A compensation-collecting multifunctional compensator for a spacecraft thermal control fluid circuit

Abstract

The application discloses a compensation-collecting multifunctional compensator for a spacecraft thermal control fluid circuit, which comprises a lower bottom assembly, a welded bellows assembly, a volute spring tensioner, an electromagnetic valve, an angular displacement sensor, a storage tank body and a guide ring; wherein the bottom of the storage tank body is connected with the lower bottom assembly; the welded bellows assembly is connected with the lower bottom assembly; the electromagnetic valve is connected with the inner wall of the lower bottom assembly, and the electromagnetic valve controls the on-off of the air cavity flow channel port of the compensator; the bottom of the volute spring tensioner is connected with the inner wall of the lower bottom assembly, and the pull rope end of the volute spring tensioner is connected with the top of the welded bellows assembly; the angular displacement sensor is arranged on the volute spring tensioner; and the guide ring is connected with the top end of the welded bellows assembly. The application solves the storage problem of the spacecraft thermal control fluid circuit under an ultralow-temperature environment, improves the environmental tolerance range of the thermal control fluid circuit, and further prolongs the service life of the spacecraft.

Description

Technical Field

[0001] This invention belongs to the technical field of thermal control fluid loop compensators for spacecraft, and particularly relates to a multi-functional compensator for thermal control fluid loops of spacecraft that combines compensation and liquid collection. Background Technology

[0002] Space thermal control fluid loops are the primary means of active temperature control for space stations, satellites, and other spacecraft. Changes in space environment temperature and the accumulation of loop leaks can cause pressure fluctuations in the fluid loop, leading to cavitation due to excessively low inlet pressure of loop pumps or structural failure due to excessively high loop pressure. In addition, after spacecraft land, they will experience an ultra-low temperature environment, and the fluid working medium in exposed fluid loop units and pipelines will solidify at low temperatures. Its volume expansion can damage the loop piping system and related products, causing the thermal control fluid loop system to fail. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a compensation-liquid collection multifunctional compensator for spacecraft thermal control fluid circuits, which solves the storage problem of spacecraft thermal control fluid circuits in ultra-low temperature environments, improves the environmental tolerance range of thermal control fluid circuits, and thus extends the service life of spacecraft.

[0004] The objective of this invention is achieved through the following technical solution: A multi-functional compensator for thermal control fluid loops in spacecraft, comprising: a lower base assembly, a welded bellows assembly, a spiral spring tensioner, a solenoid valve, an angular displacement sensor, a tank body, and a guide ring; wherein, the bottom of the tank body is connected to the lower base assembly; the welded bellows assembly is disposed inside the tank body and is connected to the lower base assembly; the space enclosed by the inner side of the welded bellows assembly and the lower base assembly is the air chamber of the compensator, and the space enclosed by the welded bellows assembly and the tank body is the liquid chamber of the compensator; the solenoid valve is connected to the inner wall of the lower base assembly and controls the opening and closing of the air chamber flow channel of the compensator; the bottom of the spiral spring tensioner is connected to the inner wall of the lower base assembly, and the end of the pull rope of the spiral spring tensioner is connected to the top of the welded bellows assembly; the angular displacement sensor is disposed on the spiral spring tensioner; and the guide ring is connected to the top of the welded bellows assembly.

[0005] The aforementioned multi-functional compensator for thermal control fluid circuits in spacecraft further includes a pin; wherein the angular displacement sensor is mounted on the spiral spring tensioner via the pin.

[0006] The aforementioned multi-functional compensator for thermal control fluid circuits in spacecraft further includes: an electrical connector; wherein the electrical connector is disposed on the outer wall of the lower base assembly; the electrical connector is connected to the solenoid valve and the angular displacement sensor respectively.

[0007] In the aforementioned multi-functional compensator for thermal control fluid loops in spacecraft, the lower base assembly includes a base plate and an inflation valve; wherein the inflation valve is located at an inflation hole on the base plate; the bottom of the storage tank is connected to the base plate; the welded bellows assembly is connected to the base plate, and the space enclosed by the inner side of the welded bellows assembly and the base plate forms the air chamber of the compensator; the solenoid valve is connected to the inner wall of the base plate; and the bottom of the spiral spring tensioner is connected to the inner wall of the base plate.

[0008] In the aforementioned multi-functional compensator for thermal control fluid circuits in spacecraft, the inflation valve includes a gasket, a spring, a valve head, a plug, a plug cap, and a retaining ring; wherein, the gasket is disposed at the bottom of the inflation port; the plug is connected to the port of the inflation port; the valve head is disposed inside the plug; the spring is disposed inside the valve head via the retaining ring, and the bottom of the spring presses against the gasket; the plug cap is fitted onto the outer surface of the plug.

