Thrust regulating valve for cryogenic propellant rocket engine

Abstract

The invention relates to a thrust regulating valve for a low-temperature propellant rocket engine. The thrust regulating valve comprises a middle shell, a motor base, a rear end cover and a motor, wherein the motor base and the rear end cover are installed at the two ends of the middle shell respectively, and the motor is installed on the motor base. A propellant inlet and a flowing cavity which communicate with each other are formed in the middle shell, and a propellant outlet communicating with the end, away from the propellant inlet, of the flowing cavity is formed in the rear end cover. The output end of the motor is located in the motor base and is in transmission fit with an adjusting cone, the adjusting cone is in sliding fit with the inner wall of the motor base, and at least two first leakage-proof mechanisms are arranged at the sliding fit position of the adjusting cone and the motor base in the axial direction of the adjusting cone. And a first one-way exhaust mechanism is mounted on the motor base. According to the thrust regulating valve, the overall size and weight of the thrust regulating valve can be reduced, and the torque output capacity of the motor and normal work of the thrust regulating valve can be guaranteed.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a thrust regulating valve for a cryogenic propellant rocket engine. Background Art

[0002] In rocket engines that use cryogenic propellants (such as liquid oxygen and liquid methane), the thrust regulating valve is a key component for achieving precise control of the rocket engine thrust. It is usually installed between the rocket engine and the rocket tank, and can adjust the flow of cryogenic propellant flowing through the valve to precisely control the thrust generated by the rocket engine.

[0003] However, the existing thrust regulating valve has at least the following defects: 1. The existing thrust regulating valve design usually uses a "long neck" packing seal structure to isolate the cryogenic propellant from the motor. This structure has a long axial dimension, which increases the overall volume and weight.

[0004] 2. The "long-neck" packing seal structure cannot effectively prevent cryogenic propellant leakage. When cryogenic propellant leaks, the low temperature is transmitted to the motor, which in turn reduces the motor's torque output capacity in low-temperature environments. Furthermore, when the cryogenic propellant accidentally leaks, the existing thrust regulating valve cannot effectively guide and discharge the leaked cryogenic propellant within the valve body. Therefore, the leaked cryogenic propellant easily accumulates and vaporizes inside the valve body, absorbing moist air, which can freeze the internal components of the thrust regulating valve and make it difficult to ensure its normal operation.

[0005] Therefore, how to reduce the overall volume and weight of the thrust regulating valve, effectively avoid the leakage of cryogenic propellant, and effectively guide and discharge the cryogenic propellant that accidentally leaks inside the valve body, so that the torque output capacity of the motor will not decrease, to ensure the normal operation and continuous stable operation of the thrust regulating valve, has become a problem that needs to be solved urgently. Summary of the Invention

[0006] The purpose of the present invention is to provide a thrust regulating valve for a cryogenic propellant rocket engine to solve the problems existing in the above-mentioned prior art.

[0007] To achieve the above object, the present invention provides the following solutions: The present invention provides a thrust regulating valve for a cryogenic propellant rocket engine, comprising a middle housing, a motor base and a rear end cover respectively mounted at both ends of the middle housing, and a motor mounted on the motor base, wherein: The middle shell is provided with a propellant inlet and a flow cavity that are interconnected, and the rear end cover is provided with a propellant outlet that is connected to an end of the flow cavity away from the propellant inlet; The output end of the motor is located in the motor base and is in transmission cooperation with an adjusting cone. The adjusting cone is in sliding cooperation with the inner wall of the motor base, and at least two first anti-leakage mechanisms are provided along the axial direction of the adjusting cone at the sliding cooperation position between the two. A first one-way exhaust mechanism is installed on the motor base, and a first exhaust duct is opened on the motor base. The sliding fit between the adjustment cone and the inner wall of the motor base is connected to an end of the first exhaust duct close to the adjustment cone, and an end of the first exhaust duct away from the adjustment cone is connected to the first one-way exhaust mechanism. Two first leak prevention mechanisms are respectively located between the flow cavity and the first exhaust duct and between the motor and the first exhaust duct. The flow cavity includes a throat and a recovery area, and the regulating cone includes a tapered area, which is configured to be in contact with and cooperate with the throat to regulate the flow of the cryogenic propellant.

[0008] According to one embodiment of the present invention, a screw-nut pair is installed at the output end of the motor, and the output end of the motor is coupled with the adjusting cone through the screw-nut pair; The screw-nut pair includes a screw and an outer nut threadedly engaged with the screw, the screw and the outer nut are both located in the motor base, and the output end of the motor, the screw, the outer nut and the adjusting cone are all coaxially arranged; One end of the outer sleeve nut close to the motor is connected to the output end of the motor, and one end of the lead screw away from the motor is fixedly connected to the adjusting cone; A milled flat surface is provided on the lead screw along its axial direction, and a limited rotation block is fixedly installed in the motor base. The limited rotation block slides with the milled flat surface to prevent the lead screw from rotating. The limited rotation block is located between the adjusting cone and the outer sleeve nut.

