CN211116306U

CN211116306U - Thin-shell solid fuel rocket

Info

Publication number: CN211116306U
Application number: CN201921197546.5U
Authority: CN
Inventors: 杨德安
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-07-29
Filing date: 2019-07-29
Publication date: 2020-07-28
Anticipated expiration: 2029-07-29

Abstract

The utility model discloses a thin-shell solid fuel rocket, which comprises a rocket shell, a fuel storage tank, a material conveying component, a combustion chamber and a spray pipe, wherein the fuel storage tank is arranged in the rocket shell, the combustion chamber is arranged at one side of the fuel storage tank, and the material conveying component is arranged between the fuel storage tank and the combustion chamber; the prior art fuel tank is divided into a fuel storage tank and a combustion chamber which are separated from each other, wherein the volumes of the fuel storage tank and the combustion chamber are the same as the volume of the prior art fuel tank, and the tank body of the fuel storage tank is thinner, so that the production cost is reduced, the mass ratio of the fuel tank to the fuel is reduced, and the load of the rocket is increased.

Description

Thin-shell solid fuel rocket

Technical Field

The utility model relates to a fuel is stored and mechanical instruments field of transport, concretely relates to thin shell solid fuel rocket.

Background

The fuel tank of the solid fuel rocket used at the present stage is a combustion chamber, so that the fuel tank needs to resist high temperature and high pressure, and the fuel tank of the solid fuel rocket is thick and firm, so that the manufacturing cost of the fuel tank is higher, and the fuel tank has larger mass relative to fuel; in addition, after a fixed fuel is ignited once, all the fuel in the fuel tank needs to be burnt out, the burning speed cannot be controlled in the middle, and the rocket is ignited and restarted, so that the function of the solid fuel rocket is limited.

Disclosure of Invention

To the not enough of above-mentioned prior art, the utility model provides a thin shell solid fuel rocket is convenient for control the fuel in the combustion chamber, can control the combustion strength of the fuel in the combustion chamber like this and the start-up of reigniting of combustion chamber, separates fuel-tank and combustion chamber simultaneously, reduces the quality and the thickness of fuel-tank like this, greatly reduced the cost, reduce the dead weight of rocket simultaneously, increased the load of rocket.

In order to achieve the above purpose, the utility model discloses a scheme: a thin-shell solid fuel rocket comprises a rocket shell, a fuel storage tank, a material conveying assembly, a combustion chamber and a spray pipe, wherein the fuel storage tank is arranged in the rocket shell, the combustion chamber is arranged on one side of the fuel storage tank, the material conveying assembly is arranged between the fuel storage tank and the combustion chamber, the fuel storage tank is communicated with the combustion chamber through the material conveying assembly, the sum of the volumes of the fuel storage tank and the combustion chamber is consistent with the volume of a fuel tank in the prior art, and the wall thickness of the fuel storage tank is smaller than the wall thickness of the combustion chamber; the combustion chamber is connected with a spray pipe.

Preferably, the material conveying assembly comprises an auger channel and a propelling channel, wherein the auger channel extends into the fuel storage box, the propelling channel is arranged below the reaming channel, one end of the auger channel, which is far away from the fuel storage box, is connected and communicated with a blanking pipeline, the other end of the blanking pipeline is connected and communicated with the propelling channel, a pushing block is arranged in the propelling channel, a hydraulic cylinder is arranged at one end of the propelling channel, a piston rod of the hydraulic cylinder is connected with the pushing block, the pushing block is pushed to move in the propelling channel through the hydraulic cylinder, the other end of the propelling channel is connected and communicated with the combustion chamber, a heat insulation sheet is arranged at the joint between the propelling channel and the combustion chamber, the heat insulation sheet is connected with a rotating module, and the rotating module is eccentrically connected with the heat insulation sheet.

Compared with the prior art, the utility model has the advantages of: 1. the fuel tank in the prior art is divided into a fuel storage tank and a combustion chamber which are separated from each other, wherein the volumes of the fuel storage tank and the combustion chamber are consistent with the volume of the fuel tank in the prior art, and meanwhile, the tank body of the fuel storage tank is thinner, so that the production cost is reduced, the mass ratio of the fuel tank to the fuel is reduced, and the load of the rocket is increased; 2. a conveying assembly is arranged between the fuel storage chamber and the combustion chamber, and the speed of conveying the fuel by the conveying assembly is controlled to control the combustion intensity of the combustion chamber and simultaneously carry out ignition restarting; 3. the heat insulation sheet can separate the propelling pipeline from the combustion chamber, and meanwhile, fuel in the propelling pipeline can enter the combustion chamber.