[0009] In the aforementioned multi-functional compensator for the thermal control fluid loop of a spacecraft, the welded bellows assembly includes a lower connecting ring, a welded bellows, an upper connecting ring, and a moving head. One end of the welded bellows is connected to the lower connecting ring, and the other end is connected to the upper connecting ring. The top of the upper connecting ring is connected to the moving head. A circular protrusion is provided on the inner bottom side of the upper connecting ring to support the arc portion of the welded bellows and optimize the stress on the diaphragm. A circular groove is provided on the outer side of the upper connecting ring for embedding a guide ring. The lower connecting ring is connected to the lower bottom assembly. A protrusion for welding the lower connecting ring to the welded bellows is arranged on the outer upper layer of the lower connecting ring, and an arc protrusion supporting the bellows diaphragm is arranged on the inner upper layer of the lower connecting ring.

[0010] In the aforementioned multi-functional compensator for thermal control fluid loops in spacecraft, the spiral spring tensioner includes a spiral spring with a support, a wheel, and a pull rope; wherein, the support of the spiral spring with a support is connected to the base plate; the wheel is mounted on the support of the spiral spring with a support; one end of the pull rope is connected to the wheel, and the other end of the pull rope is connected to the motion end cap; the angular displacement sensor is mounted on the wheel.

[0011] In the aforementioned multi-functional compensator for the thermal control fluid loop of a spacecraft, the tank body includes an upper end cap and a cylindrical section; wherein the upper end cap and the cylindrical section are connected; and the cylindrical section is connected to the lower bottom assembly.

[0012] In the aforementioned multi-functional compensator for thermal control fluid circuits of spacecraft, the guide ring is a polytetrafluoroethylene ring with an opening and fixed to the upper connecting ring by screws. There is a gap of 0.25~0.5mm between the outer side of the guide ring and the inner side of the tank body.

[0013] The aforementioned multi-functional compensator for thermal control fluid circuits in spacecraft also includes: an electrical connector sealing ring; wherein the electrical connector is disposed on the outer wall of the lower base assembly via the electrical connector sealing ring.

[0014] Compared with the prior art, the present invention has the following advantages:

[0015] (1) The present invention embeds a spiral spring tensioner and a solenoid valve in the compensator, which can realize the active release of gas in the compensator gas chamber and thus be used as a liquid collection tank for a long time, expanding the function of the compensator, realizing the recovery of working fluid in the fluid circuit and product integration design, so that the spacecraft thermal control fluid circuit can be subjected to ultra-low temperature environment in some parts.

[0016] (2) The present invention embeds a flow channel inside the compensator base plate, avoiding external pipes and achieving efficient use of space;

[0017] (3) The compensator air chamber of the present invention is equipped with an air filling shut-off valve. It is filled with air by an external air source, and the gas in the liquid chamber is recovered by the loop gas collector, which can realize the adjustment of the compensator from the liquid collection tank to the compensator compensation function in orbit.

[0018] (4) The present invention aims to achieve the goal of lightweight and integrated design of spacecraft thermal control system, meet the on-orbit and landing mission requirements of spacecraft thermal control fluid loop, expand the range of environments that spacecraft can withstand, and extend the service life of spacecraft. Attached Figure Description

[0019] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0020] Figure 1 This is a schematic diagram of a multi-functional compensator for a spacecraft thermal control fluid loop provided in an embodiment of the present invention;

[0021] Figure 2This is another structural schematic diagram of the spacecraft thermal control fluid loop compensation-liquid collection multifunctional compensator provided in the embodiments of the present invention;

[0022] Figure 3 This is another structural schematic diagram of the multi-functional compensator for spacecraft thermal control fluid loop provided in this embodiment of the invention;

[0023] Figure 4 This is a schematic diagram of the lower base component structure provided in an embodiment of the present invention;

[0024] Figure 5(a) is a schematic diagram of the upper surface of the base plate provided in an embodiment of the present invention;

[0025] Figure 5(b) is a schematic diagram of the lower surface of the base plate provided in an embodiment of the present invention;

[0026] Figure 6 This is a schematic diagram of the welded bellows assembly structure provided in an embodiment of the present invention;

[0027] Figure 7 This is a schematic diagram of the upper connecting ring cross-section provided in an embodiment of the present invention;

[0028] Figure 8 This is a schematic diagram of the lower connecting ring structure provided in an embodiment of the present invention;

[0029] Figure 9(a) is a cross-sectional view of the guide ring provided in an embodiment of the present invention;

[0030] Figure 9(b) is a perspective view of the guide ring provided in an embodiment of the present invention;

[0031] Figure 10 This is a schematic diagram of the storage tank structure provided in an embodiment of the present invention;

[0032] Figure 11 This is a schematic diagram of the valve head structure provided in an embodiment of the present invention. Detailed Implementation

[0033] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0034] Adding a compensator device to the fluid loop can, based on the compressibility and expansibility of the gas, push the compensator's liquid chamber to expel the working fluid into the loop or draw it in from the loop when the loop pressure fluctuates, thereby stabilizing the loop pressure fluctuations. To avoid cryogenic environments, the working fluid in the fluid loop needs to have a working fluid recovery function. Currently, spacecraft are developing towards integration and lightweighting. Moreover, the mission requirements after spacecraft landing require the active thermal control fluid loop to continue operating normally after experiencing ultra-low temperature environments to ensure the normal operation of high-power electronic products in spacecraft. Therefore, adopting an integrated design to expand product functions is of great significance for improving the efficiency of the spacecraft's thermal control fluid loop and extending the service life of the spacecraft after landing.

