CN213870057U

CN213870057U - Extrusion pump capable of being used for propellant supply of rocket engine

Info

Publication number: CN213870057U
Application number: CN202021672071.3U
Authority: CN
Inventors: 楚龙飞
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-08-12
Filing date: 2020-08-12
Publication date: 2021-08-03
Anticipated expiration: 2030-08-12

Abstract

The utility model provides a can be used to extrusion pump of rocket engine propellant supply, including high-pressure air source, low pressure reservoir, rocket engine, reservoir stabiliser, high-pressure pump chamber one, high-pressure pump chamber two, high-pressure air source passes through connecting tube and is connected with low pressure reservoir, high-pressure pump chamber one, high-pressure pump chamber two respectively, the other end of high-pressure pump chamber one and high-pressure pump chamber two is connected with low pressure reservoir and rocket engine respectively, be provided with the reservoir stabiliser on the connecting tube between high-pressure air source and the low pressure reservoir. The utility model discloses simple structure, the reliability is high, simultaneously greatly reduced research and development cycle and manufacturing cost and can alleviate low pressure storage tank quality more than 80% for the flight time and the carrying capacity of rocket promote greatly, have extremely wide application prospect and considerable economic value.

Description

Extrusion pump capable of being used for propellant supply of rocket engine

Technical Field

The utility model belongs to the technical field of rocket engine's extrusion pump, especially, relate to an extrusion pump that can be used to rocket engine propellant supply.

Background

The engine system is a power source necessary for finishing various tasks of spacecrafts such as rockets, satellites and space stations, the liquid rocket engine has the advantages of high performance, low cost, reusability, good safety and the like compared with a solid engine, and the liquid rocket engine needs to continuously supply propellant from a storage tank to the engine through a pressurization conveying system during working and simultaneously meets certain flow and pressure requirements.

At present, the propellant pressurization conveying mode of the liquid rocket engine mainly comprises two modes: extrusion and pump-pressure. The advantages and disadvantages of the two are compared with the applicable scene as follows:

extrusion type: pressurized gas is directly supplied to a large-volume propellant tank from a high-pressure gas cylinder, and the propellant is extruded to the engine under the action of the high-pressure gas. The extrusion type supply system has the advantages that the system is simple and reliable, and the defects that the storage tank needs to bear higher pressure, the structural weight is greatly increased, the rocket efficiency is extremely low, practical application such as orbit entering cannot be completed, meanwhile, the working pressure of the engine is difficult to improve, the specific impulse performance of the engine is poor, and the like, so the extrusion type supply system is only used for a few fields such as satellite in-orbit propulsion and the like at present.

The pump pressure formula: the propellant in the low pressure tank is typically pressurized and delivered to the engine using a centrifugal pump rotating at high speed. According to different driving modes of the centrifugal pump, the centrifugal pump can be divided into gas generator circulation, expansion circulation, staged combustion circulation, electric driving pump and the like, and the highest pressurization of dozens of megapascals can be realized. The pumping type has the advantages that the storage tank only needs to bear low pressure, the structural mass is greatly reduced, the whole rocket efficiency is high, the specific thrust of the engine is high, and the defects that a turbo pump system is extremely complex, the working environment is severe, the risk is high, the rotating speed of a heart pump is generally tens of thousands of revolutions, the temperature of a fuel gas generator is close to 1000 ℃, long-time research and development and test are needed, the manufacturing process is complex, and the cost is high.

The patent of the utility model provides a can be used to extrusion pump of rocket engine propellant supply utilizes the simple and reliable advantage of extrusion formula system, realizes that the pumping pressure formula is high-efficient, subtract heavy effect, through the design to framework optimization and control chronogenesis, this extrusion pump possesses certain system fault-tolerant ability, is showing the reliability that provides full arrow, shortens the research and development cycle, greatly reduced research and development and manufacturing cost.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model provides an extrusion pump that can be used to rocket engine propellant supply, including high-pressure air source, low pressure tank, rocket engine, tank stabiliser, high-pressure pump chamber one, high-pressure pump chamber two, high-pressure air source passes through connecting line and is connected with low pressure tank, high-pressure pump chamber one, high-pressure pump chamber two respectively, the other end of high-pressure pump chamber one and high-pressure pump chamber two is connected with low pressure tank and rocket engine respectively, be provided with tank stabiliser on the connecting line between high-pressure air source and the low pressure tank, be provided with pump chamber stabiliser one and pump chamber stabiliser two respectively on the connecting line between high-pressure air source and high-pressure pump chamber one and high-pressure pump chamber two, be provided with relief valve one, relief valve two respectively on high-pressure pump chamber one and high-pressure pump chamber two and the low-pressure pump chamber two, be provided with feed liquor valve one and feed liquor valve two respectively on the connecting branch road between high-pressure pump chamber one, high-pressure pump chamber two and low-pressure pump chamber, and a liquid outlet valve I and a liquid outlet valve II are respectively arranged on connecting branches between the high-pressure pump cavity I and the high-pressure pump cavity II and the rocket engine.

