Upper stage power system of carrier rocket

Abstract

The invention provides an upper stage power system of a carrier rocket. The upper stage power system comprises an annular gas cylinder, an annular common-bottom double-film storage tank, an electric explosion valve, a pressure reducing valve, a safety valve, a fuel liquid path diaphragm valve, a fuel filling valve, an oxidant liquid path diaphragm valve, an oxidant filling valve, an orbit control engine and an attitude control engine. And the annular common-bottom double-membrane storage tank is connected with the annular gas cylinder through a pipeline. The annular common-bottom double-membrane storage tank comprises a fuel liquid cavity shell, an oxidant liquid cavity shell, a gas cavity shell, a fuel membrane and an oxidant membrane; the fuel liquid cavity shell is connected with the oxidant liquid cavity shell through the gas cavity shell to form an outer shell of the annular common-bottom double-membrane storage tank; and the fuel diaphragm and the oxidant diaphragm are arranged in the annular common-bottom double-diaphragm storage tank to form an upper-layer annular space and a lower-layer annular space. The system structure efficiency and the space utilization rate are improved, an independent sinking system can be omitted, the utilization rate of propellants is improved, long-term on-orbit sliding of the upper stage is achieved, and the carrying capacity and the launching efficiency of the carrier rocket are improved.

Description

Technical Field

[0001] The present application relates to the technical field of launch vehicle upper stages, and in particular to a launch vehicle upper stage power system. Background Art

[0002] The upper stage of a traditional launch vehicle usually adopts a spherical, spherical (ellipsoidal) cylindrical double-bottom tank, or spherical (ellipsoidal) cylindrical common-bottom tank in parallel. During the operation of the upper stage in orbit, it needs to experience a long period of on-orbit gliding and multiple starts of the main engine. Under the microgravity conditions of space, the propellant needs to be managed to ensure that the delivery system provides it with non-air-entrained propellant when the main engine is started again after a long period of gliding.

[0003] The launch vehicle upper stage in the prior art has the following defects:

[0004] First, if a spherical or spherical (ellipsoidal) cylindrical double-bottom tank is used in series layout, or a spherical or spherical (ellipsoidal) cylindrical common-bottom tank is used, the envelope in the height direction is difficult to meet the space layout requirements of the upper stage; if a spherical or spherical (ellipsoidal) cylindrical double-bottom tank is used in parallel layout, the envelope in the diameter direction is difficult to meet the space layout requirements of the upper stage. For upper stages with large propellant mass, the above-mentioned schemes all have the disadvantages of low structural efficiency and low space utilization.

[0005] Second, if a continuous and intermittent bottom-sinking propellant management scheme is adopted, an additional system for sinking to the bottom is required, which increases the weight of the upper stage system and reduces the reliability of the upper stage power system. The continuous bottom-sinking propellant management scheme consumes more propellant and cannot adapt to the upper stage's gliding missions that can last for hours or days.

[0006] Therefore, the technical problem that urgently needs to be solved is: how to provide a launch vehicle upper stage power system, improve the structural efficiency and space utilization of the upper stage power system through the layout of annular gas cylinders and annular common bottom double membrane tanks, and provide a non-gas-entrained propellant supply throughout the mission cycle through the annular common bottom double membrane tank. By controlling the diaphragm thickness gradient, the synchronization of fuel and oxidizer supply can be ensured, the utilization rate of the propellant can be improved, the long-term on-orbit gliding of the upper stage and the multiple starting function requirements of the main engine can be realized, as well as the carrying capacity and launch efficiency of the launch vehicle can be improved. Summary of the invention

[0007] The purpose of the present application is to provide a launch vehicle upper stage power system, which improves the structural efficiency and space utilization of the upper stage power system through the layout of annular gas cylinders and annular common bottom double membrane tanks, and can provide a non-air entrained propellant supply throughout the mission cycle through the annular common bottom double membrane tank. By controlling the diaphragm thickness gradient, the synchronization of fuel and oxidizer supply is ensured, the utilization rate of the propellant is improved, the long-term on-orbit gliding of the upper stage and the multiple starting function requirements of the main engine are realized, and the carrying capacity and launch efficiency of the launch vehicle are improved.