[0009] According to one embodiment of the present invention, a movable cavity coaxially arranged with the adjusting cone is formed on the rear end cover, and an end of the adjusting cone close to the rear end cover is located in the movable cavity and slidably cooperates with the movable cavity; A second anti-leakage mechanism is installed at the sliding fit between the adjusting cone and the rear end cover; A second exhaust duct is provided on the rear end cover, and a second one-way exhaust mechanism is installed on the rear end cover. The end of the second exhaust duct close to the adjusting cone is connected to the movable cavity, and the end of the second exhaust duct away from the adjusting cone is connected to the second one-way exhaust mechanism. The second leak-proof mechanism is located between the recovery area and the second exhaust duct.

[0010] According to one embodiment of the present invention, the first anti-leakage mechanism and the second anti-leakage mechanism both include at least a Variseal seal, wherein: The Variseal seal ring of the first leak-proof mechanism is mounted on the motor base, an inner ring of the Variseal seal ring of the first leak-proof mechanism abuts against an outer wall of the adjustment cone, and two Variseal seal rings of the first leak-proof mechanism are located between the flow cavity and the first exhaust duct, and between the motor and the first exhaust duct, respectively; The Variseal seal of the second leakage prevention mechanism is installed on the rear end cover, the inner ring of the Variseal seal of the second leakage prevention mechanism abuts against the outer wall of the adjustment cone, and the Variseal seal of the second leakage prevention mechanism is located between the recovery area and the second exhaust duct.

[0011] According to one embodiment of the present invention, the first one-way exhaust mechanism and the second one-way exhaust mechanism each include at least an exhaust valve housing, wherein: A third exhaust passage is defined in the exhaust valve housing, the third exhaust passage including a through-blocking cavity disposed in the middle thereof, a spring disposed in the through-blocking cavity, the top end of the spring being connected to the top inner wall of the through-blocking cavity, a spherical blocking block being mounted at the bottom end of the spring, the outer wall of the spherical blocking block being in sliding engagement with the inner wall of the through-blocking cavity; A branch air channel is further provided in the exhaust valve housing, the bottom end of the branch air channel is connected to the bottom end of the through-blocking cavity, and the top end of the branch air channel is connected to the third exhaust channel; The spherical block is configured to block the bottom end of the branch airway to achieve one-way discharge of gas from the branch airway; The bottom end of the third exhaust passage of the first one-way exhaust mechanism is connected to the first exhaust passage, and the bottom end of the third exhaust passage of the second one-way exhaust mechanism is connected to the second exhaust passage.

[0012] According to one embodiment of the present invention, the throat portion comprises a throat inlet region and a throat middle region, wherein the throat middle region is located between the throat inlet region and the recovery region; The throat inlet region is in communication with the propellant inlet, and the recovery region is in communication with the propellant outlet; The throat inlet region is configured to be in contact with and cooperate with the tapered region to regulate the flow of the cryogenic propellant.

[0013] According to one embodiment of the present invention, the tapered area, the throat inlet area and the recovery area are all truncated cone structures; The included angle of the inner side wall of the axial section of the recovery zone is 6°-40°, the included angle of the inner side wall of the axial section of the throat inlet zone is 40°-60°, and the included angle of the outer side wall of the axial section of the tapered zone is smaller than the included angle of the inner side wall of the axial section of the throat inlet zone.

[0014] According to one embodiment of the present invention, the first anti-leakage mechanism and the second anti-leakage mechanism further include at least a pressure cover and a retaining spring, wherein: The gland and the retaining spring of the first leak-proof mechanism are both mounted on the motor base, and the gland and the retaining spring are used to fix the Variseal seal of the first leak-proof mechanism on the motor base to prevent the Variseal seal of the first leak-proof mechanism from axial displacement; The pressure cover and the retaining spring of the second leakage prevention mechanism are both installed on the rear end cover. The pressure cover and the retaining spring of the second leakage prevention mechanism are used to fix the Variseal sealing ring of the second leakage prevention mechanism on the rear end cover to prevent the Variseal sealing ring of the second leakage prevention mechanism from axial displacement.

[0015] According to one embodiment of the present invention, a motor mounting bracket is mounted on the motor, an end of the motor mounting bracket away from the motor is mounted on the motor base, and the motor is connected to the motor base via the motor mounting bracket.

[0016] According to one embodiment of the present invention, static sealing layers are installed at the connections between the motor mounting frame and the motor base, between the motor base and the middle housing, and between the middle housing and the rear end cover.

