阅读说明：本技术 用于微小卫星离轨的动力系统及动力推动方法 (Power system and power pushing method for micro satellite derailing ) 是由 孙夺 王明哲 郭利明 刘业奎 李文鹏 申帅帅 余鹏 杨海峰 于 2021-09-02 设计创作，主要内容包括：用于微小卫星离轨的动力系统及动力推动方法。本发明包括：高压气瓶,用于容纳用于冷气推进的气体；充气阀与所述高压气瓶连接,用于为所述高压气瓶充气；高压压力传感器与高压气瓶连接,用于检测高压气瓶内压力；高压电磁阀与高压气瓶连接；所述减压阀安装在所述高压电磁阀、离轨发动机之间；低压压力传感器与离轨发动机入口连通,用于检测离轨发动机入口压力。本发明离轨动力系统具有结构简单,重量轻,成本低和可靠性高的特点,可整机交付,在微小卫星离轨领域具备十分广阔的应用空间。(A power system and a power pushing method for micro satellite derailment are provided. The invention comprises the following steps: a high pressure gas cylinder for containing gas for cold gas propulsion; the inflation valve is connected with the high-pressure gas cylinder and used for inflating the high-pressure gas cylinder; the high-pressure sensor is connected with the high-pressure gas cylinder and used for detecting the pressure in the high-pressure gas cylinder; the high-pressure electromagnetic valve is connected with the high-pressure gas cylinder; the pressure reducing valve is arranged between the high-pressure electromagnetic valve and the off-rail engine; the low-pressure sensor is communicated with an inlet of the off-rail engine and used for detecting the pressure of the inlet of the off-rail engine. The off-orbit power system has the characteristics of simple structure, light weight, low cost and high reliability, can be delivered as a whole machine, and has very wide application space in the field of off-orbit of microsatellites.)

1. A power system for microsatellite derailment, comprising:

a high-pressure gas cylinder (1) for receiving gas for cold gas propulsion;

the inflation valve (2) is connected with the high-pressure gas cylinder (1) and is used for inflating the high-pressure gas cylinder (1);

the high-pressure sensor (3) is connected with the high-pressure gas cylinder (1) and used for detecting the pressure in the high-pressure gas cylinder;

the high-pressure electromagnetic valve (4), the said high-pressure electromagnetic valve (4) is connected with high-pressure gas cylinder;

the pressure reducing valve (5), the said pressure reducing valve (5) is installed between said high-pressure electromagnetic valve (4) and off-rail engine (7);

the low-pressure sensor (6) is communicated with an inlet of the off-rail engine (7) and used for detecting the inlet pressure of the off-rail engine (7).

2. The power system for microsatellite derailment according to claim 1, wherein the derailment engine is a cold air propulsion engine which consists of a solenoid valve and a thrust chamber, the high pressure solenoid valve (4) controls cold air to enter the thrust chamber, the high pressure solenoid valve (4) is opened, and the high pressure cold air is sprayed out to generate thrust.

3. The power system for the micro satellite off-orbit according to claim 1, wherein the high-pressure gas cylinder (1) is a carbon fiber coated composite gas cylinder, and the highest pressure is not more than 35 MPa.

4. The power system for the micro satellite derailment according to claim 1, wherein the high-pressure solenoid valve (4) is used for controlling the power system to be opened, and after the high-pressure solenoid valve (4) is opened, high-pressure gas enters the derailment engine (7) through the high-pressure solenoid valve (4).

5. A power driving method for a power system for the micro satellite off-orbit according to any one of claims 1 to 4, characterized in that high-pressure gas is charged into a high-pressure gas cylinder (1) through a charging valve (2), when an off-orbit engine (7) needs to work, a high-pressure electromagnetic valve (4) is opened, and the high-pressure gas enters the electromagnetic valve of the off-orbit engine (7), and the electromagnetic valve of the engine is switched on and off in real time to control the off-orbit engine to work in real time according to the satellite task requirement.

The technical field is as follows:

the invention relates to the technical field of space vehicles, in particular to a power system and a power pushing method for microsatellite derailment.

Background art:

with the vigorous development of commercial aerospace, microsatellites are increasingly applied to the fields of scientific experiments, communication, earth observation and the like, and the ratio that commercial aerospace companies emit thousands or even tens of thousands of satellites in planning years at home and abroad is that governments in various countries vigorously promote the application of the microsatellites in various fields. With the increase of the number of the micro satellites, space resources become more and more valuable, and in order to make full and reasonable use of the scarce space resources, the timely off-orbit of the waste satellites is particularly important.

Because the microsatellite has small volume and low cost, under the condition that the total impulse meets the requirement, the off-orbit power system of the microsatellite has the characteristics of small volume, light weight, reliable system, convenient installation and maintenance, low price and the like. At present, no mature microsatellite off-orbit power system exists at home and abroad.

The invention content is as follows:

the invention aims to provide a power system and a power pushing method for the off-orbit of a microsatellite, wherein the system has the characteristics of small volume, light weight, reliable system, convenient installation and maintenance and low cost, and solves the problem of the lack of the conventional off-orbit power system of the microsatellite.

