CN212313906U

CN212313906U - Modularized single-component propulsion system suitable for spacecraft

Info

Publication number: CN212313906U
Application number: CN202020871059.9U
Authority: CN
Inventors: 万美; 刘慧�
Original assignee: Beijing Yuhang Tianchi Power Technology Co ltd
Current assignee: Aerospace Science and Technology Co.,Ltd. (Wenzhou)
Priority date: 2020-05-22
Filing date: 2020-05-22
Publication date: 2021-01-08
Anticipated expiration: 2030-05-22

Abstract

The utility model discloses a modularization single unit propulsion system suitable for spacecraft, this modularization single unit propulsion system include the installation frame, the storage tank, the filter, the self-locking valve, pressure sensor, the engine, gas adds row valve and liquid adds row valve. The utility model provides a modularization single unit propulsion system suitable for spacecraft can provide the track control function for the spacecraft, and has the redundant design, and each part technical maturity, simple structure, reliability are high, the stable performance, longe-lived, the cost is controllable. The modularized design with the propellant is adopted, the modularized design is suitable for hundred-kilogram-class spacecrafts, only a mounting interface and an electrical interface are required to be reserved in the whole spacecraft, the operation is convenient, the applicability is strong, the dry weight of the whole system is not more than 6.2 kilograms, the full load is not more than 13 kilograms, the overall dimension is not more than 300X280X570mm, and the speed increment of 80m/s can be realized for the spacecraft with the initial mass of 200 kg.

Description

Modularized single-component propulsion system suitable for spacecraft

Technical Field

The utility model relates to an aerospace field especially relates to a modularization single component propulsion system suitable for spacecraft.

Background

The single-unit propulsion system refers to a propulsion system using a single-unit propellant as a working medium. In the system, propellant stored in a storage tank is extruded by high-pressure gas and discharged out of an outlet of the storage tank, enters a catalyst bed of an engine under the action of opening and closing of a valve, is catalytically decomposed into high-temperature fuel gas under the high-temperature condition, and is sprayed out of a spray pipe to generate reaction force so as to control the posture and orbital motion of a spacecraft. The common unit propulsion system has a complex structure and is only suitable for satellites with smaller weight grade, the self weight of the unit propulsion system is also larger, the cost is also high, and the popularization and the use are not facilitated.

To this end, a modular monopropellant propulsion system suitable for spacecraft is proposed. The propulsion system can provide a track control function for the spacecraft, has a redundant design, and has mature technology of each part, simple structure, high reliability, stable performance, long service life and controllable cost.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a modularization single unit propulsion system suitable for spacecraft to overcome the installation degree of difficulty and the maintenance degree of difficulty of equipment in construction and production process, reduce investment cost and manufacturing cost, thereby effectual improvement industrial production rate and the stability of product quality, with the problem of proposing in solving above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: a modular, single-unit propulsion system for a spacecraft includes a mounting frame, a tank, a filter, a latching valve, a pressure sensor, an engine, a gas and liquid charging and discharging valve.

Preferably, the gas charging and discharging valve and the liquid charging and discharging valve are arranged at the bottom of the storage tank.

Preferably, the pressure sensor is connected between the tank and the latching valve for measuring the tank pressure and detecting the performance of the system.

Preferably, the latching valve is a master switch between the tank and the engine, and is a propellant control valve designed upstream of the engine to shut off or provide liquid propellant from the tank to the engine.

Preferably, the engine comprises a solenoid valve, a capillary tube, a catalyst bed and a lance.

Preferably, the modular mono-component propulsion system for a spacecraft comprises five engines.

The method has the advantages that two opposite angles of 5 engines are backup, the other 3 engines can select 1 central thruster to work, also can select 2 opposite angles to work, and also can select 3 thrusters to work together, the steady-state work is taken as the main work, and the pulse is taken as the auxiliary work.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model provides a modularization single unit propulsion system suitable for spacecraft can provide the track control function for the spacecraft, and has the redundant design, and each part technical maturity, simple structure, reliability are high, the stable performance, longe-lived, the cost is controllable. The modularized design with the propellant is adopted, the modularized design is suitable for hundred-kilogram-class spacecrafts, only a mounting interface and an electrical interface are required to be reserved in the whole spacecraft, the operation is convenient, the applicability is strong, the dry weight of the whole system is not more than 6.2 kilograms, the full load is not more than 13 kilograms, the overall dimension is not more than 300X280X570mm, and the speed increment of 80m/s can be realized for the spacecraft with the initial mass of 200 kg.

Drawings

Fig. 1 is a schematic overall structure and a front view of the present invention;

fig. 2 is a left side view of the present invention;

fig. 3 is a top view of the present invention;

fig. 4 is a three-dimensional view of the present invention;

FIG. 5 is a schematic diagram of the system of the present invention;

fig. 6 is a schematic structural diagram of an engine according to the present invention;

fig. 7 is a three-dimensional view of the engine of the present invention.

In the figure: 1. a mounting frame; 2. a storage tank; 3. a filter; 4. a self-locking valve; 5. a pressure sensor; 6. an engine; 7. a pneumatic exhaust valve; 8. a liquid adding and discharging valve; 9. an electromagnetic valve; 10. a capillary tube; 11. a catalyst bed; 12. and (4) a spray pipe.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-7, the present invention provides a technical solution:

as shown in fig. 1-3, a modular monopropellant propulsion system for a spacecraft comprises a mounting frame 1, a tank 2, a filter 3, a latching valve 4, a pressure sensor 5, an engine 6, an air charging and discharging valve 7, and a liquid charging and discharging valve 8; as shown in fig. 4, the air charge and discharge valve 7 and the liquid charge and discharge valve 8 are installed at the bottom of the storage tank 2.

