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Propellant bottoming energy supply system for spaceflight carrier, and carrier rocket

An energy supply system and propellant technology, which is applied in the field of vehicles, can solve problems such as high cost, inability to detect product performance on arrows, and difficulty in reducing costs, so as to improve flight safety, reduce structural design pressure, and avoid heat flow erosion Effect

Pending Publication Date: 2019-05-28
BEIJING LANDSPACETECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Such expendable tests are not only costly but also unable to directly detect the performance of the product on the arrow
In addition, pyrotechnic products are produced by professional manufacturers, so it is very difficult to reduce costs

Method used

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  • Propellant bottoming energy supply system for spaceflight carrier, and carrier rocket
  • Propellant bottoming energy supply system for spaceflight carrier, and carrier rocket
  • Propellant bottoming energy supply system for spaceflight carrier, and carrier rocket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0044] Such as figure 1 and figure 2 As shown, the propellant sinking energy supply system for aerospace vehicles provided in this embodiment includes at least one gas cylinder 1 , a gas source output switch 2 and at least two Lafal nozzles 3 . Each gas cylinder 1 is connected with an inflation pipeline 4 , and the gas cylinder 1 is connected with one end of the gas source output switch 2 through the inflation pipeline 4 . The other end of the air source output switch 2 is connected with each Rafal nozzle 3 through the nozzle front end pipeline 5 .

[0045] The compressed gas stored in the gas cylinder 1 is sprayed outward through the Rafal nozzles 3 after passing through the inflation pipeline 4 to generate thrust to provide the required axial overload for the launch vehicle.

[0046] In this embodiment, an air source output voltage stabilizer 6 is also provided on the gas filling pipeline 4 connecting the gas cylinder 1 to the gas source output switch 2 . The gas source ...

Embodiment 2

[0059] Such as image 3 As shown, the propellant sinking energy supply system for aerospace vehicles provided in this embodiment includes eight gas cylinders 1 , one gas source output switch 2 and eight Lafal nozzles 3 . Eight gas cylinders 1 are arranged in the rocket body. Preferably, the eight cylinders 1 are evenly arranged at intervals of 45° around the axis in the length direction of the rocket body.

[0060] Each gas cylinder 1 is connected with an inflation pipeline 4 , and one end of the inflation pipe is provided with an inflation and deflation port 7 . A mechanical inflation switch 8 is provided on the inflation pipeline 4 connecting the inflation and deflation port 7 to the gas cylinder 1 . The gas cylinder 1 is connected to the front end pipeline 5 of the nozzle through the inflation pipeline 4 and the gas source output switch 2 . The front end pipeline 5 of the nozzle is connected with the Rafal nozzle 3 .

[0061] The eight Rafal nozzles are arranged in grou...

Embodiment 3

[0064] Such as Figure 4 As shown, the propellant sinking energy supply system for aerospace vehicles provided in this embodiment includes five gas cylinders 1 , one gas source output switch 2 and six Lafal nozzles 3 . Five gas cylinders 1 are arranged in the arrow body. Preferably, five gas cylinders 1 are evenly arranged at intervals of 72° around the axis in the length direction of the rocket body.

[0065] Each gas cylinder 1 is connected with an inflation pipeline 4 , and one end of the inflation pipe is provided with an inflation and deflation port 7 . A mechanical inflation switch 8 is provided on the inflation pipeline 4 connecting the inflation and deflation port 7 to the gas cylinder 1 . The gas cylinder 1 is connected to the front end pipeline 5 of the nozzle through the inflation pipeline 4 and the gas source output switch 2 . The front end pipeline 5 of the nozzle is connected with the Rafal nozzle 3 .

[0066] The six Rafal nozzles are grouped in pairs and di...

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Abstract

The invention provides a propellant bottoming energy supply system for a spaceflight carrier, and a carrier rocket. The propellant bottoming energy supply system comprises at least one gas cylinder, agas source output switch and at least two Rafal jet pipes. The gas cylinder is inflated with compressed gas with preset pressure. The gas cylinder is connected with the Rafal jet pipes through the gas source output switch. The gas cylinder is used for outwards jetting compressed gas through the Rafal jet pipes to generate thrust so as to provide axial overload needed by the carrier rocket. According to the propellant bottoming energy supply system for the spaceflight carrier, because the gas cylinder, the gas source output switch and the Rafal jet pipes are arranged, the gas cylinder is inflated with compressed gas, the gas source output switch is opened, the gas cylinder outwards jet the compressed gas through the Rafal pipes to generate thrust so as to provide axial overload needed by the carrier rocket, the propellant bottoming energy supply system for the spaceflight carrier can provide axial overload for an engine in the carrier rocket instead of initiating explosive devices, heat flux scour caused to a rocket body because a little rocket is used for ignition is avoided, it is beneficial for reducing the pressure on structural design, and the flight safety of the rocket bodyis improved.

Description

technical field [0001] The application belongs to the technical field of vehicles, and in particular relates to a propellant sinking energy supply system and a launch vehicle for aerospace vehicles. Background technique [0002] Before the engine is started after the cold separation and gliding stage of the liquid carrier rocket, the propellant filling of the engine must be carried out. The propellant supplied to the engine will not be mixed with pressurized gas bubbles, so as to ensure the normal start of the engine and the success of the flight test. [0003] In the existing launch vehicles, small solid rockets are basically used as the power device for providing axial overload of the engine. Small solid rockets are pyrotechnics, and pyrotechnics will inevitably generate heat flow on the rocket body during the working process. Therefore, the heat protection of this part of the rocket body needs to be specially considered during the design of the rocket body structure. In...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F17C7/00F17C13/02F17C13/00F17D1/04F42B15/00F02K9/44
Inventor 秦春云王菊金刘建戴政郭凤明张蕾杜正刚
Owner BEIJING LANDSPACETECH CO LTD
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