[0008] To achieve the above-mentioned purpose, the present application provides a launch vehicle upper stage power system, including: an annular gas cylinder, an annular common bottom double membrane tank, an electric explosion valve, a pressure reducing valve, a safety valve, a fuel liquid circuit diaphragm valve, a fuel filling valve, an oxidizer liquid circuit diaphragm valve, an oxidizer filling valve, a track control engine and an attitude control engine; the annular common bottom double membrane tank is connected to the annular gas cylinder through a pipeline; the annular common bottom double membrane tank includes: a fuel liquid chamber shell, an oxidizer liquid chamber shell, an air chamber shell, a fuel diaphragm, an oxidizer diaphragm, a fuel diaphragm support ring and an oxidizer diaphragm support ring; the fuel liquid chamber shell is connected to the oxidizer liquid chamber shell through the air chamber shell to form an outer shell of the annular common bottom double membrane tank; the fuel diaphragm and the oxidizer diaphragm are arranged inside the annular common bottom double membrane tank, and the fuel diaphragm, the fuel diaphragm support ring and the fuel liquid chamber shell form an upper annular space for storing fuel; The oxidant diaphragm, the oxidant diaphragm support ring and the oxidant liquid cavity shell form a lower annular space for storing the oxidant; the fuel diaphragm, the oxidant diaphragm, the fuel diaphragm support ring, the oxidant diaphragm support ring and the air cavity shell form an air cavity; the fuel diaphragm is connected to the fuel liquid cavity shell and the air cavity shell through the fuel diaphragm support ring; the oxidant diaphragm is connected to the oxidant diaphragm support ring and then to the oxidant liquid cavity shell and the air cavity shell; the annular gas cylinder is connected to the air cavity and is used to introduce gas into the air cavity. By adjusting the pressure of the gas introduced into the air cavity, the fuel diaphragm and the oxidant diaphragm are controlled to flip from top to bottom or from bottom to top, thereby changing the volume of the upper annular space and the lower annular space; the annular common bottom double membrane tank is connected to a track control engine and an attitude control engine downstream.

[0009] The launch vehicle upper stage power system as described above, wherein the annular common bottom double membrane tank is provided with an air inlet nozzle, one end of the air inlet nozzle is connected with the annular gas cylinder through an air inlet pipeline, and the other end is connected with the air cavity; an air path diaphragm valve, a vent nozzle and a gas diverter are provided at one end of the air inlet pipeline close to the air inlet nozzle.

[0010] The launch vehicle upper stage power system as described above, wherein a fuel outlet is arranged at the top of the annular common bottom double membrane tank, and an oxidant outlet is arranged at the bottom; the fuel outlet is communicated with the upper annular space, and the oxidant outlet is communicated with the lower annular space; a fuel liquid circuit diaphragm valve and a fuel filling valve are integratedly installed at the fuel outlet; an oxidant liquid circuit diaphragm valve and an oxidant filling valve are integratedly installed at the oxidant outlet.

[0011] The launch vehicle upper stage power system as described above, wherein the fuel diaphragm includes: a fuel diaphragm connecting ring, a first fuel diaphragm arc segment, a fuel diaphragm pre-flanged edge and a second fuel diaphragm arc segment; one end of the fuel diaphragm connecting ring is connected to the outer shell of the annular common bottom double membrane tank, and the other end is connected to the first fuel diaphragm arc segment; the end of the first fuel diaphragm arc segment away from the fuel diaphragm connecting ring is connected to the second fuel diaphragm arc segment through the fuel diaphragm pre-flanged edge.

[0012] The launch vehicle upper stage power system as described above, wherein the second fuel diaphragm arc segment adopts a uniform cross-sectional thickness; the thickness of the first fuel diaphragm arc segment gradually decreases from top to bottom; the thickness of the fuel diaphragm connecting ring is consistent with the thickness of the upper end of the first fuel diaphragm arc segment; the thickness of the fuel diaphragm pre-flange is consistent with the thickness of the lower end of the first fuel diaphragm arc segment.

[0013] The launch vehicle upper stage power system as described above, wherein the oxidizer diaphragm includes: an oxidizer diaphragm pre-flanged edge and an oxidizer diaphragm arc segment; one end of the oxidizer diaphragm pre-flanged edge is connected to the outer shell of the annular common bottom double membrane tank, and the other end is connected to the oxidizer diaphragm arc segment.

[0014] In the launch vehicle upper stage power system as described above, the oxidizer diaphragm arc segment adopts a variable cross-sectional thickness, and its thickness gradually increases from bottom to top; the thickness of the oxidizer diaphragm pre-flange is consistent with the thickness of the lower end of the oxidizer diaphragm arc segment.

[0015] The launch vehicle upper stage power system as described above, wherein a fuel anti-blocking cap is provided at the fuel outlet, and an oxidant anti-blocking cap is provided at the oxidant outlet, and the anti-blocking cap is an annular spherical cap porous structure.