Propellant is injected from the bottom of the storage tank 2 through a liquid charging and discharging valve 8, pressurized gas is injected from the top of the storage tank 2 through a gas charging and discharging valve 7, and the self-locking valve 4 and the electromagnetic valve 9 on the engine are always in a closed state after the spacecraft is charged with the propellant; when the star and the arrow are separated, the self-locking valve 4 is opened, the storage tank 2 provides propellant for the engine through the filter 3 and the self-locking valve 4 under the action of surface tension and pressurized gas, and the engine 6 is used for controlling the adjustment of the lifting, the lowering and the orbit inclination angle of the spacecraft. The action commands of the self-locking valve 4 and the engine electromagnetic valve 9 are sent by a satellite-borne computer, the power supply of the pressure sensor 5, the self-locking valve 4 and the engine electromagnetic valve 9 is provided by the spacecraft in a centralized way, and the analog quantity telemetering signals of the pressure sensor 5 are transmitted to the satellite-borne computer. The whole propulsion system is designed in a modularized mode according to the structural characteristics of the spacecraft, the propulsion system can be filled before being installed on the spacecraft, all components in the system are integrated on the installation frame, and the propulsion system is quickly installed on the spacecraft through the installation frame 1. All parts form the whole propulsion system through pipelines and joint connectors. The storage tank 2 is mainly used for storing single-component propellant, and a surface tension management device in the storage tank 2 separates liquid propellant from pressurized gas by utilizing the principle of surface tension, so that propellant without entrained gas can be still provided for the engine in a weightless state, and the normal work of the engine 6 is ensured. The filter 3 is used for filtering the redundant substances in the liquid path, preventing the redundant substances from polluting the downstream self-locking valve 4 or the engine 6, avoiding the system leakage or the capillary tube blockage of the engine 6 and ensuring the normal work of the engine 6. When the propellant flows through the filter 3, all particles in the medium which are larger than the filtering precision are blocked, and the system is filtered. The latching valve 4 is the main switch between the tank 2 and the engine and is a propellant control valve designed upstream of the engine 6 to shut off or provide liquid propellant from the tank to the engine 6. The self-locking valve 4 has the characteristics of bistable self-locking, extremely low energy consumption and high reliability. A pressure sensor 5 is connected between the tank 2 and the latching valve 4 for measuring the tank 2 pressure and for detecting the performance of the system. The gas charging and discharging valve 7 and the liquid charging and discharging valve 8 are respectively used for charging gas and propellant for the storage tank 2 of the spacecraft on the ground. And simultaneously ensures that the propellant and the gas do not leak outwards during the flight test operation. Propellant, pressurized gas, can be vented from the impulse storage tank 2 when a particular situation or requirement occurs. After the gas and liquid filling valve is used, the valve core is screwed down, the pipeline connected with the ground is disassembled, and then the plug is screwed up, so that the joint of the filling and discharging valve forms two sealing surfaces which are connected in series and prevent leakage.

As shown in fig. 5-7, a modular monopropellant propulsion system for spacecraft comprises five engines, wherein the engine 6 comprises a solenoid valve 9, a capillary tube 10, a catalyst bed 11, a nozzle 12 and the like. The engine 6 is mainly used as a track adjusting mechanism of a spacecraft, single-component propellant is adopted, gas is generated after catalytic decomposition and is accelerated to be sprayed out, and chemical energy of the propellant is converted into kinetic energy. Two opposite corners of 5 engines are backup, the other 3 engines can select 1 central thruster to work, also can select 2 opposite corners to work, also can select 3 thrusters to work together, the steady state work is taken as the main, and the pulse is taken as the auxiliary.

The modular single-component propulsion system can provide a track control function for the spacecraft, has a redundancy design, and is mature in each component technology, simple in structure, high in reliability, stable in performance, long in service life and controllable in cost.

The modularized single-unit propulsion system adopts the modularized design with the propellant, is suitable for hundred-kilogram-class spacecrafts, only needs to reserve an installation interface and an electrical interface, is convenient to operate and high in applicability, has the total system dry weight not exceeding 6.2 kilograms, the full load not exceeding 13 kilograms and the overall dimension not exceeding 300 multiplied by 280 multiplied by 570mm, and can realize the speed increment of 80m/s for the spacecrafts with the initial mass of 200 kg.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention. The scope of which is defined by the appended claims and equivalents thereof.

Claims

1. A modular monopropellant propulsion system for a spacecraft, comprising: the modularized single-component propulsion system suitable for the spacecraft comprises a mounting frame (1), a storage box (2), a filter (3), a self-locking valve (4), a pressure sensor (5), an engine (6), a gas adding and discharging valve (7) and a liquid adding and discharging valve (8).

2. A modular monopropellant propulsion system for a spacecraft as claimed in claim 1, wherein: the gas adding and discharging valve (7) and the liquid adding and discharging valve (8) are arranged at the bottom of the storage tank (2).

3. A modular monopropellant propulsion system for a spacecraft as claimed in claim 2, wherein: the pressure sensor (5) is connected between the storage tank (2) and the self-locking valve (4).

4. A modular monopropellant propulsion system for a spacecraft as claimed in claim 3, wherein: the self-locking valve (4) is a main switch between the storage tank (2) and the engine and is a propellant control valve designed for the upstream of the engine (6).

5. A modular monopropellant propulsion system for a spacecraft as claimed in claim 4, wherein: the engine (6) comprises an electromagnetic valve (9), a capillary tube (10), a catalyst bed (11) and a spray pipe (12).

6. A modular monopropellant propulsion system for a spacecraft as claimed in claim 5, wherein: the modular single-component propulsion system suitable for the spacecraft comprises five engines.