[0017] Beneficial effects The present invention has at least the following technical effects: 1. By setting the first anti-leakage mechanism, the present invention eliminates the need to use a traditional "long-neck" packing seal structure to isolate the cryogenic propellant from the motor, thereby reducing the axial size of the structure and also reducing the overall volume and weight of the thrust regulating valve.

[0018] 2. The present invention can also effectively prevent the leakage of cryogenic propellant by setting the first anti-leakage mechanism, and will not allow the low temperature to be transmitted to the motor, thereby ensuring the torque output capacity of the motor, that is, the torque output capacity of the motor will not be reduced, thereby ensuring the normal operation and continuous stable operation of the thrust regulating valve.

[0019] 3. The present invention, through the provision of the first one-way exhaust mechanism, can unidirectionally guide and discharge the accidentally leaked cryogenic propellant, and at the same time prevent external moist air from being sucked into the thrust regulating valve body, thereby preventing the internal components of the thrust regulating valve body from icing and freezing, thereby ensuring the normal operation and continuous and stable operation of the thrust regulating valve. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 It is a schematic cross-sectional view of the overall structure of the present invention; Figure 2 for Figure 1 A partial enlarged view of point A in the middle; Figure 3 for Figure 1 A partial enlarged view of point B in the middle; Figure 4 for Figure 1 A partial enlarged view of point C in the middle; Figure 5 for Figure 1 A partial enlarged view of point D in the middle; Figure 6 for Figure 1 Schematic cross-sectional view along the EE direction; Figure 7 for Figure 3 Schematic diagram of the angles between the mid-cone area, throat inlet area, and recovery area; Figure 8 for Figure 1 A partial enlarged view of point F in the middle; Figure 9 Schematic diagram of the overall structure of the lead screw, outer nut and rotation limit block in the present invention; Figure 10 for Figure 9 Schematic diagram of the overall structure from another angle.

[0022] Description of reference numerals: 1. Motor; 2. Screw; 3. Motor mounting bracket; 4. Motor base; 5. Middle housing; 6. Rear end cover; 7. Propellant inlet; 8. Propellant outlet; 9. Adjusting cone; 901. Conical area; 10. Flow cavity; 1001. Throat inlet area; 1002. Throat middle area; 1003. Recovery area; 11. Pressure cap; 12. Circlip; 13. Universal seal ring; 14. First exhaust duct; 15. Second exhaust duct; 16. Moving cavity; 17. Exhaust valve housing; 18. Third exhaust duct; 19. Spring; 20. Spherical block; 21. Branch air duct; 22. Through-blocking cavity; 23. Outer sleeve nut; 24. Rotation limit block. DETAILED DESCRIPTION

[0023] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In order to make the purposes, technical solutions and advantages of the present invention more clear, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and are used to illustrate the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or areas in the drawings may be enlarged for other structural components or areas to facilitate understanding of the embodiments of the present invention.

[0024] The directional words appearing in the following description refer to the directions shown in the drawings and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected through an intermediate medium. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0025] In addition, the terms "include", "comprising", "having" or any other variations thereof are intended to cover non-exclusive inclusion, so that a structure or component comprising a series of elements includes not only those elements, but also other mechanical elements not explicitly listed or inherent in the structure or component. In the absence of more limitations, the elements defined by the sentence "comprising..." do not exclude the presence of other identical elements in the article or device comprising the elements.

[0026] Spatially relative terms such as "below," "beneath," "under," "low," "above," "on," "high," and the like are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to encompass different orientations of the device in addition to those shown in the figures. Additionally, for example, "one element is above / below another element" may indicate that the two elements are in direct contact, or may indicate that there are other elements between the two elements. Furthermore, terms such as "first," "second," and the like are also used to describe various elements, regions, portions, and the like, and do not specifically refer to an order or sequence, and should not be considered limiting. Similar terms are used throughout the description to indicate similar elements.

[0027] For those skilled in the art, the present invention can be implemented without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention.

[0028] Reference Figures 1-10 The present invention provides a thrust regulating valve for a cryogenic propellant rocket engine. Figure 1 As shown, it at least includes a middle shell 5, a motor base 4 and a rear end cover 6 respectively mounted at both ends of the middle shell 5, and a motor 1 mounted on the motor base 4, wherein: like Figure 1 As shown, a number of bolts are installed on the outer walls of the middle shell 5 and the rear end cover 6, so that the thrust regulating valve can be connected to the rocket body, which will not be described in detail here.

[0029] like Figure 1 As shown, the middle shell 5 is provided with a propellant inlet 7 and a flow cavity 10 that are interconnected, and the rear end cover 6 is provided with a propellant outlet 8 that is connected to the end of the flow cavity 10 away from the propellant inlet 7, that is, the propellant inlet 7 and the flow cavity 10 are connected at Figure 1 The right end of the propellant outlet 8 is connected to the flow cavity 10. Figure 1 The left end of the propellant inlet 7 is connected to the propellant outlet 8 through the flow cavity 10.

