CN211336490U

CN211336490U - Piston type propellant storage tank for spacecraft power system

Info

Publication number: CN211336490U
Application number: CN202021372111.2U
Authority: CN
Inventors: 不公告发明人
Original assignee: Xi'an Sky Engine Technology Co ltd
Current assignee: Xi'an Sky Engine Technology Co ltd
Priority date: 2020-07-14
Filing date: 2020-07-14
Publication date: 2020-08-25
Anticipated expiration: 2030-07-14

Abstract

The utility model discloses a piston propellant storage tank for spacecraft power system, including the inside air cavity casing that is formed with the air cavity and one end is the air cavity open-ended and the inside sap cavity casing that is formed with the sap cavity and one end is the sap cavity open-ended, the open end of air cavity casing and the open end sealing connection of sap cavity casing, air cavity and sap cavity are the cylindrical appearance chamber and the diameter of air cavity is less than the diameter of sap cavity, the sliding is equipped with the piston in the sap cavity, the external diameter of piston is the same with the diameter of sap cavity, and be equipped with the sealing washer between piston and the sap cavity casing, and the external diameter of piston is greater than the diameter of air cavity, be equipped with air cavity filling outlet on the air cavity casing, the one end of keeping away from the sap cavity open-ended is equipped with; the piston is limited by the different diameters of the air cavity and the liquid cavity, a piston rod structure of the transmission piston is omitted, the processing difficulty and the production cost of parts are reduced, the overall weight of the storage tank is reduced, the number of holes in the storage tank is reduced, and the sealing performance of the storage tank is improved.

Description

Piston type propellant storage tank for spacecraft power system

Technical Field

The utility model belongs to spacecraft driving system field especially relates to a piston propellant storage tank for spacecraft driving system.

Background

The propellant storage tank is a device for managing and controlling the propellant in a spacecraft power system, has the function of providing the engine with the continuously flowing propellant without gas inclusion, and can be divided into a capsule type storage tank, a diaphragm type storage tank, a piston type storage tank, a surface tension storage tank and the like according to the propellant management and control mode, wherein the piston type storage tank is widely applied to the spacecraft power system due to the characteristics of high emptying efficiency, long service life and the like.

The existing piston type propellant storage tank generally comprises a liquid cavity shell, an air cavity end enclosure, a piston, a sealing device and the like, wherein the liquid cavity shell is connected with the air cavity end enclosure in a welding mode, pressurized gas (air cavity) and propellant (liquid cavity) are isolated by the sealing device at the head of the piston, when the piston works, the piston realizes forward propelling movement by means of the pressure of the air cavity and outputs the propellant from the storage tank, the piston type propellant storage tank generally comprises two sealing devices, the sealing device at the head of the piston realizes gas-liquid separation in the storage tank, the sealing device at the rod part of the piston ensures the sealing performance inside and outside the storage tank, the sealing device is generally a sealing ring, in order to obtain reliable sealing performance and ensure the flexibility of the piston movement, the requirements on the processing precision, the surface roughness and the like of the outer surface of the piston and the inner surface of the liquid cavity shell are very high, and the, the cost is high, in the welding process of the liquid cavity shell and the air cavity end enclosure, in order to prevent and reduce adverse effects caused by welding thermal deformation on the sealing performance of the sealing device and the motion flexibility of the piston, the welding process has high requirements, and in addition, the propellant storage tank cannot be decomposed, maintained and maintained in the later period due to the adoption of a welding connection form.

Disclosure of Invention

The utility model aims to overcome current technical defect, provide a piston propellant storage tank for spacecraft driving system, utilize the different diameter of air cavity and sap cavity to carry on spacingly to the piston, cancelled the piston rod structure of transmission piston, reduced the processing degree of difficulty and the manufacturing cost of part, alleviateed the whole weight of storage tank, still reduced the trompil quantity on the storage tank, increased the sealing performance of storage tank.