[0016] In the launch vehicle upper stage power system as described above, the gas diverter is a hollow frustum structure, and a plurality of diverter circular holes are distributed along the circumference of the hollow frustum structure; the gas diverter is fixedly connected to the air cavity shell.

[0017] In the launch vehicle upper stage power system as described above, an electric explosion valve, a pressure reducing valve and a safety valve are sequentially arranged on the pipeline connecting the annular gas cylinder and the annular common bottom double membrane tank.

[0018] The beneficial effects achieved by this application are as follows:

[0019] (1) The present application uses an annular gas cylinder and an annular common bottom double membrane tank, and combines the existing separately arranged fuel and oxidant tanks into the annular common bottom double membrane tank, which can improve the structural efficiency and space utilization.

[0020] (2) The present application uses the annular double-membrane common bottom tank to adopt an active propellant management method. An air cavity is formed between the fuel diaphragm, the fuel diaphragm support ring, the oxidizer diaphragm, the oxidizer diaphragm support ring and the air cavity shell; the annular gas cylinder is connected to the air cavity and is used to introduce gas into the air cavity. By adjusting the pressure of the gas introduced into the air cavity, the fuel diaphragm and the oxidizer diaphragm are controlled to flip from top to bottom or from bottom to top, thereby changing the volume of the upper annular space and the lower annular space, and a separate bottom sinking system can be eliminated; by controlling the diaphragm thickness gradient, the synchronization of fuel and oxidizer supply is ensured, the utilization rate of propellant is improved, and the functional requirements of long-term on-orbit gliding of the upper stage and multiple starts of the main engine are realized.

[0021] (3) The present application can be used for both normal temperature propellant upper stages and low temperature propellant upper stages. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0023] Figure 1 This is a schematic diagram of the structure of a launch vehicle upper stage power system according to an embodiment of the present application.

[0024] Figure 2 This is a bottom view of a launch vehicle upper stage power system according to an embodiment of the present application.

[0025] Figure 3 This is an appearance diagram of an annular common-bottom double-membrane tank and orbit control engine of a launch vehicle upper stage power system in an embodiment of the present application.

[0026] Figure 4 This is a schematic diagram of a fuel membrane according to an embodiment of the present application.

[0027] Figure 5 This is a schematic diagram of an oxidant membrane according to an embodiment of the present application.

[0028] Figure 6 This is a schematic diagram of the welding of the fuel membrane and the oxidant membrane according to an embodiment of the present application.

[0029] Figure 7 This is a schematic diagram of the splitter structure of an embodiment of the present application.

[0030] Figure 8 This is a schematic diagram of the anti-blocking cap structure of an embodiment of the present application.

[0031] Figure numerals: 1-annular gas cylinder; 2-electric explosion valve; 3-pressure reducing valve; 4-safety valve; 5-annular common bottom double membrane storage tank; 6-gas circuit diaphragm valve; 7-fuel liquid circuit diaphragm valve; 8-fuel filling valve; 9-oxidant liquid circuit diaphragm valve; 10-oxidant filling valve; 51-fuel diaphragm; 52-oxidant diaphragm; 53-fuel liquid chamber housing; 54-oxidant liquid chamber housing; 55-gas chamber housing; 56-gas diverter; 57-fuel anti-blocking cap; 58- Oxidizer anti-blocking cap; 59-ventilation nozzle; 11-track control engine; 12-attitude control engine; 511-fuel diaphragm connecting ring; 512-first fuel diaphragm arc segment; 513-fuel diaphragm pre-flanged edge; 514-second fuel diaphragm arc segment; 515-fuel diaphragm support ring; 521-oxidizer diaphragm pre-flanged edge; 522-oxidizer diaphragm arc segment; 523-oxidizer diaphragm support ring; 561-diverter circular hole; 571-anti-blocking cap circular hole. DETAILED DESCRIPTION