[0030] In this embodiment, it should be understood that the flow direction of the cryogenic propellant is the propellant inlet 7, the flow cavity 10, and the propellant outlet 8, wherein the cryogenic propellant can be liquid oxygen and liquid methane known in the art, etc., and is not particularly limited here.

[0031] like Figure 1 As shown, the propellant outlet 8 can be a structure with parallel ends and an inclined middle portion. Figure 6 As shown, the propellant outlet 8 is close to one end of the flow cavity 10 (i.e. Figure 1The right end of the propellant outlet 8) can be a structure with 1-8 evenly arranged holes, and the number is preferably Figure 6 Three shown.

[0032] like Figure 1 As shown, the output end of the motor 1 (i.e., the output shaft of the motor 1) is located in the motor base 4 and is in transmission cooperation with an adjusting cone 9. The adjusting cone 9 is in sliding cooperation with the inner wall of the motor base 4 and is in the axial direction of the adjusting cone 9 (i.e., along the direction of the adjusting cone 9). Figure 2 At least two first leakage prevention mechanisms are provided (in the horizontal direction), preferably two first leakage prevention mechanisms.

[0033] Preferably, the regulating cone 9 , the flow cavity 10 and the end of the propellant outlet 8 away from the flow cavity 10 are all arranged in parallel.

[0034] More preferably, in this embodiment, if Figure 1 As shown, the regulating cone 9, the flow cavity 10 and the end of the propellant outlet 8 away from the flow cavity 10 are all coaxially arranged.

[0035] Specifically, if Figure 1 、 Figure 2 、 Figure 8 、 Figure 9 and Figure 10 As shown, a screw-nut pair is installed on the output end of the motor 1 (ie, the output shaft of the motor 1 ), so that the output end of the motor 1 can be transmission-matched with the adjusting cone 9 through the screw-nut pair.

[0036] More specifically, if Figures 8-10 As shown, the screw-nut pair includes a screw 2 and an outer nut 23 threadedly engaged with the screw 2. The screw 2 and the outer nut 23 are both located within the motor base 4. The output end of the motor 1 (i.e., the output shaft of the motor 1), the screw 2, the outer nut 23, and the adjusting cone 9 are all coaxially arranged.

[0037] like Figure 8 As shown, the outer nut 23 is close to one end of the motor 1 (i.e. Figure 8 The right end of the outer sleeve nut 23) and the output end of the motor 1 (ie Figure 8 The left end of the output terminal of motor 1 is connected. Figure 2 As shown, the end of the screw 2 away from the motor 1 (i.e. Figure 1 and Figure 2 The left end of the middle screw 2 is fixedly connected to the adjusting cone 9.

[0038] In this embodiment, the output end of the motor 1 and the outer sleeve nut 23 can be connected by a flat key (not shown in the figure) known in the art, and the screw 2 and the adjusting cone 9 can be fixedly connected by a welding connection method known in the art, etc. The above connection methods are not particularly limited.

[0039] like Figure 9 and Figure 10 As shown, a milled flat surface is provided on the screw 2 along its (i.e., the screw 2) axial direction. Figure 8 As shown, a rotation limiter 24 is fixedly mounted within the motor base 4. The rotation limiter 24 is configured to slideably engage with the milled flat surface on the lead screw 2, thereby preventing the lead screw 2 from rotating (i.e., rotating in its circumferential direction), thereby preventing the adjusting cone 9 from rotating in its circumferential direction. This ensures that the lead screw 2 and adjusting cone 9 can only move in the axial direction through the rotation of the outer nut 23. The rotation limiter 24 is located between the adjusting cone 9 and the outer nut 23.

[0040] In this embodiment, the shape of the rotation-limiting block 24 is not particularly limited, as long as it can prevent the screw 2 from rotating. Figure 9 and Figure 10 As shown, the rotation limiting block 24 can be a flat rectangular parallelepiped structure, and the outer side wall of one end thereof contacts and slides with the milled flat surface on the lead screw 2.

[0041] In this embodiment, both ends of the rotation limiting block 24 can be fixedly mounted inside the motor base 4 by welding connections known in the art, which is not particularly limited herein.

[0042] When the thrust regulating valve is used, the rotation of the output end of the motor 1 (i.e., the output shaft of the motor 1) drives the outer sleeve nut 23 to rotate. Since the outer sleeve nut 23 is threadedly engaged with the lead screw 2, the rotation of the outer sleeve nut 23 causes the lead screw 2 to move along its own axial direction, and thus causes the regulating cone 9 to move along its own axial direction, thereby regulating the flow rate of the cryogenic propellant.

