An integrated space attitude and orbit control power system

Abstract

This invention discloses an integrated space attitude and orbit control propulsion system, comprising a liquefied gas (LPG) tank, a heater, a nozzle, a valve, a flange, and a solid rocket motor propulsion unit. The heater is installed at the bottom of the LPG tank, which is connected to the nozzle via a pipeline. The valve is installed on the pipeline. The solid rocket motor propulsion unit is fixed by the flange, which is bolted to the LPG attitude and orbit control propulsion unit, thus connecting the LPG attitude and orbit control propulsion system with the solid rocket motor propulsion system. This invention reduces the weight of the attitude and orbit control propulsion system, saves space, and reduces costs.

Description

Technical Field

[0001] This invention belongs to the field of aerospace propulsion technology, specifically relating to an integrated propulsion system for space attitude and orbit control. Background Technology

[0002] The attitude and orbit control engine system is a critical system for maintaining and adjusting the orbit and attitude of a spacecraft, ensuring its normal on-orbit operation. With the rapid development of my country's space program and the increasing on-orbit operation time of spacecraft, higher demands are placed on its attitude and orbit control propulsion system, requiring it to adapt to more complex mission requirements.

[0003] Currently, countries around the world have intensified their space exploration, launching hundreds and even thousands of satellites. However, this has also led to the generation of more space debris. This poses a significant danger to satellites already in orbit. A collision with another satellite or space debris could cause catastrophic damage, rendering the satellite unable to function properly. Summary of the Invention

[0004] To overcome the shortcomings of existing technologies, this invention provides an integrated space attitude and orbit control propulsion system, including a liquefied gas (LPG) tank, a heater, a nozzle, a valve, a flange, and a solid rocket motor propulsion unit. The heater is installed at the bottom of the LPG tank, which is connected to the nozzle via a pipeline, and the valve is installed on the pipeline. The solid rocket motor propulsion unit is fixed by the flange, which is bolted to the LPG attitude and orbit control propulsion unit, thus connecting the LPG attitude and orbit control propulsion system with the solid rocket motor propulsion system. This invention reduces the weight of the attitude and orbit control propulsion system, saves space, and reduces costs.

[0005] The technical solution adopted by this invention to solve its technical problem is as follows:

[0006] An integrated space attitude and orbit control propulsion system includes a liquefied gas attitude and orbit control propulsion system, a flange, and a solid rocket motor propulsion system;

[0007] The liquefied gas attitude and orbit control power system includes a liquefied gas storage tank, a heater, a nozzle, and valves;

[0008] The heater is installed at the bottom of the liquefied gas storage tank to heat the bottom of the liquefied gas storage tank, thereby increasing the pressure of the liquefied gas in the storage tank and making it easier to obtain greater thrust when ejected from the nozzle.

[0009] The nozzles are connected to the liquefied gas storage tank via pipes, and the four nozzles are respectively located at the four corners of the liquefied gas attitude and orbit control power system.

[0010] There are four valves, which are installed on four pipes respectively, and serve as switches to control the release of liquefied gas;

[0011] The flange is installed on the upper end of the solid rocket engine propulsion system, connecting the solid rocket engine propulsion system with the liquefied gas attitude and orbit control propulsion system.

[0012] Preferably, the solid rocket motor propulsion system is connected to the liquefied gas attitude and orbit control propulsion system by bolts through a flange.

[0013] Preferably, when the liquefied gas attitude and trajectory control power system performs attitude control, the liquefied gas in the liquefied gas storage tank is heated by a heater to increase its pressure. Only two of the four valves that are not diagonally opposite are opened, and the liquefied gas is ejected from the nozzle, generating a non-centrally symmetrical thrust and generating rotational inertia to achieve attitude control.

[0014] The beneficial effects of this invention are as follows:

[0015] 1. This invention designs an integrated space attitude and orbit control power system, which uses liquefied gas as the working fluid of the attitude and orbit control power system, thereby reducing the mass of the attitude and orbit control power system, saving space, and reducing costs.

[0016] 2. This invention utilizes the switching of valves on different pipelines to realize the switching of liquefied gas nozzles, thereby generating rotational inertia in the satellite. This achieves the integration of the attitude control propulsion system and the orbit control propulsion system, reducing mass, saving space, lowering system complexity, and increasing system reliability.

[0017] 3. By combining the attitude and orbit control propulsion system with the solid rocket motor propulsion system, the satellite can be provided with high thrust for a short period of time through the pulse ignition of the solid rocket motor, enabling the satellite to quickly avoid obstacles and change orbits. Attached Figure Description

[0018] Figure 1 This is a half-sectional view of the integrated spatial attitude and orbit control power system of the present invention.

[0019] Figure 2 This is the first overall schematic diagram of the integrated space attitude and orbit control power system of the present invention.

[0020] Figure 3 This is a front view of the integrated spatial attitude and orbit control power system of the present invention.

[0021] Figure 4 This is a rear view of the integrated spatial attitude and orbit control power system of the present invention.

[0022] Figure 5 This is the second overall schematic diagram of the integrated space attitude and orbit control power system of the present invention.

[0023] In the diagram: 1-Liquefied gas storage tank, 2-Heater, 3-Nozzle, 4-Valve, 5-Flange, 6-Solid rocket engine propulsion system. Detailed Implementation

[0024] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0025] This invention designs an integrated space attitude and orbit control propulsion system, integrating the attitude control propulsion system and the orbit control propulsion system, reducing structural mass and saving space. Furthermore, this invention combines a liquefied gas propulsion system with a solid rocket motor propulsion system, enabling rapid obstacle avoidance and rapid orbit changes for the satellite.

[0026] The purpose of this invention is to provide an integrated space attitude and orbit control propulsion system, which can realize the integration of attitude and orbit control propulsion systems and enable satellites to quickly avoid obstacles and change orbits.

