and the screws are passed through the solenoid valve bracket 7, the module main structure 1 and the metal auxiliary bracket 6 in order to realize the connection between the solenoid valve bracket 7 and the module main structure .

The internal storage tank 9 of the module main structure 1 is an annular main structure, and the gasification chamber 10 is located at the annular middle position of the storage tank 9, and is used to completely vaporize the liquid propellant or the gas-liquid mixed propellant flowing out of the storage tank, and circulate The pipeline 11 is located in the gap between the storage tank 9 and the gasification chamber 10, and is a propellant circulation channel. The number of nozzles 12 can be N according to requirements, and their distribution positions can also be arranged according to requirements. The gaseous propellant is sprayed out through the nozzles 12 , generating thrust.

There are N+1 circulation channels 11 in total, one of which is connected to the storage tank 9 and the gasification chamber 10 , and the remaining N channels are connected to the gasification chamber 10 and the nozzle 12 .

The solenoid valves 8 are N+1 in total, arranged side by side on the module main body structure 1 , and the two ends are fixed by the solenoid valve brackets 7 .

A kind of miniature modular butane propulsion method of the present invention is characterized in that the steps are as follows:

1. Install the solenoid valve 8 on the main structure 1 through the metal auxiliary bracket 6 and the solenoid valve mounting bracket 7;

2. Fill the propellant into the storage tank 9 through the filling and discharging valve 2;

3. The solenoid valve 8 located between the storage tank 9 and the gasification chamber 10 is in an open state, and the propellant can enter the gasification chamber 10 through the flow pipe 11;

4. Put the heater 3 in the vaporization chamber 10 in the working state, and the heating system also starts to work at the same time;

5. The electromagnetic valve 8 located between the gasification chamber 10 and the nozzle 12 is in an open state, and the heated gaseous propellant is sprayed out from the nozzle 12 .

By adopting the structure of the present invention, the mass and volume of the entire propulsion system can be greatly reduced, thereby meeting the strict requirements of the micro-nano satellite on the propulsion system. The butane propellant is stored in a liquid form, and the liquid propellant is vaporized by a heating and vaporization device, and then sprayed through a nozzle to generate thrust.

Parts not described in detail in the present invention belong to the well-known technology of those skilled in the art.

Claims (10)

1. a kind of micromodule butane propulsion system structure, which is characterized in that including：Module bodies structure (1) plus valve (2), heating system, solenoid valve (8)；Heating system is located at the center of module bodies structure (1), for being carried out to propellant State is determined and is heated；Solenoid valve (8) arranged in parallel on the top of module bodies structure (1), for the circulation to propellant into Row break-make management；Valve (2) is added to pass through screw and module bodies structure (1) in the side groove of module bodies structure (1) Connection, by the way that valve (2) is added to realize the filling and discharge of propellant.

2. a kind of micromodule butane propulsion system structure according to claim 1, it is characterised in that：Further include metal Auxiliary stand (6), solenoid valve mounting bracket (7)；Solenoid valve (8) both ends are fixed, then lead to by solenoid valve mounting bracket (7) It crosses screw and solenoid valve bracket (7), metal auxiliary stand (6) is connect fixation with module bodies structure (1).

3. a kind of micromodule butane propulsion system structure according to claim 1, it is characterised in that：The module master Body structure (1) is formed using nonmetallic materials by 3D printing；Module bodies structure (1) shape is a rectangular parallelepiped structure, interior Portion includes tank (9), vaporizer (10), circulation duct (11) and jet pipe (12) structure.

4. a kind of micromodule butane propulsion system structure according to claim 1, it is characterised in that：The heating system System includes heater (3), temperature sensor (4), pressure sensor (5)；Wherein heater (3) will be for will flow into vaporizer (10) Propellant heated, temperature sensor (4) and pressure sensor (5) are for monitoring the temperature of propellant in vaporizer (10) And pressure value.

5. a kind of micromodule butane propulsion system structure according to claim 1, it is characterised in that：The heater (3) including primary heater and secondary heater；Primary heater and secondary heater are located at flow pipe (11) and vaporizer (10) respectively In；Primary heater and secondary heater are made of thermal capacitance (13) and heater strip (14), and heater strip (14) is wrapped in thermal capacitance (13), Thermal capacitance (13) is generally made of porous media material.

6. a kind of micromodule butane propulsion system structure according to claim 2, it is characterised in that：The module master Metal auxiliary stand (6) is placed in the grooves on two sides of body structure (1), screw is sequentially passed through into solenoid valve bracket (7), module bodies Structure (1) and metal auxiliary stand (6) are, it can be achieved that solenoid valve bracket (7) and the connection of module bodies structure.

7. according to a kind of arbitrary micromodule butane propulsion system structures of claim 1-6, it is characterised in that：It is described The internal tank (9) of module bodies structure (1) is annular body structure, vaporizer (10) positioned at the annular centre position of tank (9), It is used to implement and the liquid propellant or gas-liquid mixed propellant that tank flows out is gasified totally, circulation duct (11) is positioned at tank (9) and the gap of vaporizer (10), it is propellant circulation passage, the quantity of jet pipe (12) can be N number of according to demand, be distributed position Putting can also arrange according to demand, and gaseous propellant is sprayed by jet pipe (12), generate thrust.

8. a kind of micromodule butane propulsion system structure according to claim 1-6, it is characterised in that：The circulation The common N+1 items of pipeline (11), wherein 1 connection tank (9) and vaporizer (10), remaining N channel connection vaporizer (10) and spray It manages (12).

9. a kind of micromodule butane propulsion system structure according to claim 8, it is characterised in that：The solenoid valve (8) common N+1, for arranged in parallel above module bodies structure (1), both ends are fixed by solenoid valve bracket (7).

10. a kind of micromodule butane propulsion method, it is characterised in that step is as follows：

1) solenoid valve (8) is installed to by metal auxiliary stand (6), solenoid valve mounting bracket (7) in agent structure (1)；

2) by propellant by the way that valve (2) is added to be filled into tank (9)；

3) by the solenoid valve (8) between tank (9) and vaporizer (10) in open state, propellant passes through circulation duct (11), vaporizer (10) can be entered；

4) it is the heater (3) in vaporizer (10) is in running order, while heating system also begins to work；

5) gaseous propellant of the solenoid valve (8) after open state, heating that will be between vaporizer (10) and jet pipe (12) It is sprayed by jet pipe (12).