Drawings

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

Fig. 2 is a sectional view of the present invention.

Fig. 3 is a matching view of the propulsion passage and the combustion chamber of the present invention.

The fuel storage device comprises a rocket shell, a fuel storage box, a fuel conveying assembly, a packing auger channel, a propelling channel, a pushing block, a hydraulic cylinder, a discharging pipeline, a heat insulation sheet, a rotating module, a combustion chamber and a spray pipe, wherein the rocket shell is 1, the fuel storage box is 2, the fuel conveying assembly is 3, the packing auger channel is 3.2, the propelling channel is 3.3, the pushing block is 3.4, the hydraulic cylinder is 3.5, the discharging pipeline is 3.6, the heat insulation.

Detailed Description

The present invention will now be further elucidated with reference to the accompanying drawings.

As shown in figures 1-3, a thin-shell solid fuel rocket comprises a rocket shell 1, a fuel storage tank 2, a material conveying assembly 3, a combustion chamber 4 and a nozzle 5, wherein the fuel storage tank 2 is fixed in the rocket shell 1 in a bolt fastening manner, the combustion chamber 4 is arranged at the lower side of the fuel storage tank 2, the combustion chamber 4 is fixed in the rocket shell 1 in a welding manner, the material conveying assembly 3 is arranged between the fuel storage tank 2 and the combustion chamber 4, the material conveying assembly 3 comprises an auger channel 3.1 and a propelling channel 3.2, wherein the auger channel 3.1 extends into the fuel storage tank 2, the propelling channel 3.2 is arranged below the auger channel 3.1, one end of the auger channel 3.1 far away from the fuel storage tank 2 is connected and communicated with a vertically downward blanking pipeline 3.5 in a welding manner, the lower end of the blanking pipeline 3.5 is connected and communicated with the propelling channel 3.2 in a welding manner, a pushing block 3.3 which slides back and forth in a pushing channel 3.2 is placed in the pushing channel 3.2, the outer wall of the pushing block 3.3 is attached to the inner wall of a pushing pipeline, a hydraulic cylinder 3.4 is fixed at one end of the pushing channel 3.2 in a bolt fastening mode, a piston rod of the hydraulic cylinder 3.4 is connected with the pushing block 3.3, the pushing block 3.3 is pushed to move in the pushing channel 3.2 through the hydraulic cylinder 3.4, so that solid fuel is pushed to move in the pushing channel 3.2, the other end of the pushing channel 3.2 is connected and communicated with a combustion chamber 4 in a welding mode, a heat insulation sheet 3.6 is arranged at the connection part between the pushing channel 3.2 and the combustion chamber 4, the pushing channel 3.2 is completely blocked by the heat insulation sheet 3.6, a rotating module 3.7 is connected with the heat insulation sheet 3.6 in a welding mode, the rotating module 3.7 is eccentrically connected with the heat insulation sheet 3.6, the rotating module 3.7 is a stepping motor, the rotating of the stepping motor is used for sealing the pushing channel 3.2, meanwhile, the pushing channel 3.2 can be opened by the heat insulating sheet 3.6 through the rotation of the stepping motor, when the pushing channel 3.2 is opened by the heat insulating sheet 3.6, the solid fuel enters the combustion chamber 4 through the pushing channel 3.2 to be combusted, the fuel storage tank 2 is communicated with the combustion chamber 4 through the material conveying assembly 3, the sum of the volumes of the fuel storage tank 2 and the combustion chamber 4 is consistent with the volume of the fuel tank in the prior art, wherein the thickness of the wall of the fuel storage tank 2 is far smaller than the wall thickness of the combustion chamber 4 (the fuel storage tank 2 is separated from the combustion chamber 4, the fuel storage tank 2 does not have higher strength requirement, so that the thickness of the fuel storage tank 2 is thinner, the fuel storage tank 2 does not have strong pressure inside, the fuel storage tank 2 can be made of common materials (iron sheet and stainless steel sheet), and meanwhile, the fuel storage tank 2 needs to store a large amount of solid raw materials, namely, the, the volume of the fuel storage box 2 is larger, when the shell of the fuel storage box 2 becomes thinner, the weight of the fuel storage box 2 is far less than that of the original rocket fuel storage box 2, the auger channel 3.1 and the blanking pipeline 3.5 of the material conveying assembly 3 do not need to bear larger pressure, the auger channel 3.1 and the blanking pipeline 3.5 are both made of light materials, and the propulsion channel 3.2 is the same as the combustion chamber 4 when the heat insulation sheet 3.6 is opened, the propulsion channel 3.2 needs to ensure the same material and thickness as the outer wall of the combustion chamber 4, but the propelling passage 3.2 can be set shorter to reduce the weight and the cost, so that the dead weight of the whole rocket is reduced, the load of the rocket can be properly increased, the weight of the rocket is reduced, the load of the rocket can be properly increased, meanwhile, if the requirement on the strength of the fuel storage tank 2 is reduced, the manufacturing cost of the fuel storage tank 2 is correspondingly reduced; the combustion chamber 4 is connected and communicated with a spray pipe 5 in a welding mode, and high-temperature and high-pressure gas generated in the combustion chamber 4 is sprayed out through the spray pipe 5, so that the rocket can fly.