In order to solve the technical problem, the utility model provides a piston propellant storage tank for spacecraft driving system, be formed with air cavity and one end for air cavity open-ended air cavity casing and inside be formed with sap cavity and one end for sap cavity open-ended sap cavity casing including inside, the open end of air cavity casing with the open end sealing connection of sap cavity casing, air cavity and sap cavity are columniform appearance chamber, just the diameter of air cavity is less than the diameter of sap cavity, it is equipped with the piston to slide in the sap cavity, be equipped with the sealing washer between piston and the sap cavity casing, just the external diameter of piston is greater than the diameter of air cavity, be equipped with the air cavity filling outlet with the air cavity intercommunication on the air cavity casing, the sap cavity open-ended one end of keeping away from on the sap cavity casing is equipped with the sap cavity filling outlet with the sap cavity intercommunication.

Further, the piston is in a U shape with an opening facing the air chamber.

Further, the shape of the inner end surface of the liquid chamber is the same as the shape of the outer end surface of the piston.

Further, the end surface of the inner side of the liquid cavity and the end surface of the outer side of the piston are spherical surfaces with the same curvature radius.

Further, the surface roughness of the inner wall of the liquid cavity and the surface roughness of the periphery of the piston are both less than 0.8 μm; the cylindricity of liquid chamber inner wall and the cylindricity of piston periphery all is less than 0.01 mm.

Furthermore, the front end of the air cavity shell is provided with a boss which is inserted into the liquid cavity and takes the shape of a ring, and a sealing gasket is arranged between the liquid cavity shell and the boss.

Furthermore, the periphery of the piston is provided with at least one annular groove, the sealing ring is sleeved in the groove, and the periphery of the sealing ring protrudes out of the peripheral surface of the piston.

Furthermore, a check ring positioned on one side of the sealing ring is arranged in the groove.

Furthermore, the periphery of the opening end of the air cavity shell radially protrudes and extends to form a first flange, the periphery of the opening end of the liquid cavity shell radially protrudes and extends to form a second flange, and the first flange is fixedly connected with the second flange through bolts.

Furthermore, be equipped with a plurality of through-holes on the first flange, be equipped with on the second flange a plurality of with the perforation of through-hole one-to-one, the bolt passes in proper order perforation and through-hole and through nut cooperation fixed connection.

The utility model discloses following beneficial effect has:

the utility model limits the piston by utilizing the different inner diameters of the air cavity and the liquid cavity, thereby canceling the piston rod structure of the transmission piston, reducing the precision structure and the size range of the propellant storage tank, effectively reducing the processing difficulty and the production cost of parts, reducing the whole weight of the propellant storage tank, reducing the number of holes on the liquid cavity shell and increasing the sealing performance of the liquid cavity shell; the shape of the end surface of the outer side of the piston is designed to be the same as the shape of the end surface of the inner cavity of the liquid cavity shell, so that the liquid discharge efficiency of the propellant storage box can be improved; and the flange structure is used for fixing the air cavity shell and the liquid cavity shell, so that the installation and the disassembly are convenient, the propellant storage tank has good maintainability, and meanwhile, the flange structure connection can also improve the rigidity of the propellant storage tank, thereby being beneficial to ensuring the sealing performance and the flexibility of the piston movement at each position.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, do not constitute a limitation of the invention, and in which:

FIG. 1 is a schematic illustration of a piston type propellant tank for a spacecraft power system in an embodiment;

FIG. 2 is an enlarged view of portion A of FIG. 1;

FIG. 3 is a schematic view of an air cavity enclosure in an embodiment;

FIG. 4 is a schematic view of a liquid chamber housing in an embodiment.

Detailed Description

For a fuller understanding of the technical content of the present invention, the present invention will be further described and illustrated with reference to the accompanying drawings and specific embodiments.