[0032] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0033] like Figure 1-8As shown, the present application provides a launch vehicle upper stage power system, including: an annular gas cylinder 1, an annular common bottom double membrane tank 5; the annular common bottom double membrane tank 5 is connected to the annular gas cylinder 1 through a pipeline; the annular common bottom double membrane tank 5 includes: a fuel liquid chamber shell 53, an oxidant liquid chamber shell 54, an air chamber shell 55, a fuel diaphragm 51 and an oxidant diaphragm 52; the fuel liquid chamber shell 53 is connected to the oxidant liquid chamber shell 54 through the air chamber shell 55 to form an outer shell of the annular common bottom double membrane tank 5; the fuel diaphragm 51 and the oxidant diaphragm 52 are arranged inside the annular common bottom double membrane tank 5, and the fuel diaphragm 51, the fuel diaphragm support ring 515 and the fuel liquid chamber shell 53 form a The upper annular space for storing fuel; the oxidant diaphragm 52, the oxidant diaphragm support ring 523 and the oxidant liquid chamber shell 54 form a lower annular space for storing oxidant; the fuel diaphragm 51, the fuel diaphragm support ring 515, the oxidant diaphragm 52, the oxidant diaphragm support ring 523 and the air chamber shell 55 form an air chamber; the annular gas cylinder 1 is connected to the air chamber, and is used to pass gas into the air chamber. By adjusting the pressure of the gas passed into the air chamber, the fuel diaphragm 51 and the oxidant diaphragm 52 are controlled to flip from top to bottom or from bottom to top, thereby changing the volume of the upper annular space and the lower annular space; the annular common bottom double membrane tank 5 is connected to the orbit control engine 11 and the attitude control engine 12. The upper annular space and the lower annular space of the annular common bottom double membrane tank 5 are both connected to the orbit control engine 11 and the attitude control engine 12, and provide fuel and oxidant to the orbit control engine 11 and the attitude control engine 12.

[0034] like Figure 1 As shown, an electric explosion valve 2, a pressure reducing valve 3 and a safety valve 4 are sequentially arranged on the pipeline connecting the annular gas cylinder 1 and the annular common bottom double membrane storage tank 5.

[0035] As a specific embodiment of the present invention, the layout of the upper stage power system of the present application is as follows: with the orbit control engine 11 as the center, an annular gas cylinder 1 and an annular common bottom double membrane tank 5 are arranged from the inside to the outside in sequence on the upper side. The annular gas cylinder 1 is annular, and the inside of the annular gas cylinder 1 is a cavity for containing gas. The middle of the annular gas cylinder 1 is hollow and can be used to arrange multiple system components. The hollow part of the annular gas cylinder 1 is arranged with an electric explosion valve 2, a pressure reducing valve 3, and a safety valve 4 to save space and improve the compactness of the structure. The attitude control engine 12 is arranged below the annular common bottom double membrane tank 5.

[0036] like Figure 1-3 As shown, the orbit control engine 11 is arranged at the bottom center of the annular common bottom double membrane tank 5; the attitude control engine 12 is arranged at the bottom of the annular common bottom double membrane tank 5, and is arranged around the outer peripheral side of the orbit control engine 11, and every two attitude control engines 12 are arranged opposite to each other to adjust the aircraft attitude more reliably and stably.

[0037] like Figure 1As shown, the annular common bottom double membrane storage tank 5 is provided with an air inlet nozzle, one end of which is connected to the annular gas cylinder 1 through an air inlet pipeline, and the other end is connected to the air cavity; an air circuit diaphragm valve 6, a vent nozzle 59 and a gas diverter 56 are provided at one end of the air inlet pipeline close to the air inlet nozzle.

[0038] As a preferred embodiment of the present invention, the annular common bottom double membrane storage tank 5 has 4 to 6 air inlet nozzles evenly distributed at the equatorial position. The air path diaphragm valve 6 and the vent nozzle 59 are integrated and installed at the air inlet nozzle.

[0039] As a specific embodiment of the present invention, a fuel outlet is arranged at the top of the annular common bottom double membrane storage tank 5, and an oxidant outlet is arranged at the bottom; the fuel outlet is connected to the upper annular space, and the oxidant outlet is connected to the lower annular space; a fuel liquid circuit diaphragm valve 7 and a fuel filling valve 8 are integratedly installed at the fuel outlet; an oxidant liquid circuit diaphragm valve 9 and an oxidant filling valve 10 are integratedly installed at the oxidant outlet.

[0040] like Figure 4 As shown, the fuel diaphragm 51 includes: a fuel diaphragm connecting ring 511, a first fuel diaphragm circular arc segment 512, a fuel diaphragm pre-flange 513 and a second fuel diaphragm circular arc segment 514; one end of the fuel diaphragm connecting ring 511 is connected to the outer shell of the annular common bottom double membrane storage tank 5, and the other end is connected to the first fuel diaphragm circular arc segment 512; one end of the first fuel diaphragm circular arc segment 512 away from the fuel diaphragm connecting ring 511 is connected to the second fuel diaphragm circular arc segment 514 through the fuel diaphragm pre-flange 513.