[0035] Based on the working principle of compensators and the concept of fluid loop working fluid recovery, a multi-functional compensator for spacecraft thermal control fluid loops, combining compensation and liquid collection, is proposed. During the spacecraft's on-orbit phase, this compensator can perform its compensation function to stabilize loop pressure fluctuations. It also has a mode switching function; when adjusted to liquid collection tank mode, it can recover fluid working fluid from exposed spacecraft components and pipelines, preventing the loop working fluid from being in an ultra-low temperature environment. This can solve the storage problem of spacecraft thermal control fluid loops in ultra-low temperature environments, improve the environmental tolerance range of thermal control fluid loops, and thus extend the service life of spacecraft.

[0036] Figure 1 This is a schematic diagram of a multi-functional compensator for a spacecraft thermal control fluid loop provided in an embodiment of the present invention; Figure 2 This is another structural schematic diagram of the spacecraft thermal control fluid loop compensation-liquid collection multifunctional compensator provided in the embodiments of the present invention; Figure 3 This is another structural schematic diagram of the multi-functional compensator for spacecraft thermal control fluid loops provided in this embodiment of the invention. (See diagram below.) Figure 1 , Figure 2 and Figure 3 As shown, the spacecraft's thermal control fluid loop compensation-liquid collection multi-functional compensator includes: a lower base assembly 1, a welded bellows assembly 2, a spiral spring tensioner 3, a solenoid valve 4, an angular displacement sensor 5, a tank body 6, and a guide ring 7. The bottom of the tank body 6 is connected to the lower base assembly 1. The welded bellows assembly 2 is located inside the tank body 6 and is connected to the lower base assembly 1. The space enclosed by the inner side of the welded bellows assembly 2 and the lower base assembly 1 forms the air chamber of the compensator, and the space enclosed by the welded bellows assembly 2 and the tank body forms the liquid chamber of the compensator. The solenoid valve 4 is connected to the inner wall of the lower base assembly 1 and controls the opening and closing of the air chamber flow channel of the compensator. The bottom of the spiral spring tensioner 3 is connected to the inner wall of the lower base assembly 1, and the end of the pull rope of the spiral spring tensioner 3 is connected to the top of the welded bellows assembly 2. The angular displacement sensor 5 is located on the spiral spring tensioner 3. The guide ring 7 is connected to the top of the welded bellows assembly 2.

[0037] like Figure 2 As shown, the spacecraft thermal control fluid loop compensation-liquid collection multi-functional compensator also includes: pin 8; wherein, the angular displacement sensor 5 is mounted on the spiral spring tensioner 3 via pin 8.

[0038] like Figure 2 As shown, the spacecraft thermal control fluid loop compensation-liquid collection multi-functional compensator also includes: an electrical connector 16; wherein, the electrical connector 16 is disposed on the outer wall of the lower bottom assembly 1; the electrical connector 16 is connected to the solenoid valve 4 and the angular displacement sensor 5 respectively.

[0039] like Figure 4 As shown in Figures 5(a) and 5(b), the lower base assembly 1 includes a base plate 110 and an inflation valve; wherein, the inflation valve is located at the inflation hole position opened in the base plate 110; the bottom of the storage tank 6 is connected to the base plate 110; the welded bellows assembly 2 is connected to the base plate 110, and the space enclosed by the inner side of the welded bellows assembly 2 and the base plate 110 is the air chamber of the compensator; the solenoid valve 4 is connected to the inner wall of the base plate 110; and the bottom of the spiral spring tensioner 3 is connected to the inner wall of the base plate 110.

[0040] like Figure 4 and Figure 11 As shown, the inflation valve includes a gasket 111, a spring 112, a valve head 113, a plug 114, a plug cap 115, and a retaining ring 116; wherein, the gasket 111 is disposed at the bottom of the inflation hole; the plug 114 is connected to the inflation hole port; the valve head 113 is disposed inside the plug 114; the spring 112 is disposed inside the valve head 113 through the retaining ring 116, and the bottom of the spring 112 presses against the gasket 111; the plug cap 115 is sleeved on the outer surface of the plug 114.

[0041] like Figure 6 , Figure 7 and Figure 8 As shown, the welded bellows assembly 2 includes a lower connecting ring, a welded bellows, an upper connecting ring, and a moving end cap; one end of the welded bellows is connected to the lower connecting ring, and the other end of the welded bellows is connected to the upper connecting ring; the top of the upper connecting ring is connected to the moving end cap; a circular protrusion is provided on the inner side of the bottom of the upper connecting ring to support the arc portion of the welded bellows and optimize the stress on the diaphragm; a circular groove is provided on the outer side of the upper connecting ring for embedding the guide ring 7; the lower connecting ring is connected to the lower bottom assembly 1, and a protrusion for welding connection with the welded bellows is arranged on the outer side of the upper layer of the lower connecting ring, and an arc protrusion for supporting the bellows diaphragm is arranged on the inner side of the upper layer of the lower connecting ring.