[0043] It should be understood that if Figure 10 As shown, the position of the milled flat surface will not be higher than the diameter of the cross section of the screw 2 (i.e., the cross section perpendicular to the axial direction of the screw 2), that is, the cross-sectional area of ​​the screw 2 with the milled flat surface will be larger than half the area of ​​the cross-sectional area of ​​the screw 2, thereby ensuring normal threaded fit between the screw 2 and the outer sleeve nut 23.

[0044] Preferably, the above-mentioned screw-nut pair can be a ball screw pair known in the art, that is, the screw 2 can be a ball screw known in the art, thereby reducing the friction force of the threaded fit between the screw 2 and the outer nut 23, which will not be elaborated here.

[0045] More preferably, the adjustment cone 9 and the middle shell 5 can be made of nickel-based alloy or stainless steel with relatively high surface roughness (nickel-based alloy or stainless steel are materials known in the art), thereby reducing damage caused by cavitation of cryogenic propellant and extending service life.

[0046] More specifically, the surface roughness of the adjustment cone 9 and the middle shell 5 may both be Ra1.0 μm-Ra1.6 μm, which is not particularly limited herein.

[0047] In addition, it should be understood that since the screw 2 and the outer nut 23 are threaded together, the two will produce a "self-locking" effect, that is, the adjusting cone 9 (that is, the screw 2) can only move in the axial direction under the rotation of the outer nut 23, and will not move in the axial direction itself to cause the outer nut 23 to rotate.

[0048] like Figure 1 and Figure 5 As shown, a first one-way exhaust mechanism is installed on the motor base 4, and a first exhaust duct 14 is opened on the motor base 4. The sliding fit between the adjustment cone 9 and the inner wall of the motor base 4 is connected to the end of the first exhaust duct 14 close to the adjustment cone 9, and the end of the first exhaust duct 14 away from the adjustment cone 9 is connected to the first one-way exhaust mechanism. Figure 1 and Figure 2 As shown, the two first leakage prevention mechanisms are respectively located between the flow cavity 10 and the first exhaust duct 14 and between the motor 1 and the first exhaust duct 14, that is, one of the first leakage prevention mechanisms is located between the flow cavity 10 and the first exhaust duct 14, and the other first leakage prevention mechanism is located between the motor 1 and the first exhaust duct 14.

[0049] In this embodiment, if Figure 1 As shown, the first one-way exhaust mechanism (i.e. Figure 1 The first exhaust duct 14 is preferably vertically disposed within the motor base 4. Its top end (i.e., the end of the first exhaust duct 14 away from the adjustment cone 9) is connected to the first one-way exhaust mechanism, and its bottom end (i.e., the end of the first exhaust duct 14 closer to the adjustment cone 9) is connected to the sliding fit between the adjustment cone 9 and the inner wall of the motor base 4.

[0050] In this embodiment, the sliding fit between the adjusting cone 9 and the inner wall of the motor base 4 can be a micro-gap fit, for example, the gap between the two can be 0.1mm-0.5mm, thereby making the sliding fit between the adjusting cone 9 and the inner wall of the motor base 4 connected to the bottom end of the first exhaust duct 14.

[0051] like Figure 1 and Figure 2 As shown, since the number of the first leakage prevention mechanism is preferably two, that is, Figure 2 As shown in FIG, one of the first leakage prevention mechanisms is located between the flow cavity 10 and the first exhaust passage 14, and the other first leakage prevention mechanism is located between the motor 1 and the first exhaust passage 14. That is, the two first leakage prevention mechanisms are respectively located on both sides of the first exhaust passage 14. Therefore, the provision of the two first leakage prevention mechanisms can more effectively prevent leakage of the cryogenic propellant.

[0052] like Figure 1 and Figure 3 As shown, the flow cavity 10 includes a throat and a recovery zone 1003, and the regulating cone 9 includes a tapered zone 901. The tapered zone 901 is configured to be able to contact and cooperate with the throat to regulate the flow of the cryogenic propellant, that is, to regulate the flow of the cryogenic propellant entering the recovery zone 1003 from the propellant inlet 7.

[0053] Specifically, if Figure 3 As shown, the throat includes a throat inlet area 1001 and a throat middle area 1002, and the throat middle area 1002 is located between the throat inlet area 1001 and the recovery area 1003. Figure 3 In the figure, the right end of the throat inlet area 1001 is connected to the propellant inlet 7. Figure 1 In the figure, the left end of the recovery zone 1003 is connected to the propellant outlet 8. The throat inlet zone 1001 is configured to contact and cooperate with the tapered zone 901 to adjust the flow rate of the cryogenic propellant. That is, by adjusting the movement of the cone 9 along its own axial direction, the flow rate of the cryogenic propellant entering the recovery zone 1003 from the throat inlet zone 1001 is adjusted.