[0027] An integrated space attitude and orbit control propulsion system includes a liquefied gas attitude and orbit control propulsion system, a flange 5, and a solid rocket engine propulsion system 6;

[0028] The liquefied gas attitude and trajectory control power system includes an liquefied gas storage tank 1, a heater 2, a nozzle 3, and a valve 4;

[0029] The heater 2 is installed at the bottom of the liquefied gas storage tank 1 to heat the bottom of the liquefied gas storage tank 1, thereby increasing the pressure of the liquefied gas in the liquefied gas storage tank 1, which makes it easier to spray out from the nozzle 3 to obtain greater thrust.

[0030] The nozzle 3 is connected to the liquefied gas storage tank 1 through a pipe, and the four nozzles 3 are respectively set at the four corners of the liquefied gas attitude and track control power system.

[0031] There are four valves 4, which are installed on four pipes respectively, and serve as switches to control the release of liquefied gas;

[0032] The flange 5 is installed on the upper end of the solid rocket engine propulsion system 6, connecting the solid rocket engine propulsion system 6 with the liquefied gas attitude and orbit control propulsion system.

[0033] The solid rocket motor propulsion system 6 is connected to the liquefied gas attitude and orbit control propulsion system by bolts through the flange 5.

[0034] When the liquefied gas attitude and orbit control power system performs attitude control, the liquefied gas in the liquefied gas storage tank 1 is heated by the heater 2 to increase its pressure. Only two of the four valves that are not diagonally opposite are opened, and the liquefied gas is ejected from the nozzle, generating a non-centrally symmetrical thrust and generating rotational inertia to achieve attitude control.

[0035] Example:

[0036] An integrated space attitude and orbit control propulsion system includes a liquefied gas (LPG) tank, a heater, nozzles, valves, flanges, and a solid rocket motor propulsion unit. The orbit control power of this invention originates from the LPG propulsion system. The heating system heats the LPG, causing it to be ejected from the nozzles through pipes, thereby generating thrust. The opening and closing of the four nozzles is achieved by controlling the valves on the four pipes, thus generating rotational inertia for the satellite and controlling its attitude. Combined with the pulse ignition of the solid rocket motor propulsion system, a large thrust is provided for a short time, enabling rapid obstacle avoidance and orbit changes for the satellite.

[0037] The liquefied petroleum gas (LPG) storage tank is used to store LPG and is connected to nozzles via pipelines.

[0038] The heater is installed at the bottom of the liquefied gas storage tank to heat the bottom of the tank, thereby increasing the pressure of the liquefied gas inside the tank and making it easier to obtain greater thrust when ejected from the nozzle.

[0039] The nozzles are connected to the liquefied gas storage tank via pipes, and the four nozzles are respectively located at the four corners of the liquefied gas attitude control power system.

[0040] Valves are installed on four pipelines and are opened and closed according to task requirements to control the release of liquefied gas.

[0041] The flange is mounted on the solid rocket motor propulsion system, connecting the solid rocket motor propulsion system with the liquefied gas attitude and orbit control propulsion system.

[0042] The solid rocket motor propulsion system consists of multiple solid rocket motors arranged in an array via flanges, which are then connected to the liquefied gas attitude and orbit control propulsion system using bolts and flanges.

[0043] The working process of the integrated space attitude and orbit control power system is as follows:

[0044] Liquefied petroleum gas (LPG) is stored in an LPG tank. The LPG in the tank is heated by a heater to increase its pressure. The valve on the pipeline is then opened, allowing the LPG to enter the nozzle through the pipeline and then be ejected from the nozzle to generate thrust, thus achieving track control.

[0045] When attitude control of a satellite is required, the liquefied gas in the gas tank is heated by a heater to increase its pressure. Only two of the four valves are opened (note that the opened valves must not be diagonally opposite), and the liquefied gas is ejected from the nozzle, generating a non-centrosymmetric thrust and producing rotational inertia. Similarly, changing the opening and closing of different valves can produce rotation in different directions, thus achieving attitude control.

[0046] When satellites need to perform rapid obstacle avoidance and orbit changes, pulse ignition of the solid rocket propulsion system can generate a large thrust in a short time, enabling the satellite to quickly avoid obstacles and change orbits.

Claims

1. A space attitude and orbit control integrated power system, characterized in that, This includes the liquefied gas attitude and orbit control propulsion system, the flange, and the solid rocket motor propulsion system; The liquefied gas attitude and trajectory control power system includes a liquefied gas storage tank, a heater, a nozzle, and valves. When the liquefied gas attitude and trajectory control power system performs attitude control, the heater heats the liquefied gas in the liquefied gas storage tank to increase its pressure. Only two of the four valves that are not diagonally opposite are opened, and the liquefied gas is ejected from the nozzle, generating a non-centrally symmetrical thrust and generating rotational inertia to achieve attitude control. The heater is installed at the bottom of the liquefied gas storage tank to heat the bottom of the liquefied gas storage tank, thereby increasing the pressure of the liquefied gas in the storage tank and making it easier to obtain greater thrust when ejected from the nozzle. The nozzles are connected to the liquefied gas storage tank via pipes, and the four nozzles are respectively located at the four corners of the liquefied gas attitude and orbit control power system. There are four valves, which are installed on four pipes respectively, and serve as switches to control the release of liquefied gas; The flange is installed on the upper end of the solid rocket engine propulsion system, connecting the solid rocket engine propulsion system with the liquefied gas attitude and orbit control propulsion system.

2. The integrated space attitude and orbit control power system according to claim 1, characterized in that, The solid rocket motor propulsion system is connected to the liquefied gas attitude and orbit control propulsion system via bolts through a flange.

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