When in use, solid fuel is placed in the fuel storage box 2, the solid fuel is conveyed out through the auger and enters the discharging pipeline 3.5, the solid fuel in the discharging pipeline 3.5 falls into the propelling channel 3.2 through gravity, then the pushing block 3.3 is pushed by the hydraulic cylinder 3.4 to move towards the combustion chamber 4 in the propelling channel 3.2, at this time, the heat insulation sheet 3.6 rotates through the stepping motor, so that the propelling channel 3.2 is communicated with the combustion chamber 4, the pushing block 3.3 pushes the solid fuel in the propelling channel 3.2 to the combustion chamber 4, so that the conveying of solid combustion is completed, meanwhile, the ignition device in the combustion chamber 4 still exists, after fuel is added into the combustion chamber 4, the ignition combustion is carried out through the ignition device, the conveying component arranged between the fuel storage box 2 and the combustion chamber 4 can control the combustion intensity in the combustion chamber 4, and the combustion intensity in the combustion chamber 4 needs to be enhanced, accelerate the conveying speed of fuel through conveying assembly 3, otherwise then reduce conveying assembly 3's conveying speed, for solid rocket in the past, the utility model discloses can control combustion strength of combustion chamber 4, the utility model discloses only improve the combustion chamber and the fuel storage case of rocket, other structures all do not change, simultaneously the utility model discloses a combustion box is unanimous with the combustion box of original rocket.

Claims

1. A thin-shell solid fuel rocket comprises a rocket shell, a fuel storage tank, a material conveying assembly, a combustion chamber and a spray pipe, and is characterized in that the fuel storage tank is arranged in the rocket shell, the combustion chamber is arranged on one side of the fuel storage tank, the material conveying assembly is arranged between the fuel storage tank and the combustion chamber, the fuel storage tank is communicated with the combustion chamber through the material conveying assembly, the sum of the volumes of the fuel storage tank and the combustion chamber is consistent with the volume of a fuel tank in the prior art, and the thickness of the wall of the fuel storage tank is smaller than the wall thickness of the combustion chamber; the combustion chamber is connected with a spray pipe.

2. The thin-shelled solid fuel rocket of claim 1, wherein the material conveying assembly comprises an auger channel and a propulsion channel, wherein the auger channel extends into the fuel storage tank, the propulsion channel is arranged below the reaming channel, one end of the auger channel, which is far away from the fuel storage tank, is connected and communicated with a blanking pipeline, the other end of the blanking pipeline is connected and communicated with the propulsion channel, a push block is arranged in the propulsion channel, one end of the propulsion channel is provided with a hydraulic cylinder, a piston rod of the hydraulic cylinder is connected with the push block, the push block is pushed by the hydraulic cylinder to move in the propulsion channel, the other end of the propulsion channel is connected and communicated with the combustion chamber, a heat insulation sheet is arranged at the joint between the propulsion channel and the combustion chamber, the heat insulation sheet is connected with a rotating module, and the rotating module and the heat insulation sheet are eccentrically connected.