[0042] The welded bellows is welded to the upper and lower connecting rings on both sides along the axial direction. The upper connecting ring is then welded to the moving head. A connecting piece is welded to the center of the inner side of the moving head. The connecting piece is provided with a threaded blind hole for threaded connection. The welded bellows assembly is located in the cavity formed by the tank body and the bottom plate. The lower connecting ring of the welded bellows assembly is fixed to the bottom plate by screws. The lower connecting ring has a local groove at the outlet of the flow channel in the bottom plate to ensure the gas and liquid flow channels. A non-metallic guide ring is arranged on the outer side of the upper connecting ring to support the welded bellows assembly and to guide it when the bellows is axially compressed and the moving head moves. The seal at the bottom fixing screw of the welded bellows adopts the end face seal of one non-metallic sealing ring inside and one outside the screw based on the sealing groove of the bottom plate. The seal inside the screw seals the gas chamber of the compensator and the external environment of the compensator, and the seal outside the screw seals the liquid chamber of the compensator and the external environment of the compensator, so as to prevent the working medium of the gas and liquid chambers from leaking to the external environment of the compensator through the gap between the lower connecting ring of the welded bellows assembly and the bottom plate - screw hole.

[0043] The space enclosed by the inner side of the welded bellows assembly and the base plate is the gas chamber of the compensator, and the space enclosed by the outer side of the welded bellows assembly and the storage tank is the liquid chamber of the compensator. The gas and liquid chambers can be connected through a flow channel embedded in the base plate. A solenoid valve 4 is installed at the flow channel opening of the compensator's gas chamber to control its on / off state. The solenoid valve is connected to the base plate by a plunger and fixed with screws. The plunger connection is equipped with two static seals: one end face seal and one radial seal, to prevent the working fluid in the flow channel from communicating with the gas in the compensator's gas chamber through the gap between the solenoid valve and the base plate. The bottom of the compensator's inner cavity... The plate is also equipped with a spiral spring tensioner 3. The tensioner bracket is fixed to the compensator base plate by screws. A section of tension rope is wound on the wheel in the middle of the tensioner. The end of the tension rope is connected to the connector of the motion head by a thread. An angular displacement sensor 5 is arranged at one end of the central shaft of the tensioner. The compensator base plate is provided with an opening interface for wire passage. An electrical connector 16 is arranged on the outside of the interface for external power supply and signal acquisition. The wires on the inside of the interface are respectively connected to the angular displacement sensor and the solenoid valve that are matched with the spiral spring tensioner.

[0044] The compensator tank has one liquid inlet on the top and one on the bottom side. The top is the liquid inlet and the bottom side is the liquid outlet. The compensator base plate has two interfaces: one electrical interface and one gas shut-off valve interface. The electrical interface can supply power and monitor the status of the internal angular displacement sensor and solenoid valve of the compensator. The gas shut-off valve interface can charge and release gas in the compensator's gas chamber. The angular displacement sensor is used to provide feedback on the displacement signal of the spiral spring tensioner. The solenoid valve is used to control the flow channel to discharge gas from the gas chamber into the liquid chamber.

[0045] The free state of the welded bellows is the stretched state (no axial compression displacement), and the free state of the spiral spring tensioner is the fully retracted tension. When the compensator is working normally, the moving head in the bellows assembly is in the middle equilibrium position along the axis of the bellows. The welded bellows is compressed to a certain extent, and the spiral spring tensioner generates a certain tension on the moving head. For the moving head, the axial force generated by the pressure of the liquid cavity on the outside of the welded bellows, the tension of the spiral spring tensioner, the rebound force generated by the stiffness of the welded bellows, and the axial force generated by the pressure of the air cavity on the inside of the welded bellows are balanced.

[0046] like Figure 1 As shown, the spiral spring tensioner 3 includes a spiral spring with a bracket, a wheel, and a pull rope; wherein, the bracket of the spiral spring with a bracket is connected to the base plate; the wheel is set on the bracket of the spiral spring with a bracket; one end of the pull rope is connected to the wheel, and the other end of the pull rope is connected to the motion end cap; the angular displacement sensor 5 is set on the wheel.

[0047] like Figure 10 As shown, the storage tank 6 includes an upper end cap and a cylindrical section; the upper end cap and the cylindrical section are connected; the cylindrical section is connected to the lower bottom assembly 1. The storage tank is a cylindrical structure with an upper end cap, and a flange is provided on the outer edge of the bottom. The bottom plate is a disc structure with a flange. The storage tank and the bottom plate are connected by bolt flanges and sealed by a non-metallic sealing ring end face based on the sealing groove of the bottom plate. This seal is a seal between the compensator liquid chamber and the external environment of the compensator, preventing the working fluid in the liquid chamber from leaking to the external environment of the compensator through the gap between the storage tank and the bottom plate. The part enclosed by the storage tank and the bottom plate is the inner cavity of the compensator. The bottom plate is integrated with a self-locking inflation shut-off valve, which can be used to inflate and deflate the compensator's gas chamber from outside the compensator using matching tooling.