[0041] As a preferred embodiment of the present invention, the profiles of the components of the fuel diaphragm 51 are tangent, that is, the profiles of the fuel diaphragm connecting ring 511, the first fuel diaphragm arc segment 512, the fuel diaphragm pre-flange 513 and the second fuel diaphragm arc segment 514 are tangent. Since the second fuel diaphragm arc segment 514 does not participate in the metal diaphragm flipping process, a uniform cross-sectional thickness design is adopted. In order to control the stability of the diaphragm flipping process, the remaining cross-sectional thickness design is adopted. The thickness of the first fuel diaphragm arc segment 512 gradually decreases from top to bottom, the fuel diaphragm connecting ring 511 is consistent with the thickness of the upper end of the first fuel diaphragm arc segment 512, and the fuel diaphragm pre-flange 513 is consistent with the thickness of the lower end of the first fuel diaphragm arc segment 512. The radius R3 of the first fuel diaphragm arc segment 512 and the radius R1 of the second fuel diaphragm arc segment 514 are matched with the radius of the fuel liquid chamber shell. The radius r0 of the fuel diaphragm connecting ring 511 is matched with the radius R3 of the first fuel diaphragm arc segment 512. The radius r1 of the fuel diaphragm pre-flange 513 matches the radius R3 of the first fuel diaphragm circular arc segment 512 and the radius R1 of the second fuel diaphragm circular arc segment 514 .

[0042] As a specific embodiment of the present invention, the second fuel diaphragm arc segment 514 adopts a uniform cross-sectional thickness; the thickness of the first fuel diaphragm arc segment 512 gradually decreases from top to bottom; the thickness of the fuel diaphragm connecting ring 511 is consistent with the thickness of the upper end of the first fuel diaphragm arc segment 512; the thickness of the fuel diaphragm pre-flange 513 is consistent with the thickness of the lower end of the first fuel diaphragm arc segment 512.

[0043] like Figure 5 As shown, the oxidant diaphragm 52 includes: an oxidant diaphragm pre-flange 521 and an oxidant diaphragm arc segment 522; one end of the oxidant diaphragm pre-flange 521 is connected to the outer shell of the annular common bottom double membrane storage tank 5, and the other end is connected to the oxidant diaphragm arc segment 522.

[0044] As a specific embodiment of the present invention, in order to control the stability of the membrane flipping process, the oxidant diaphragm arc segment 522 adopts a variable cross-sectional thickness design, and the thickness gradually increases from bottom to top. The radius R2 of the oxidant diaphragm arc segment 522 is matched with the radius of the oxidant liquid chamber housing 54. The radius r2 of the oxidant diaphragm pre-flange 521 is matched with the radius R2 of the oxidant diaphragm arc segment 522.

[0045] As a specific embodiment of the present invention, the contact part of the fuel diaphragm support ring 515 and the fuel connection ring 511 is conformed, and the end of the fuel connection ring 511 is connected to the fuel diaphragm support ring 515. The fuel diaphragm support ring 515 is connected to the fuel liquid cavity shell 53 and the gas cavity shell 55. The contact part of the oxidant diaphragm support ring 515 and the oxidant diaphragm pre-flange 521 is conformed, and the end of the oxidant diaphragm pre-flange 521 is connected to the oxidant diaphragm support ring 515. The oxidant diaphragm support ring 515 is connected to the oxidant liquid cavity shell 54 and the gas cavity shell 55.

[0046] As a preferred embodiment of the present invention, in order to ensure the synchronization of the turning time of the fuel diaphragm 51 and the oxidant diaphragm 52 , the thickness gradient of the oxidant diaphragm arc segment 522 is slightly greater than the thickness of the first fuel diaphragm arc segment 512 .

[0047] As a specific embodiment of the present invention, the outer shell of the annular common bottom double membrane storage tank 5 and the fuel diaphragm 51, the fuel diaphragm support ring 515, the oxidant diaphragm 52, and the oxidant diaphragm support ring 523 form an upper and lower annular spaces, which can store oxidant and fuel respectively. When the pressurized gas is filled into the interlayer of the fuel diaphragm 51 and the oxidant diaphragm 52 from the air inlet nozzle (i.e., enters the air cavity), the fuel diaphragm 51 and the oxidant diaphragm 52 begin to deform and flip regularly according to the predetermined design due to the influence of the pressure difference. The fuel diaphragm 51 and the oxidant diaphragm 52 are designed with pre-flanges at the equator of the annular common bottom double membrane storage tank 5. When the fuel diaphragm 51 and the oxidant diaphragm 52 are subjected to air pressure, the fuel diaphragm 51 starts to flip from bottom to top, from the point where the arc segment of the fuel diaphragm pre-flange 513 is tangent to the first fuel diaphragm arc segment 512; the oxidant diaphragm 52 starts to flip from top to bottom, from the point where the oxidant diaphragm arc segment 522 is tangent to the oxidant diaphragm pre-flange 521.