[0054] In this embodiment, if Figure 3 As shown, the conical area 901, the throat inlet area 1001 and the recovery area 1003 are all truncated cone structures, while the throat middle area 1002 can be a cylindrical structure. Figure 3 As shown, the small circular surface of the throat inlet area 1001 and the small circular surface of the recovery area 1003 are respectively connected to the two ends of the throat middle area 1002. The small circular surface of the tapered area 901 and the small circular surface of the throat inlet area 1001 are arranged in the same direction.

[0055] In this embodiment, if Figure 3 and Figure 7As shown, the included angle of the inner side wall of the axial cross-section of the recovery zone 1003 (i.e., the cross-section parallel to the axial direction of the recovery zone 1003) (i.e., the included angle of the extension lines of the inner side walls of the axial cross-section of the recovery zone 1003 on opposite sides) is 6°-40°, and is preferably 18°; the included angle of the inner side wall of the axial cross-section of the throat inlet zone 1001 (i.e., the included angle of the extension lines of the inner side walls of the axial cross-section of the throat inlet zone 1001 on opposite sides) is 40°-60°, and is preferably 60°; the included angle of the outer side wall of the axial cross-section of the tapered zone 901 (i.e., the included angle of the extension lines of the outer side walls of the axial cross-section of the tapered zone 901 on opposite sides) is smaller than the included angle of the inner side wall of the axial cross-section of the throat inlet zone 1001 (i.e., smaller than the included angle of the extension lines of the inner side walls of the axial cross-section of the throat inlet zone 1001 on opposite sides), and is preferably 19°.

[0056] By setting the above angles, the cryogenic propellant flow rate at the throat is linearly related to the horizontal displacement of the regulating cone 9, thereby enabling more accurate control and adjustment of the cryogenic propellant flow rate. For details, please refer to Chinese invention patent application number "201410189054.7", the content of which is incorporated herein by reference in its entirety and will not be further elaborated here.

[0057] In this embodiment, the adjustment range of the rocket engine thrust by the throat inlet area 1001 and the conical area 901 can be 30%-120%, and the maximum cryogenic propellant flow rate can be 11.5 kg / s, which will not be elaborated here.

[0058] Furthermore, the thrust control valve includes a linear displacement sensor (not shown) capable of measuring the relative position of the control cone 9 to determine the position of the conical region 901. The calculated result of the measurement at this position is then fed back to the rocket system, which then determines whether to further adjust the position of the control cone 9 based on the input result. This allows for more accurate and precise control and regulation of the cryogenic propellant flow rate. The linear displacement sensor may be any known LVDT, encoder, or grating linear displacement sensor, and is not particularly limited herein.

[0059] According to one embodiment of the present invention, Figure 1 and Figure 4 As shown, a movable cavity 16 is provided on the rear end cover 6 and is coaxially arranged with the adjusting cone 9. The movable cavity 16 is adapted to the end of the adjusting cone 9 close to the movable cavity 16. The end of the adjusting cone 9 close to the rear end cover 6 is located in the movable cavity 16 and slides with the inner side wall of the movable cavity 16.

[0060] like Figure 4 As shown, a second anti-leakage mechanism is installed at the sliding fit between the adjusting cone 9 and the rear end cover 6.

[0061] like Figure 1 As shown, the rear end cover 6 is provided with a second exhaust duct 15, which can be arranged in parallel with the first exhaust duct 14. A second one-way exhaust mechanism is installed on the rear end cover 6, preferably installed on the top of the rear end cover 6. The second exhaust duct 15 is close to one end of the regulating cone 9 (i.e. Figure 1 The bottom end of the second exhaust passage 15 in the middle is connected to the moving cavity 16, and the second exhaust passage 15 is away from the end of the adjustment cone 9 (i.e. Figure 1 The top of the second exhaust passage 15 is connected to the second one-way exhaust mechanism. Figure 1 As shown, the second leakage prevention mechanism is located between the recovery area 1003 and the second exhaust passage 15 .

[0062] In this embodiment, both the first and second leak-proof mechanisms effectively prevent leakage of the cryogenic propellant within the flow cavity 10, thereby preventing the low temperature from being transferred to the motor 1 and ensuring the torque output capacity of the motor 1. If the cryogenic propellant still accidentally leaks and vaporizes, the first and second exhaust ducts 14 and 15 can respectively direct the leaked and vaporized cryogenic propellant into the first and second one-way exhaust mechanisms and discharge it from there, thereby preventing the vaporized cryogenic propellant from accumulating within the thrust regulating valve body. Furthermore, the first and second one-way exhaust mechanisms only allow gas to pass in one direction, i.e., only allowing the vaporized cryogenic propellant to be discharged from within the thrust regulating valve body, preventing external moist air from being drawn into the thrust regulating valve body and preventing ice or freezing of the internal components of the thrust regulating valve body, thereby ensuring the normal operation and sustained stable operation of the thrust regulating valve.