[0048] As shown in Figures 9(a) and 9(b), the guide ring 7 is a polytetrafluoroethylene ring with an opening and is fixed to the upper connecting ring by screws. There is a gap of 0.25~0.5mm between the outer side of the guide ring 7 and the inner side of the tank body.

[0049] Specifically, the spacecraft's thermal control fluid circuit compensation-liquid collection multi-functional compensator includes: a lower base assembly 1, a welded bellows assembly 2, a spiral spring tensioner 3, a solenoid valve 4, an angular displacement sensor 5, a tank body 6, a guide ring 7, a pin 8, a tank body-base plate connecting bolt 9, a welded bellows assembly-base plate connecting screw 10, a spiral spring tensioner mounting screw 11, a solenoid valve mounting screw 12, a base plate sealing ring 13, a solenoid valve sealing ring 15, an electrical connector 16, an electrical connector sealing ring 17, and an electrical connector mounting screw 18.

[0050] The lower assembly 1 consists of a base plate 110, a gasket 111, a spring 112, a valve head 113, a plug 114, a plug cap 115, a retaining ring 116, and sealing rings 117, 118, and 119. Flow channels are arranged on the top and sides of the valve head 113. The spring 112 inside the valve head 113, in conjunction with the retaining ring 116 and the gasket 111, supports the valve head 113 and compresses the sealing ring 117 to form a static seal. A plug 114 is installed on the other side of the base plate 110. After the plug cap 115 is threadedly connected to the base plate 110 and tightened, it compresses the sealing rings 118 and 119 to form seals. After removing the plug cap 115 and the plug 114, the valve head 113 can be pushed by a pin to compress the spring 112, thereby generating gas. The filling and discharging channels; the base plate 110 has O-ring grooves, screw holes, embedded flow channels, solenoid valve mounting platforms, and scroll spring tensioner mounting platforms on the inner side of the compensator. A ring of bolt holes is arranged around the circumference of the base plate, and three O-ring grooves are arranged sequentially from the outside in. After the O-ring is placed in the outermost groove, it is compressed by the base plate and the tank body to form a seal between the liquid cavity outside the compensator bellows and the external environment. The O-ring in the middle groove is compressed by the base plate and the lower connecting ring to form a static seal between the liquid cavity of the compensator and the external environment, avoiding… To prevent leakage of the liquid working fluid through the gap between the lower connecting ring and the base plate and through the screw holes, the innermost grooved O-ring, after being compressed by the base plate and the lower connecting ring, forms a static seal between the inner air cavity of the compensator bellows and the external environment of the compensator. A ring of screw holes is arranged circumferentially between the two inner O-rings for connecting the base plate and the lower connecting ring for fixation. A spiral spring tensioner mounting platform and a solenoid valve mounting platform are arranged on the inner plane of the O-ring groove. These two platforms are independent and form a plane parallel to the surface. The system includes blind screw holes for fixing the scroll spring tensioner and the solenoid valve. The solenoid valve mounting platform also has a flow channel for connecting the solenoid valve's mechanical interface. The flow channel is embedded in the base plate and connects to the opening between the outermost O-ring groove and the middle O-ring groove on the base plate, serving as a flow channel for gas to enter the liquid chamber. The base plate has an electrical connector interface between the scroll spring tensioner and the solenoid valve mounting platform, which is used to supply power, monitor the status, and regulate the scroll spring tensioner and solenoid valve inside the compensator from outside the compensator.

[0051] The welded bellows assembly 2 consists of a lower connecting ring, a welded bellows, an upper connecting ring, a moving head, and connecting parts. The lower connecting ring is a circular plate with blind holes for mounting screws, bosses for welding the welded bellows, and bosses supporting the arc segment of the bellows. The welded bellows is a bellows formed by stamping a metal strip with a corrugated diaphragm along its inner and outer edges, allowing for a large axial displacement. Both ends of the bellows are welded to the upper and lower connecting rings at their outer circumferences, respectively. The upper connecting ring is a circular ring with its upper side welded to the moving head and its lower outer edge welded to the bellows. The inner bottom of the upper connecting ring has a circular protrusion to support the arc segment of the bellows and optimize the stress on the diaphragm. The outer side of the upper connecting ring has a circular groove for embedding a guide ring. The bottom has a boss for welding the bellows and a boss for supporting the arc segment of the bellows diaphragm. The outer side of the upper connecting ring has a groove for placing the guide ring. The moving head is a stamped thin plate head. The inner side of the lower connecting ring has a protrusion for arranging blind holes for screws to connect with the base plate. The outer side of the upper layer of the lower connecting ring has a protrusion for welding the bellows. The inner side of the upper layer has an arc protrusion to support the bellows diaphragm, which is used to better withstand the force when the bellows is axially compressed.

[0052] The spiral spring tensioner 3 is a spiral spring with a bracket and a wheel for winding the pull rope. One end of the pull rope is connected to the wheel, and the other end is connected to the moving end cap. The tension on the moving end cap is generated by the rebound force of the spiral spring. An angular displacement sensor 5 is installed at one end of the tensioner shaft to monitor the displacement of the pull rope. The tensioner is equipped with a limit plate to stop the movement of the tensioner when the displacement of the pull rope is large enough, so as to avoid excessive displacement of the moving end cap and scratches.