[0048] It should be explained that, when the pressurized gas is filled into the interlayer of the fuel diaphragm 51 and the oxidant diaphragm 52 from the air inlet nozzle, the fuel diaphragm 51 and the oxidant diaphragm 52 are deformed and flipped regularly according to the predetermined design due to the pressure difference, which has the following advantages: First, the fuel diaphragm 51 and the oxidant diaphragm 52 physically isolate the fuel and the oxidant before they are deformed and flipped, so as to avoid the two from contacting each other in advance and causing unexpected reactions, thereby reducing the possibility of fire or explosion and other dangers in the system and improving the inherent safety of the system. Second, the fuel diaphragm 51 and the oxidant diaphragm 52 are deformed and flipped to adapt to the gravity and microgravity environment, so that the system can quickly adjust the supply state of the fuel and the oxidant according to different working conditions and load requirements. Under different power output requirements, the diaphragm can make corresponding deformation and flipping in time to ensure the stable operation of the system. Third, the supply of fuel and oxidant is accurately controlled, and the flow output is stabilized. By accurately controlling the pressure and flow of the pressurized gas, the deformation and flipping process of the diaphragm can be stable and repeatable, thereby ensuring that the fuel and oxidant are supplied to the engine at a stable flow rate and ensuring the stable operation of the engine. Fourth, by controlling the thickness gradient of the diaphragm, the supply synchronization of fuel and oxidizer is ensured, and the utilization rate of propellant is improved. The deformation and flipping process of the diaphragm is relatively gentle, which can effectively buffer the pressure impact of the pressurized gas on the system, reduce the damage to the equipment caused by excessive pressure fluctuations, and improve the operating stability and reliability of the power system.

[0049] like Figure 6 As shown, the fuel diaphragm 51 is fixedly connected to the inner wall of the annular double-membrane tank 5 with a common bottom through the fuel diaphragm support ring 515, and the oxidant diaphragm 52 is fixedly connected to the inner wall of the annular double-membrane tank 5 with a common bottom through the oxidant diaphragm support ring 523. The fuel diaphragm support ring 515 plays a role in fixing the fuel diaphragm 51, and the oxidant diaphragm support ring 523 plays a role in fixing the oxidant diaphragm 52.

[0050] As a preferred embodiment of the present invention, the fuel diaphragm support ring 515 and the oxidant diaphragm support ring 523 are both annular; the fuel diaphragm support ring 515 and the oxidant diaphragm support ring 523 are both suitable for being installed on the inner wall of the annular common bottom double membrane tank 5, and the fuel diaphragm support ring 515 and the oxidant diaphragm support ring 523 are fixedly connected inside the annular common bottom double membrane tank 5 along the inner circumferential wall of the annular common bottom double membrane tank 5, thereby fixing the fuel diaphragm 51 and the oxidant diaphragm 52 on the inner wall of the annular common bottom double membrane tank 5.

[0051] As a specific embodiment of the present invention, in order to improve the environmental adaptability of the metal diaphragm, the fuel diaphragm 51 is welded to the fuel diaphragm support ring 515 and then welded to the fuel liquid chamber shell and the gas chamber shell 55. Similarly, the oxidant diaphragm 52 is welded to the oxidant diaphragm support ring 523 and then welded to the oxidant liquid chamber shell 54 and the gas chamber shell 55. In order to prevent the support ring (fuel diaphragm support ring 515 or oxidant diaphragm support ring 523) from damaging the metal diaphragm when the metal diaphragm is bent by the impact of the liquid, a fillet r is set at the separation of the support ring and the metal diaphragm. Preferably, the radius of the fillet r ranges from 0.3mm to 0.5mm.