Examples

As shown in fig. 1-4, the piston type propellant tank for a spacecraft power system shown in this embodiment includes a cylindrical air cavity housing 1 and a cylindrical liquid cavity housing 2, an air cavity 10 is formed in the air cavity housing 1, a liquid cavity 20 is formed in the liquid cavity housing 2, an air cavity opening 11 is provided at the right end of the air cavity housing 1, a liquid cavity opening 21 is provided at the left end of the liquid cavity housing 2, the open end of the air cavity housing 1 and the open end of the liquid cavity housing 2 are hermetically connected to form an outer shell of the propellant tank, the diameter of the air cavity 10 is smaller than that of the liquid cavity 20, a circle of step 4 is formed at the position where the air cavity opening 11 and the liquid cavity opening 21 contact, a piston 3 is slidably provided in the liquid cavity 20, the diameter of the periphery of the piston 3 is the same as the inner diameter of the liquid cavity housing 2, a sealing ring is provided between the piston 3 and the liquid cavity housing 2, a liquid cavity filling and discharging port 23 is arranged on the liquid cavity shell 2; in the structure, before the propellant is filled, the liquid cavity filling and discharging port 23 is opened, gas with certain pressure is introduced into the gas cavity 10 through the gas cavity filling and discharging port 13, the piston 3 moves to the rightmost end position of the liquid cavity 20 to ensure that the air in the liquid cavity 20 is discharged, then the gas cavity filling and discharging port 13 is opened, the propellant is filled into the liquid cavity 20 from the liquid cavity filling and discharging port 23, the piston 3 moves leftwards in the filling process, the step 4 plays a limiting role due to the existence of the step 4, when the piston 3 slides to the leftmost end in the liquid cavity 20, the piston 3 is blocked by the step 4 to realize the limiting of the piston 3, at the moment, the liquid cavity filling and discharging port 23 is closed, then high-pressure gas is filled into the gas cavity 10, and when the engine works, the high-pressure gas is used for pushing the piston 3 to move, and the propellant is output from the liquid cavity filling and discharging port 23.

Specifically, the piston 3 is a U-shaped piston with an opening facing the air cavity 10, the end surface of the inner cavity of the liquid cavity shell 2 and the end surface of the outer side of the piston 3 are spherical surfaces with the same curvature radius, the liquid cavity filling and discharging port 23 is positioned at the central position of the end surface of the liquid cavity shell 2, the end surface of the inner cavity of the air cavity shell 1 is spherical, and the air cavity filling and discharging port 13 is positioned at the central position of the end surface of the air cavity shell 1; the U-shaped piston 3 can enable the piston to be pushed by gas in the gas cavity 10 more easily, the curvature of the end face of the inner cavity of the liquid cavity shell 2 is the same as that of the end face of the outer side of the piston 3, so that when the piston 3 moves to the rightmost end of the liquid cavity shell 2, the end face of the outer side of the piston 3 is completely attached to the end face of the inner cavity of the liquid cavity shell 2, the volume of the liquid cavity 20 is minimum, and the liquid drainage efficiency can be improved; the air cavity filling and discharging port 13 and the liquid cavity filling and discharging port 23 are respectively positioned at the central positions of the end surfaces of the air cavity shell 1 and the liquid cavity shell 2, and the filling and discharging efficiency of the air cavity 10 and the liquid cavity 20 can be improved.

Specifically, the fit tolerance of the inner wall of the liquid cavity shell 2 and the outer wall fitting surface of the piston 3 is H8/d7, the surface roughness of the inner wall of the liquid cavity shell 2 and the surface roughness of the periphery of the piston 3 are both smaller than 0.8 μm, the cylindricity of the inner wall of the liquid cavity shell 2 and the cylindricity of the periphery of the piston 3 are both smaller than 0.01mm, so that the sealing performance between the air cavity 10 and the liquid cavity 20 can be ensured, the backflow of gas or propellant in the air cavity 10 and the liquid cavity 20 between the air cavity 10 and the liquid cavity 20 can be prevented, the flexibility of the movement of the piston 3 in the liquid cavity shell 2 can be ensured simultaneously, the piston 3 can slide in the liquid cavity shell 2 smoothly, and the piston 3 cannot be clamped when sliding in the liquid cavity shell 2.