[0053] A solenoid valve is a valve that automatically switches on and off using electromagnetic force to control the flow path.

[0054] The angular displacement sensor 5 is a displacement sensor that provides feedback displacement signals. It is mounted on one end of the rotating shaft of the spiral spring tensioner via pin 8 and moves with the rotating shaft.

[0055] The storage tank 6 is a cylindrical structure with a cover. The center of the upper end cap and the bottom side of the storage tank 6 have interfaces for connecting the liquid chamber inside the compensator storage tank with the thermal control fluid circuit. The cylindrical section inside the storage tank 6 and the upper end cap are provided with grooves to prevent the formation of dead cavities between the outside of the bellows and the inside of the storage tank 6, and between the moving end cap and the upper end cap of the storage tank, to prevent the residual working fluid. The bottom side of the storage tank 6 is provided with flanges and bolt holes, which are connected to the bottom plate 110 with storage tank-bottom plate connecting bolts 9 and sealed with bottom plate sealing ring 13 and grooves on the bottom plate.

[0056] The guide ring 7 is a polytetrafluoroethylene ring with an opening and is fixed to the upper connecting ring by screws. There is a gap of about 0.25~0.5mm between its outer side and the inner side of the tank body. It is used to support and guide the moving end of the welded bellows assembly 2 along the axial direction.

[0057] The electrical connector 16 is fitted with the electrical connector sealing ring 17 and is installed on the outer side of the electrical connector mounting boss of the compensator lower bottom assembly 1 using the electrical connector mounting screw 18. The electrical connector wires inside the compensator cavity are respectively connected to the angular displacement sensor and the solenoid valve.

[0058] The upper and lower connecting rings are welded to both ends of the bellows. The upper side of the upper connecting ring is then welded to the moving head. A polytetrafluoroethylene guide ring 7 is embedded on the outside of the upper connecting ring. The guide ring 7 is connected to the upper connecting ring by small screws to form the welded bellows assembly 2.

[0059] When the base plate 110 is in the component state, the air-filled shut-off valve is composed of valve head 113, spring 112, O-ring 1e, retaining ring 116, gasket 111, etc., installed on the upper side of the base plate. On the other side, after the air chamber is filled with air, the plug 114, O-rings 1i and 1j and plug cap 115 are installed.

[0060] The spiral spring tensioner 3 and the solenoid valve 4 are installed on the mounting platform of the base plate 110 with screws. The solenoid valve 4 is connected to the embedded flow channel of the base plate 110 through the plunger interface. Two O-ring static seals (one end face seal + one radial seal) are used to isolate the gas and liquid chambers at the solenoid valve interface.

[0061] The pull rope of the spiral spring tensioner 3 is connected to the connecting piece at the center of the inner side of the moving head via a thread. The base plate 110 and the lower connecting ring are fixed by screws 10. The contact plane between the base plate 110 and the lower connecting ring compresses the two O-rings 13 to form two static seals to ensure the sealing between the compensator's air chamber and the outside, and between the liquid chamber and the outside.

[0062] The compensator tank body 5 is connected to the base plate 110 by bolts 9 arranged in the outer circumferential direction. The contact plane between the tank body and the base plate compresses the outermost O-ring 13 to form a static seal to ensure the sealing of the compensator liquid chamber from the external environment.

[0063] The space enclosed by the outer side of the welded bellows assembly 2 and the inner side of the tank body 6 is the compensator liquid chamber. The liquid chamber is connected to the fluid circuit through a mechanical interface. The space enclosed by the lower bottom assembly 1 and the welded bellows assembly 2 is the compensator gas chamber. The gas in the gas chamber can be actively discharged to the liquid chamber through the embedded flow channel via the solenoid valve in the gas chamber. The volume of the inner cavity of the welded bellows decreases, and the working fluid of the circuit is recovered to the compensator liquid chamber, resulting in a state of gas and liquid coexistence.

[0064] The welded bellows assembly is always in equilibrium under stress. Let's assume the initial state is when the welded bellows is in a free state (axial compressive displacement is 0). Its constraint relationships are as follows:

[0065] P1•A+k•x=P2•A +F(x)

[0066] V=A•x

[0067] Where A is the equivalent cross-sectional area of ​​the welded bellows assembly, which is related to the inner and outer diameters of the bellows; P1 is the air chamber pressure; k is the axial compressive stiffness of the bellows; x is the axial displacement of the bellows, which can be obtained from the output of the angular displacement sensor; P2 is the liquid chamber pressure; F(x) is the external output tension of the spiral spring tensioner, which is a function of the axial displacement (x); V is the volume of working fluid that the compensator compensates for by the loop and draws in.

[0068] Effects: Through this formula, ① the remaining working fluid volume inside the compensator when it performs the compensation function and the working fluid volume recovered inside the compensator when it performs the liquid collection function can be calculated in combination with system requirements during the system design stage. The bellows and tensioner parameters can be iteratively adjusted to meet system requirements; ② combined with calibration tests, the product performance during the operation stage can be monitored in real time through angular displacement sensors.