[0052] like Figure 1 As shown, a fuel anti-blocking cap 57 is provided at the fuel outlet, and an oxidant anti-blocking cap 58 is provided at the oxidant outlet. It should be explained that in order to prevent the metal diaphragm (fuel diaphragm 51 or oxidant diaphragm 52) from blocking the outlet (fuel outlet or oxidant outlet) due to eccentricity in the later stage of flipping, causing the propellant to be unable to be discharged and reducing the emptying efficiency of the tank, anti-blocking caps (fuel anti-blocking cap 57, oxidant anti-blocking cap 58) are provided at the outlet of the fuel liquid cavity and the outlet of the oxidant liquid cavity. The anti-blocking caps (fuel anti-blocking cap 57, oxidant anti-blocking cap 58) are annular spherical cap porous structures, and the anti-blocking caps are connected to the liquid cavity shell by welding. The height of the anti-blocking cap (fuel anti-blocking cap 57 or oxidant anti-blocking cap 58) should match the profile after the diaphragm (fuel diaphragm 51 or oxidant diaphragm 52) flips. The equivalent flow area of ​​the small hole of the anti-blocking cap shall not be less than the designed flow area of ​​the outlet.

[0053] like Figure 8 As shown, the fuel anti-blocking cap 57 is provided with a plurality of anti-blocking cap circular holes 571, and the equivalent flow area of ​​the anti-blocking cap circular holes 571 of the fuel anti-blocking cap 57 is not less than the designed flow area of ​​the fuel liquid outlet. The equivalent flow area of ​​the anti-blocking cap circular holes of the oxidant anti-blocking cap 58 is not less than the designed flow area of ​​the oxidant liquid outlet.

[0054] like Figure 7As shown, the gas diverter 56 is a hollow truncated cone structure, and a plurality of diverter circular holes 561 are distributed along the circumference of the hollow truncated cone structure; the gas diverter 56 is fixedly connected to the air cavity shell 55. It should be explained that in order to prevent the high-pressure gas from locally impacting the metal diaphragm, a gas diverter 56 is provided at the air inlet, and the gas diverter 56 is a hollow truncated cone structure with circumferential openings. The gas diverter 56 is connected to the air cavity shell 55 by welding, and the equivalent flow area of ​​the diverter circular hole 561 is not less than the designed flow area of ​​the air inlet.

[0055] As a preferred embodiment of the present invention, the annular gas cylinder 1 is a titanium alloy or aluminum alloy lined gas cylinder wrapped with a composite material. The composite material is an existing composite material. The annular common bottom double membrane storage tank 5 is a full metal structure, and each part can be made of titanium alloy or aluminum alloy.

[0056] The beneficial effects achieved by this application are as follows:

[0057] (1) The present application uses an annular gas cylinder and an annular common bottom double membrane tank, and combines the existing separately arranged fuel tank and oxidant tank into the annular common bottom double membrane tank, which can improve the structural efficiency and space utilization.

[0058] (2) The present application uses the annular double-membrane common bottom tank to adopt an active propellant management method. An air cavity is formed between the fuel diaphragm, the fuel diaphragm support ring, the oxidizer diaphragm, the oxidizer diaphragm support ring and the air cavity shell; the annular gas cylinder is connected to the air cavity and is used to introduce gas into the air cavity. By adjusting the pressure of the gas introduced into the air cavity, the fuel diaphragm and the oxidizer diaphragm are controlled to flip from top to bottom or from bottom to top, thereby changing the volume of the upper annular space and the lower annular space, and the separate bottom sinking system can be eliminated; by controlling the diaphragm thickness gradient, the synchronization of fuel and oxidizer supply is ensured, the utilization rate of propellant is improved, and the functional requirements of long-term on-orbit gliding of the upper stage and multiple starts of the main engine are realized.

[0059] (3) The present application can be used for both normal temperature propellant upper stages and low temperature propellant upper stages.

[0060] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise clearly and specifically defined.

[0061] In the description of the present application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any technician in the field to implement and use the present invention. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the present invention can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid obscuring the description of the present invention with unnecessary details. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the widest scope consistent with the principles and features disclosed in the present application.