The above purpose is realized by the following technical scheme:

a power system for microsatellite off-orbit comprising:

a high pressure gas cylinder for containing gas for cold gas propulsion;

the inflation valve is connected with the high-pressure gas cylinder and used for inflating the high-pressure gas cylinder;

the high-pressure sensor is connected with the high-pressure gas cylinder and used for detecting the pressure in the high-pressure gas cylinder;

the high-pressure electromagnetic valve is connected with the high-pressure gas cylinder;

the pressure reducing valve is arranged between the high-pressure electromagnetic valve and the off-rail engine;

and the low-pressure sensor is communicated with an inlet of the off-rail engine and is used for detecting the pressure of the inlet of the off-rail engine.

The power system for the microsatellite derailment is characterized in that the derailment engine is a cold air propulsion engine which consists of an electromagnetic valve and a thrust chamber, the high-pressure electromagnetic valve controls cold air to enter the thrust chamber, the high-pressure electromagnetic valve is opened, and the high-pressure cold air is sprayed out to generate thrust.

The power system for the off-orbit of the microsatellite is characterized in that the high-pressure gas cylinder is a carbon fiber coated composite gas cylinder, and the highest pressure is not more than 35 MPa.

The power system for the micro satellite to leave the orbit is characterized in that the high-pressure electromagnetic valve is used for controlling the power system to be opened, and high-pressure gas enters the off-orbit engine through the high-pressure electromagnetic valve after the high-pressure electromagnetic valve is opened.

A power driving method by using the power system for the micro satellite off-orbit according to any one of claims 1 to 4, wherein high-pressure gas is filled into a high-pressure gas cylinder through an inflation valve, when the off-orbit engine needs to work, a high-pressure electromagnetic valve is opened, and the high-pressure gas enters the electromagnetic valve of the off-orbit engine, and the electromagnetic valve of the engine is opened and closed in real time to control the off-orbit engine to work in real time according to the task requirement of the satellite.

The invention has the beneficial effects that:

the off-orbit power system only consists of the gas cylinder, the off-orbit engine and the valves, is simple and reliable, has light weight and lower cost, and solves the problem that the microsatellite is not provided with a mature off-orbit engine at the present stage.

Description of the drawings:

FIG. 1 is a schematic structural diagram of the present invention.

Wherein the figures include the following reference numerals:

1. a high pressure gas cylinder;

2. an inflation valve;

3. a high pressure sensor;

4. a high-pressure solenoid valve;

5. a pressure reducing valve;

6. a low pressure sensor;

7. an off-track engine.

The specific implementation mode is as follows:

in order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

The invention provides a power system for micro satellite derailment, as shown in fig. 1, comprising: the device comprises a high-pressure gas cylinder 1, an inflation valve 2, a high-pressure sensor 3, a high-pressure electromagnetic valve 4, a pressure reducing valve 5, a low-pressure sensor 6 and an off-rail engine 7.

In the embodiment, the high-pressure gas cylinder 1 is a carbon fiber-coated composite gas cylinder, and the pressure is 20 MPa; the gas in the high-pressure gas cylinder 1 is nitrogen (N)₂) Laughing gas (N)₂O) or other gases suitable for cold gas propulsion.

In this embodiment, the charging valve 2 communicates with the high-pressure gas cylinder for charging the high-pressure gas cylinder.

In the present embodiment, the high-pressure sensor 3 communicates with the high-pressure gas cylinder for detecting the pressure in the high-pressure gas cylinder.

In this embodiment, the high-pressure solenoid valve 4 is used to control the power system to be opened, the high-pressure solenoid valve 4 is opened, and high-pressure gas can enter the front of the off-rail engine solenoid valve through the high-pressure solenoid valve 4.

In this embodiment, the pressure reducing valve 5 is used to reduce the pressure of the high pressure gas to the pressure required by the off-rail engine.

In this embodiment, the low pressure sensor 6 is in communication with the derailing engine inlet 7 for sensing the derailing engine 7 inlet pressure.

In bookIn the embodiment, the off-track engine 7 is N₂The cold air propulsion engine consists of an electromagnetic valve and a thrust chamber, wherein the electromagnetic valve controls cold air to enter the thrust chamber, the electromagnetic valve is opened, and high-pressure cold air is sprayed out to generate thrust.

In the embodiment, high-pressure gas is filled into the high-pressure gas bottle 1 through the inflation valve 2, when the off-orbit engine 7 needs to work, the high-pressure electromagnetic valve 4 is opened, and the high-pressure gas enters the electromagnetic valve of the off-orbit engine 7, and the electromagnetic valve of the engine is switched on and off in real time to control the off-orbit engine to work in real time according to the satellite task requirement.

From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:

by applying the technical scheme of the invention, the off-rail power system only consists of the gas cylinder, the off-rail engine and a plurality of valves, and is simple and reliable, light in weight and low in cost. The problem that the microsatellite is not provided with a mature off-orbit engine at the present stage is solved.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.