[0069] like Figure 1 As shown, after the multi-functional compensator is assembled, the space enclosed by the welded bellows assembly 2 and the storage tank 6 and the flow channel of the base plate 110 constitute the liquid chamber of the compensator (outside of the bellows). The space enclosed by the bellows assembly 2 and the base plate 110 is the air chamber of the compensator (inside the bellows). The liquid chamber of the compensator is filled with fluid working medium, and the air chamber of the storage tank 6 is filled with gas at a certain pressure. The spiral spring tensioner 3 and the solenoid valve 4 are located in the air chamber of the compensator.

[0070] The axial force generated by the air chamber pressure, the tension of the spiral spring tensioner 3, and the axial force (relatively small) generated by the stiffness of the bellows reach a balance with the axial force generated by the liquid chamber pressure. The spiral spring is in its free state when the rope is retracted; therefore, the air chamber pressure of the compensator is greater than the liquid chamber pressure.

[0071] When the multi-functional compensator is used for compensation, the compensator's liquid chamber is filled with working fluid, the moving head is in the middle position, the spiral spring has not fully returned to its free state, and the compensator's liquid chamber is connected to the thermal control fluid circuit. When the circuit pressure increases due to factors such as increased ambient temperature, the pressure in the compensator's liquid chamber increases, breaking the initial equilibrium state. The gas in the gas chamber is compressed, the bellows experiences axial compression, the moving head moves downward, the space in the compensator's liquid chamber increases, and working fluid is drawn into the fluid circuit through the liquid inlet. The working fluid pressure in the circuit decreases, and the bellows and moving head reach a new equilibrium state in their new positions. When the circuit pressure decreases due to factors such as working fluid leakage, the pressure in the compensator's liquid chamber decreases, breaking the equilibrium state. The gas in the compensator's gas chamber expands, the moving head moves upward, and working fluid is squeezed from the compensator's liquid chamber into the circuit, reaching equilibrium at a new pressure point and preventing the circuit pressure from becoming too low.

[0072] When the multi-functional compensator is switched from compensator mode to liquid collection tank mode, the solenoid valve 4 of the compensator's air chamber is opened. Since the air chamber pressure is greater than the liquid chamber pressure, the gas in the air chamber is discharged into the bottom plate flow channel through solenoid valve 4, and finally accumulates in the space between the lower connecting ring opening, the outside of the bellows, and the inside of the tank body, on the upper side of the moving end cap and the inside of the tank body cover. The air chamber pressure drops, and the scroll spring tensioner pulls the moving end cap downward. When the scroll spring approaches its limit position, the solenoid valve is closed, and the compensator air chamber remains small. In the compensator liquid chamber, the bottom layer contains the working fluid, while the upper layer is gas. All working fluids in the fluid circuit flow back to the compensator liquid chamber to prevent the working fluid from solidifying and bursting the pipeline under the ultra-low temperature environment outside the cabin. After the ultra-low temperature environment has passed, the mechanical pump or other power device connected to the outlet of the compensator liquid chamber draws in the working fluid from the bottom of the compensator liquid chamber and delivers it to the fluid circuit. It then returns to the compensator liquid chamber from the inlet. The multi-functional compensator acts as a liquid collection and storage tank to ensure the normal operation of the thermal control fluid circuit after the low temperature environment.

[0073] The multifunctional compensator proposed in this invention has two working modes: compensator and liquid collection tank. It has high integration and is suitable for different environments of spacecraft in orbit and landing. The main power is the gas pressure in the air chamber and the spiral spring. It has high reliability and low energy consumption. When the spacecraft is in orbit, the compensator can effectively reduce the pressure fluctuation of the spacecraft's in-orbit thermal control fluid circuit and compensate for the working fluid leakage of the in-orbit fluid circuit. After the spacecraft lands, the compensator can be actively adjusted to the liquid collection tank mode by controlling the solenoid valve. The working fluid of the fluid circuit flows to the compensator's liquid chamber to avoid the ultra-low temperature environment. This ensures that the spacecraft's active thermal control fluid circuit can still work normally after experiencing ultra-low temperature environment, thus extending the service life of the active thermal control fluid circuit system after the spacecraft lands.

[0074] This invention embeds a spiral spring tensioner and a solenoid valve within the compensator, enabling active gas release from the compensator's gas chamber for long-term use as a liquid collection tank. This expands the compensator's functionality, allowing for the recovery of the working fluid in the fluid loop and integrated product design. It also enables the spacecraft's thermal control fluid loop to withstand cryogenic environments. Furthermore, the invention embeds a flow channel inside the compensator's base plate, avoiding external piping and achieving efficient space utilization. The compensator's gas chamber is equipped with an inflation shut-off valve; after inflation via an external gas source, the gas in the liquid chamber is recovered by the loop gas collector, enabling on-orbit readjustment of the compensator from a liquid collection tank to its compensator compensation function. This invention aims to achieve a lightweight and integrated design for the spacecraft's thermal control system, meeting the on-orbit and landing mission requirements of the spacecraft's thermal control fluid loop, expanding the spacecraft's environmental tolerance range, and extending its service life.