[0062] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A launch vehicle upper stage power system, characterized in that: include: Annular gas cylinders, annular common bottom double membrane storage tanks, electric explosion valves, pressure reducing valves, safety valves, fuel liquid circuit diaphragm valves, fuel filling valves, oxidizer liquid circuit diaphragm valves, oxidizer filling valves, track control engines and attitude control engines; The annular common bottom double membrane storage tank is connected to the annular gas cylinder through a pipeline; The annular common bottom double membrane storage tank comprises: a fuel liquid chamber shell, an oxidant liquid chamber shell, an air chamber shell, a fuel diaphragm and an oxidant diaphragm, a fuel diaphragm support ring and an oxidant diaphragm support ring; The fuel liquid chamber housing is connected to the oxidant liquid chamber housing through the gas chamber housing to form the outer shell of the annular common bottom double membrane tank; The fuel diaphragm and the oxidant diaphragm are arranged inside the annular common bottom double membrane storage tank, the fuel diaphragm, the fuel diaphragm support ring and the fuel liquid cavity shell form an upper annular space for storing fuel; the oxidant diaphragm, the oxidant diaphragm support ring and the oxidant liquid cavity shell form a lower annular space for storing oxidant; the fuel diaphragm, the oxidant diaphragm, the fuel diaphragm support ring, the oxidant diaphragm support ring and the gas cavity shell form an air cavity; The fuel diaphragm is connected to the fuel liquid cavity housing and the gas cavity housing through the fuel diaphragm support ring; The oxidant diaphragm is connected to the oxidant diaphragm support ring and then connected to the oxidant liquid chamber housing and the gas chamber housing; The annular gas cylinder is in communication with the gas cavity and is used to introduce gas into the gas cavity. By adjusting the pressure of the gas introduced into the gas cavity, the fuel diaphragm and the oxidant diaphragm are controlled to flip from top to bottom or from bottom to top, thereby changing the volumes of the upper annular space and the lower annular space. The annular common-bottom double-membrane tank is connected downstream with a track control engine and an attitude control engine.

2. The launch vehicle upper stage power system according to claim 1, characterized in that: The annular common bottom double membrane storage tank is provided with an air inlet nozzle, one end of which is connected to the annular gas cylinder through an air inlet pipeline, and the other end of which is connected to the air cavity; An air path diaphragm valve, a vent nozzle and a gas diverter are arranged at one end of the air intake pipeline close to the air intake nozzle.

3. The launch vehicle upper stage power system according to claim 1, characterized in that: The top of the annular double-membrane tank is provided with a fuel outlet, and the bottom is provided with an oxidant outlet; The fuel outlet is in communication with the upper annular space, and the oxidant outlet is in communication with the lower annular space; The fuel liquid outlet is integrally installed with a fuel liquid circuit diaphragm valve and a fuel filling valve; An oxidant liquid path diaphragm valve and an oxidant filling valve are integrated and installed at the oxidant liquid outlet.

4. The launch vehicle upper stage power system according to claim 1, characterized in that: The fuel diaphragm comprises: a fuel diaphragm connecting ring, a first fuel diaphragm circular arc section, a fuel diaphragm pre-flange and a second fuel diaphragm circular arc section; One end of the fuel diaphragm connecting ring is connected to the outer shell of the annular common bottom double membrane storage tank, and the other end is connected to the first fuel diaphragm circular arc segment; One end of the first fuel diaphragm circular arc segment away from the fuel diaphragm connecting ring is connected to the second fuel diaphragm circular arc segment through the fuel diaphragm pre-flange.

5. The launch vehicle upper stage power system according to claim 4, characterized in that: The second fuel diaphragm arc segment adopts a constant cross-sectional thickness; the thickness of the first fuel diaphragm arc segment gradually decreases from top to bottom; the thickness of the fuel diaphragm connecting ring is consistent with the thickness of the upper end of the first fuel diaphragm arc segment; the thickness of the fuel diaphragm pre-flange is consistent with the thickness of the lower end of the first fuel diaphragm arc segment.

6. The launch vehicle upper stage power system according to claim 1, characterized in that: The oxidant diaphragm comprises: an oxidant diaphragm pre-flange and an oxidant diaphragm arc segment; One end of the pre-flange of the oxidant diaphragm is connected to the outer shell of the annular common bottom double membrane storage tank, and the other end is connected to the circular arc segment of the oxidant diaphragm.

7. The launch vehicle upper stage power system according to claim 6, characterized in that: The arc segment of the oxidant diaphragm adopts a variable cross-sectional thickness, and its thickness gradually increases from bottom to top. The thickness of the pre-flange of the oxidant diaphragm is consistent with the thickness of the lower end of the arc segment of the oxidant diaphragm.

8. The launch vehicle upper stage power system according to claim 3, characterized in that: A fuel anti-blocking cap is arranged at the fuel liquid outlet, and an oxidant anti-blocking cap is arranged at the oxidant liquid outlet. The anti-blocking cap is an annular spherical cap porous structure.

9. The launch vehicle upper stage power system according to claim 2, characterized in that: The gas diverter is a hollow truncated cone structure, and a plurality of diverter circular holes are distributed along the circumference of the hollow truncated cone structure; The gas flow divider is fixedly connected to the gas cavity housing.

10. The launch vehicle upper stage power system according to claim 1, characterized in that: An electric explosion valve, a pressure reducing valve and a safety valve are arranged in sequence on the pipeline connecting the annular gas cylinder and the annular double-membrane storage tank with a common bottom.

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