Specifically, a circle of annular bosses 16 are arranged at the front end of an air cavity opening 11 on the air cavity shell 1, a circle of concave platforms 26 corresponding to the bosses 16 are arranged at the front end of a liquid cavity opening 21 on the liquid cavity shell 2, and a sealing gasket 43 is arranged between the bosses 16 and the concave platforms 26; when the gas cavity opening 11 is aligned with the liquid cavity opening 21 and the first flange 14 and the second flange 24 are fixedly connected through the matching of the bolt 41 and the nut 42, the boss 16 extends into the concave platform 26 corresponding to the boss and presses the sealing gasket 43, the contact surface of the gas cavity opening 11 and the liquid cavity opening 21 is non-planar through the matching of the boss 16 and the concave platform 26, after the first flange 14 and the second flange 24 are fixedly connected through the matching of the bolt 41 and the nut 42, the rigidity of the propellant storage tank can be improved through the non-planar contact mode, and the sealing performance of the propellant storage tank is improved through the sealing gasket 43.

Specifically, a first annular groove 31 and a second annular groove 32 are provided at positions where the outer periphery of the piston 3 contacts the chamber housing 2, the first sealing ring 33 and the first retainer ring 34 are arranged in the first groove 31, the second sealing ring 35 and the second retainer ring 36 are arranged in the second groove 32, the sealing performance between the piston 3 and the liquid cavity shell 2 can be improved due to the existence of the first sealing ring 33 and the second sealing ring 35, gas in the gas cavity 10 can be prevented from entering the liquid cavity 20, propellant in the liquid cavity 20 can also be prevented from entering the gas cavity 10, the first retainer ring 34 and the second retainer ring 36 can play a limiting role for the first sealing ring 33 and the second sealing ring 35, and the first sealing ring 33 and the second sealing ring 35 are prevented from being rolled into a gap between the piston 3 and the liquid cavity shell 2 to damage the first sealing ring 33 and the second sealing ring 35 when the piston 3 moves in the liquid cavity shell 2.

Specifically, the periphery of the piston 3 is located between the first groove 31 and the second groove 32, a third groove 37 is further arranged, the depth of the third groove 37 is smaller than the depths of the first groove 31 and the second groove 32, a fourth groove 38 is arranged at the lower end of the inner periphery of the piston 3 corresponding to the third groove 37, the third groove 37 can ensure that the guide length of the piston 3 is not changed, the contact area between the piston 3 and the liquid cavity shell 2 is reduced, the piston 3 is prevented from being clamped and blocked when sliding in the liquid cavity shell 2, the fourth groove 38 can increase the thrust of the piston 3, and the third groove 37 and the fourth groove 38 can also reduce the overall quality of the propellant storage box.

Specifically, a first flange 14 is arranged on the air cavity shell 1 and positioned outside an air cavity opening 11 in an outward extending manner, a second flange 24 is arranged on the liquid cavity shell 2 and positioned outside a liquid cavity opening 21 in an outward extending manner, a plurality of through holes 15 are formed in the first flange 14, a plurality of through holes 25 corresponding to the through holes 15 in a one-to-one manner are formed in the second flange 24, and the first flange 14 and the second flange 24 sequentially penetrate through the through holes 25 and the through holes 15 through bolts 41 and then are fixedly connected with nuts 42 in a matched manner; through adopting the flange structure between liquid chamber casing 2 and air cavity casing 1, utilize the cooperation of bolt 41 and nut 42 with first flange 14 and second flange 24 fixed connection, can guarantee the leakproofness between liquid chamber casing 2 and the air cavity casing 1, can reduce welding heat altered shape and cause adverse effect to sealing device's sealing performance, and simultaneously, the dismouting of being convenient for through flange joint's structure, make propellant storage tank have good maintainability, and simultaneously, flange structural connection can also improve propellant storage tank's rigidity, be favorable to guaranteeing the flexibility of leakproofness and piston motion everywhere.