Preferably, the high pressure gas source is made of composite material or metal.

Preferably, the tank pressure stabilizer, the first pump cavity pressure stabilizer and the second pump cavity pressure stabilizer can adopt diaphragm type pressure stabilizers or other types of pressure stabilizers, and control electromagnetic valves are arranged in the tank pressure stabilizer, the first pump cavity pressure stabilizer and the second pump cavity pressure stabilizer.

Preferably, a first pump cavity pressure stabilizer and a first pressure relief valve are arranged above the first high-pressure pump cavity respectively, and a second pump cavity pressure stabilizer and a second pressure relief valve are arranged above the second high-pressure pump cavity respectively.

Preferably, a first liquid inlet valve and a first liquid outlet valve are respectively arranged below the high-pressure pump cavity, and a second liquid inlet valve and a second liquid outlet valve are respectively arranged below the second high-pressure pump cavity.

The utility model has the advantages that:

(1) the utility model discloses compare with traditional turbopump, do not have high-speed rotary part, do not have combustion part, do not have high low temperature adverse circumstances, do not have high pressure dynamic seal's demand, simple structure, the reliability is high, simultaneously greatly reduced research and development cycle and manufacturing cost.

(2) The utility model discloses compare with traditional extrusion formula booster pump, can alleviate the storage tank quality more than 80% for the flight time and the carrying capacity of rocket promote greatly, have extremely wide application prospect and considerable economic value.

(3) The utility model discloses not only can use the normal temperature propellant of space flight kerosene, alcohol, hydrogen peroxide class, also can use the low temperature propellant of liquid oxygen, methane class, have extensive suitability and inheritance.

Drawings

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

In the figure: 1. a high pressure gas source; 2. a low pressure tank; 3. a rocket motor; 4. a tank regulator; 5. a first high-pressure pump cavity; 6. a second high-pressure pump cavity; 7. a pump cavity voltage stabilizer I; 8. a pump cavity voltage stabilizer II; 9. a first pressure relief valve; 10. a second pressure release valve; 11. a first liquid inlet valve; 12. a liquid inlet valve II; 13. a first liquid outlet valve; 14. and a second liquid outlet valve.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings of 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.

The present invention is further described below:

example (b):

as shown in figure 1, the extrusion pump for supplying the propellant to the rocket engine comprises a high-pressure air source 1, a low-pressure storage tank 2, a rocket engine 3, a storage tank voltage stabilizer 4, a high-pressure pump cavity I5 and a high-pressure pump cavity II 6, wherein the high-pressure air source 1 is respectively connected with the low-pressure storage tank 2, the high-pressure pump cavity I5 and the high-pressure pump cavity II 6 through connecting pipelines, the other ends of the high-pressure pump cavity I5 and the high-pressure pump cavity II 6 are respectively connected with the low-pressure storage tank 2 and the rocket engine 3, the storage tank voltage stabilizer 4 is arranged on the connecting pipeline between the high-pressure air source 1 and the low-pressure storage tank 2, the pump cavity voltage stabilizer I7 is arranged on the connecting branch between the high-pressure air source 1 and the high-pressure pump cavity I5, the pump cavity voltage stabilizer II 8 is arranged on the connecting branch between the high-pressure air source 1 and the high-pressure pump cavity II 6, and the storage tank voltage stabilizer 4 and the pump cavity voltage stabilizer I7, Pump chamber stabiliser two 8 can adopt diaphragm type stabiliser, and all is provided with control solenoid valve in the portion, still be provided with relief valve one 9 on the high-pressure pump chamber one 5, still be provided with relief valve two 10 on the high-pressure pump chamber two 6, be provided with feed liquor valve one 11 on the branch road of being connected between high-pressure pump chamber one 5 and the low pressure storage tank 2, be provided with feed liquor valve two 12 on the branch road of being connected between high-pressure pump chamber two 6 and the low pressure storage tank 2, be provided with out liquid valve one 13 on the branch road of being connected between high-pressure pump chamber one 5 and the rocket engine 3, be provided with out liquid valve two 14 on the branch road of being connected between high-pressure pump chamber two 6 and the engine rocket 3.

Specifically, the high-pressure gas source 1 is made of composite material or metal, the main high-pressure gas of the high-pressure gas source is generally nitrogen or helium, and the low-pressure tank 2, the high-pressure pump cavity I5 and the high-pressure pump cavity II 6 are continuously pressurized by the pressure stabilizer 4.

Specifically, the low-pressure storage tank 2 is a large-volume storage tank for storing rocket liquid propulsion, is formed by welding high-strength metal, can be used for using normal-temperature propellants such as space kerosene, alcohol and hydrogen peroxide and also can be used for using low-temperature propellants such as liquid oxygen and methane, and compared with the traditional extrusion type booster pump, the low-pressure storage tank can be lightened by more than 80% in mass, so that the flight time and the carrying capacity of the rocket are greatly improved.