[0075] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A compensation-accumulator multifunctional compensator for a spacecraft thermal control fluid circuit, characterized by include: The components include: bottom assembly (1), welded bellows assembly (2), spiral spring tensioner (3), solenoid valve (4), angular displacement sensor (5), tank body (6), and guide ring (7); among which, The bottom of the tank body (6) is connected to the bottom assembly (1); The welded bellows assembly (2) is disposed inside the tank body (6), and the welded bellows assembly (2) is connected to the bottom assembly (1); The space enclosed by the inner side of the welded bellows assembly (2) and the lower bottom assembly (1) is the air chamber of the compensator, and the space enclosed by the welded bellows assembly (2) and the tank body is the liquid chamber of the compensator. The solenoid valve (4) is connected to the inner wall of the lower bottom assembly (1), and the solenoid valve (4) controls the opening and closing of the air chamber flow channel of the compensator; The bottom of the spiral spring tensioner (3) is connected to the inner wall of the lower bottom assembly (1), and the end of the pull rope of the spiral spring tensioner (3) is connected to the top of the welded bellows assembly (2). The angular displacement sensor (5) is mounted on the spiral spring tensioner (3); The guide ring (7) is connected to the top end of the welded bellows assembly (2); The lower base assembly (1) includes a base plate (110) and an inflation valve; wherein, The inflation valve is located at the inflation hole position of the base plate (110); The bottom of the storage tank (6) is connected to the bottom plate (110); The welded bellows assembly (2) is connected to the base plate (110), and the space enclosed by the inner side of the welded bellows assembly (2) and the base plate (110) is the air chamber of the compensator. The solenoid valve (4) is connected to the inner wall of the base plate (110); The bottom of the spiral spring tensioner (3) is connected to the inner wall of the base plate (110); The spiral spring tensioner (3) includes a spiral spring with a bracket, a wheel, and a pull rope; wherein, The bracket of the spiral spring with support is connected to the base plate; The wheel is mounted on the bracket of the spiral spring with a support. One end of the pull rope is connected to the wheel, and the other end of the pull rope is connected to the moving end cap of the welded bellows assembly; The angular displacement sensor (5) is mounted on the wheel.

2. The spacecraft thermal control fluid loop compensation-accumulator multifunctional compensator of claim 1, wherein Also includes: Sales (8); among which, The angular displacement sensor (5) is mounted on the spiral spring tensioner (3) via the pin (8).

3. The spacecraft thermal control fluid loop compensated-accumulator multifunctional compensator of claim 1, wherein It also includes: electrical connectors (16); wherein, The electrical connector (16) is disposed on the outer wall of the lower bottom assembly (1); The electrical connector (16) is connected to the solenoid valve (4) and the angular displacement sensor (5) respectively.

4. The spacecraft thermal control fluid loop compensation-accumulator multifunctional compensator of claim 1, wherein: The inflation valve includes a gasket (111), a spring (112), a valve head (113), a plug (114), a plug cap (115), and a retaining ring (116); wherein, The gasket (111) is disposed at the bottom of the inflation hole; The plug (114) is connected to the inflation port; The valve head (113) is disposed inside the plug (114); The spring (112) is disposed inside the valve head (113) by means of a retaining ring (116), and the bottom of the spring (112) presses against the gasket (111); The cap (115) is fitted onto the outer surface of the plug (114).

5. The spacecraft thermal control fluid loop compensation-accumulator multifunctional compensator of claim 1, wherein: The welded bellows assembly (2) includes a lower connecting ring, a welded bellows, an upper connecting ring, and a moving end cap; wherein, One end of the welded corrugated pipe is connected to the lower connecting ring, and the other end of the welded corrugated pipe is connected to the upper connecting ring; The top of the upper connecting ring is connected to the moving end cap; The bottom inner side of the upper connecting ring is provided with a circular protrusion to support the arc part of the welded bellows and optimize the stress on the diaphragm. The outer side of the upper connecting ring is provided with an annular groove for embedding the guide ring (7); The lower connecting ring is connected to the lower bottom assembly (1). The upper outer side of the lower connecting ring is provided with a protrusion for welding the corrugated pipe. The upper inner side of the lower connecting ring is provided with an arc protrusion for supporting the corrugated pipe diaphragm.

6. The spacecraft thermal control fluid loop compensation-accumulator multifunctional compensator of claim 1, wherein: The storage tank (6) includes an upper end cap and a cylindrical section; wherein, The upper end cap is connected to the cylindrical section; The cylindrical section is connected to the lower bottom assembly (1).

7. The spacecraft thermal control fluid loop compensation-accumulator multifunctional compensator of claim 5, wherein: The guide ring (7) is a polytetrafluoroethylene ring with an opening and is fixed to the upper connecting ring by screws. There is a gap of 0.25~0.5mm between the outer side of the guide ring (7) and the inner side of the tank body.

8. The spacecraft thermal control fluid loop compensation-accumulator multifunctional compensator of claim 3, wherein It also includes: an electrical connector sealing ring (17); wherein, The electrical connector (16) is disposed on the outer wall of the lower bottom assembly (1) via the electrical connector sealing ring (17).

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