The utility model discloses an in other embodiments, the material of first sealing washer and second sealing washer is rubber, and the material of first retaining ring and second retaining ring is fluoroplastics.

The technical solutions provided by the embodiments of the present invention are described in detail above, and the principles and embodiments of the present invention are explained herein by using specific examples, and the descriptions of the above embodiments are only applicable to help understand the principles of the embodiments of the present invention; meanwhile, for a person skilled in the art, according to the embodiments of the present invention, there may be variations in the specific implementation manners and application ranges, and in summary, the content of the description should not be construed as a limitation to the present invention.

Claims

1. The piston type propellant storage tank for the spacecraft power system is characterized by comprising an air cavity shell and a liquid cavity shell, wherein an air cavity is formed inside the air cavity shell, one end of the air cavity shell is provided with an air cavity opening, a liquid cavity is formed inside the liquid cavity shell, one end of the liquid cavity shell is provided with a liquid cavity, the open end of the air cavity shell is hermetically connected with the open end of the liquid cavity shell, the air cavity and the liquid cavity are both cylindrical containing cavities, the diameter of the air cavity is smaller than that of the liquid cavity, a piston is arranged in the liquid cavity in a sliding mode, a sealing ring is arranged between the piston and the liquid cavity shell, the outer diameter of the piston is larger than that of the air cavity, an air cavity filling and discharging port communicated with the air cavity is arranged on the air cavity shell, and a liquid cavity filling and discharging port communicated with the.

2. The piston-type propellant tank for a spacecraft power system of claim 1, wherein said piston is U-shaped with an opening facing said air cavity.

3. A piston-type propellant tank for a spacecraft power system as claimed in claim 2, wherein a shape of an inside end face of said liquid chamber is the same as a shape of an outside end face of said piston.

4. The piston-type propellant tank for a spacecraft power system of claim 3, wherein said inboard end surface of said liquid chamber and said outboard end surface of said piston are spherical surfaces having the same radius of curvature.

5. The piston-type propellant tank for spacecraft power systems of claim 4, wherein a surface roughness of an inner wall of said liquid chamber and a surface roughness of an outer periphery of said piston are each less than 0.8 μm; the cylindricity of liquid chamber inner wall and the cylindricity of piston periphery all is less than 0.01 mm.

6. A piston type propellant tank for a spacecraft power system as claimed in any one of claims 1 to 5, wherein said air cavity housing is provided at a front end thereof with a boss inserted into said liquid cavity and having a ring shape, and a gasket is provided between said liquid cavity housing and said boss.

7. The piston-type propellant tank for a spacecraft power system of claim 6, wherein said piston is provided with at least one annular groove on an outer periphery thereof, said sealing ring is fitted in said groove, and an outer periphery of said sealing ring protrudes from an outer peripheral surface of said piston.

8. The piston-type propellant tank for a spacecraft power system of claim 7, wherein a retaining ring is disposed in said groove on a side of said seal ring.

9. The piston-type propellant tank for spacecraft power systems of claim 8, wherein a first flange is radially protruded from an outer periphery of the open end of said air cavity housing, a second flange is radially protruded from an outer periphery of the open end of said liquid cavity housing, and said first flange and said second flange are fixedly connected by bolts.

10. The piston-type propellant tank for a spacecraft power system as claimed in claim 9, wherein said first flange is provided with a plurality of through holes, said second flange is provided with a plurality of through holes corresponding to said through holes one to one, and said bolts are sequentially inserted through said through holes and fixedly connected thereto by nuts.