[0063] In addition, since the first and second anti-leakage mechanisms are used to prevent leakage of the cryogenic propellant, there is no need to use a traditional "long-neck" packing seal structure to isolate the cryogenic propellant from the motor, thereby reducing the overall volume and weight of the thrust regulating valve.

[0064] Specifically, if Figure 2 and Figure 4 As shown, both the first anti-leakage mechanism and the second anti-leakage mechanism include at least a Variseal seal 13 (i.e., a spring-energized seal known in the art), and the Variseal seal 13 is coaxially arranged with the adjustment cone 9, wherein: like Figure 2As shown, the two first leak prevention mechanisms' Variseal seals 13 are both mounted on the inner wall of the motor base 4, and their inner rings abut the outer wall of the adjustment cone 9. The two first leak prevention mechanisms' Variseal seals 13 are located between the flow cavity 10 and the first exhaust duct 14, and between the motor 1 and the first exhaust duct 14, respectively. Specifically, one first leak prevention mechanism's Variseal seal 13 is located between the flow cavity 10 and the first exhaust duct 14, while the other first leak prevention mechanism's Variseal seal 13 is located between the motor 1 and the first exhaust duct 14. In other words, the two first leak prevention mechanisms' Variseal seals 13 are located on either side of the first exhaust duct 14.

[0065] like Figure 4 As shown, the second anti-leakage mechanism's Variseal seal 13 is mounted on the inner wall of the rear end cover 6 , the inner ring of the second anti-leakage mechanism's Variseal seal 13 abuts against the outer wall of the adjustment cone 9 , and the second anti-leakage mechanism's Variseal seal 13 is located between the recovery area 1003 and the second exhaust duct 15 .

[0066] In this embodiment, the provision of the Variseal seal 13 can effectively prevent leakage of cryogenic propellant, thereby ensuring the normal operation and continuous and stable operation of the thrust regulating valve.

[0067] When adjusting the flow rate of the cryogenic propellant, the regulating cone 9 will be displaced axially by the motor 1, and the Variseal seal 13 will also easily displace axially along with the regulating cone 9. Therefore, to prevent the Variseal seal 13 from axially displacing along with the regulating cone 9 and thereby ensure the secure installation and continuous sealing of the Variseal seal 13, the first and second leak-proof mechanisms further include at least a gland 11 and a retaining spring 12, wherein: like Figure 2 As shown, the glands 11 and retaining springs 12 of the two first leakage prevention mechanisms are mounted on the inner wall of the motor base 4. Each gland 11 and retaining spring 12 of the first leakage prevention mechanism is used to securely fix the corresponding Variseal seal 13 of the first leakage prevention mechanism to the inner wall of the motor base 4, thereby preventing the Variseal seal 13 of the first leakage prevention mechanism from axially displacing along with the adjusting cone 9.

[0068] In this embodiment, if Figure 2 As shown, the pressure cover 11 and the retaining spring 12 of the first leakage prevention mechanism on the left side of the first exhaust duct 14 are arranged in sequence from left to right, and the pressure cover 11 and the retaining spring 12 of the first leakage prevention mechanism on the right side of the first exhaust duct 14 are arranged in sequence from right to left, that is, the retaining spring 12 of each first leakage prevention mechanism is located between the corresponding pressure cover 11 and the Variseal sealing ring 13.

[0069] like Figure 4As shown, the gland 11 and the retaining spring 12 of the second leak prevention mechanism are both mounted on the inner wall of the rear end cover 6. The gland 11 and the retaining spring 12 are used to securely fix the Variseal seal 13 of the second leak prevention mechanism to the inner wall of the rear end cover 6, thereby preventing the Variseal seal 13 of the second leak prevention mechanism from axially displacing along with the adjusting cone 9.

[0070] In this embodiment, if Figure 4 As shown, the second leakage prevention mechanism pressure cover 11 and the retaining spring 12 are arranged in sequence from right to left, that is, the retaining spring 12 of the second leakage prevention mechanism is located between the second leakage prevention mechanism pressure cover 11 and the second leakage prevention mechanism's PanSeal seal 13.

[0071] In addition, the Variseal seal ring 13 may be fixed by threads and wire holes to prevent the Variseal seal ring 13 from axially displacing along with the adjusting cone 9, which is not particularly limited herein.