Specifically, the rocket engine 3, which is a device for generating thrust by using a chemical reaction of rocket fuel, needs to continuously supply a liquid propellant meeting certain pressure and flow requirements during the working process.

Specifically, the first high-pressure pump cavity 5 and the second high-pressure pump cavity 6 are both cylindrical pressure-resistant containers and are used for pressurizing a small-volume propellant, and the internal pressure is higher than the working pressure of the rocket engine 3 during use.

Specifically, the relief valve 9, the relief valve two 10, the feed liquor valve 11, the feed liquor valve two 12, go out liquid valve 13, go out liquid valve two 13, be used for the pump chamber pressure release respectively, the pump chamber inlet liquid, the pump chamber goes out liquid, by control system control pump chamber stabiliser 7 and pump chamber stabiliser two 8 and relief valve 9, relief valve two 10, feed liquor valve 11, feed liquor valve two 12, go out liquid valve 13, go out the precedence chronogenesis of liquid valve two 13 for a plurality of branches work in coordination, the chronogenesis links up, can last constantly to the engine supply, the liquid propellant of pressure and flow stability.

The working principle is as follows: the initial state inside the high-pressure gas source 1 is a state of being filled with nitrogen; the upper space of the low-pressure storage tank is nitrogen, and the lower space of the low-pressure storage tank is liquid propellant; high-pressure pump chamber one 5 and high-pressure pump chamber two 6 are through pump chamber stabiliser one 7 and pump chamber stabiliser two 8 control work in turn to realize the continuous pressure boost and the supply of liquid propellant, again by control system control pump chamber stabiliser one 7 and pump chamber stabiliser two 8 and relief valve one 9, relief valve two 10, feed liquor valve one 11, feed liquor valve two 12, go out liquid valve one 13, go out the precedence chronogenesis of liquid valve two 13, control pump chamber pressure release, pump chamber feed liquor and pump chamber play liquid, make a plurality of branches collaborative work, the chronogenesis links up, can be continuously to the engine supply, the liquid propellant of pressure and flow stability.

It should be noted that, in this document, moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that 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 in the appended claims and their equivalents.

Claims

1. An extrusion pump capable of being used for propellant supply of a rocket engine is characterized by comprising a high-pressure air source (1), a low-pressure storage tank (2), a rocket engine (3), a storage tank pressure stabilizer (4), a high-pressure pump cavity I (5) and a high-pressure pump cavity II (6), wherein the high-pressure air source (1) is respectively connected with the low-pressure storage tank (2), the high-pressure pump cavity I (5) and the high-pressure pump cavity II (6) through connecting pipelines, the other ends of the high-pressure pump cavity I (5) and the high-pressure pump cavity II (6) are respectively connected with the low-pressure storage tank (2) and the rocket engine (3), the storage tank pressure stabilizer (4) is arranged on a connecting pipeline between the high-pressure air source (1) and the high-pressure pump cavity I (5) and the high-pressure pump cavity II (6), the pump cavity pressure stabilizer I (7) and the pump cavity pressure stabilizer II (8) are respectively arranged on the connecting pipeline between the high-pressure air source (1) and the high-pressure pump cavity I (5) and the high-pressure pump cavity II (6), be provided with relief valve (9), relief valve two (10) on high-pressure pump chamber (5) and the high-pressure pump chamber two (6) respectively, be provided with feed liquor valve (11) and feed liquor valve two (12) on the branch road of being connected between high-pressure pump chamber (5), high-pressure pump chamber two (6) and low pressure storage tank (2) respectively, be provided with liquid valve (13) and liquid valve two (14) on the branch road of being connected between high-pressure pump chamber (5) and high-pressure pump chamber two (6) and rocket engine (3) respectively.

2. A squeeze pump usable for rocket engine propellant supply according to claim 1, characterized in that said high pressure gas source (1) is made of composite material or metal.

3. A squeeze pump for rocket engine propellant supply according to claim 1, characterized in that the tank stabilizer (4), the pump chamber stabilizer one (7), and the pump chamber stabilizer two (8) can be diaphragm type stabilizers or other types of stabilizers, and are all provided with control solenoid valves.

4. A squeeze pump usable for propellant supply of rocket engines according to claim 1, characterized in that a first pump chamber regulator (7) and a first pressure relief valve (9) are provided above said first high-pressure pump chamber (5), and a second pump chamber regulator (8) and a second pressure relief valve (10) are provided above said second high-pressure pump chamber (6).

5. An extrusion pump for propellant supply in rocket engines according to claim 1 wherein said first high-pressure pump chamber (5) is provided with a first inlet valve (11) and a first outlet valve (13) below it, and said second high-pressure pump chamber (6) is provided with a second inlet valve (12) and a second outlet valve (14) below it.