[0072] Specifically, if Figure 1 and Figure 5 As shown, the first one-way exhaust mechanism and the second one-way exhaust mechanism each include at least an exhaust valve housing 17, wherein: like Figure 1 and Figure 5 As shown, the exhaust valve housing 17 of the first one-way exhaust mechanism is installed on the top of the motor base 4, and the exhaust valve housing 17 of the second one-way exhaust mechanism is installed on the top of the rear end cover 6.

[0073] like Figure 5 As shown, a third exhaust passage 18 is vertically defined within the exhaust valve housing 17. The third exhaust passage 18 includes at least a centrally located through-and-blocking cavity 22, the aperture of which is larger than that of the third exhaust passage 18. A spring 19 is disposed within the through-and-blocking cavity 22, the top end of which is connected to the top inner wall of the through-and-blocking cavity 22. A spherical block 20 is mounted on the bottom end of the spring 19, the outer wall of which slides in engagement with the inner wall of the through-and-blocking cavity 22. A branch air passage 21 is also defined within the exhaust valve housing 17. The bottom end of the branch air passage 21 communicates with the bottom end of the through-and-blocking cavity 22, and the top end of the branch air passage 21 communicates with the third exhaust passage 18. The bottom end of the third exhaust passage 18 of the first one-way exhaust mechanism communicates with the first exhaust passage 14, while the bottom end of the third exhaust passage 18 of the second one-way exhaust mechanism communicates with the second exhaust passage 15. The spherical blocking block 20 is configured to block the bottom end of the branch airway 21 and slide up and down inside the blocking cavity 22 , thereby achieving one-way discharge of gas from the branch airway 21 .

[0074] In this embodiment, if Figure 5As shown, the number of branch airways 21 can be several, preferably two, and they are symmetrically arranged with the clear and block cavity 22 as the symmetry axis. The branch airways 21 can be or approximately be L-shaped.

[0075] Preferably, if Figure 5 As shown, the bottom end of the branch airway 21 can be an arc-shaped structure that matches the outer wall of the spherical blockage 20 and is located below the horizontal diameter line of the spherical blockage 20, thereby making the bottom end of the branch airway 21 fit more closely with the outer wall of the spherical blockage 20.

[0076] Taking the first exhaust passage 14 as an example, Figure 5 As shown, when the cryogenic propellant leaks, the vaporized cryogenic propellant will flow through the first exhaust passage 14 to the top of the first exhaust passage 14. Since the spherical block 20 will continue to block the bottom of the branch air passage 21 and the bottom of the blocking cavity 22 under the elastic force of the spring 19 in the default state, the vaporized cryogenic propellant will push the spherical block 20 upward due to its own gas pressure and compress the spring 19. At this time, the vaporized cryogenic propellant will flow through the branch air passage 21 into the third exhaust passage 18 and be discharged from the top of the third exhaust passage 18, realizing a one-way discharge of the cryogenic propellant. When the cryogenic propellant is not leaking, the spherical block 20 will continue to block the bottom of the branch air passage 21 and the bottom of the blocking cavity 22 under the elastic force of the spring 19, thereby preventing external moist air from being drawn into the interior of the thrust regulating valve body, thereby ensuring the normal operation and continuous stable operation of the thrust regulating valve.

[0077] Furthermore, in order to improve the firmness of the motor 1 on the motor base 4, as Figure 1 As shown, a motor mounting frame 3 is mounted on the motor 1 , and one end of the motor mounting frame 3 away from the motor 1 is mounted on the motor base 4 , and the motor 1 is connected to the motor base 4 through the motor mounting frame 3 .

[0078] In this embodiment, if Figure 1 As shown, the motor mounting bracket 3 is mounted on the right end of the motor base 4, and the two can be connected by a number of bolts.

[0079] Furthermore, in order to improve the sealing performance of the joints between the motor mounting frame 3 and the motor base 4, between the motor base 4 and the middle housing 5, and between the middle housing 5 and the rear end cover 6, and further prevent the cryogenic propellant from leaking, as shown in FIG. Figure 1 As shown, static sealing layers are installed at the connections between the motor mounting frame 3 and the motor base 4 , between the motor base 4 and the middle housing 5 , and between the middle housing 5 and the rear end cover 6 .

[0080] In this embodiment, the static sealing layer may be made of polytetrafluoroethylene or perfluoroether rubber, which is known in the art and is suitable for cryogenic environments, and is not particularly limited here.

[0081] In addition, due to space limitations on the engine, the design of existing thrust regulating valves makes it difficult to arrange a sufficiently long pressure recovery zone, and the throat inlet is usually perpendicular to the throat outlet. As a result, the low-temperature propellant will have a high degree of turbulence at the outlet, making it difficult to achieve high-precision flow control (because the flow is easily affected by outlet pressure fluctuations), and there is a large pressure loss at the inlet and outlet.

[0082] In this embodiment, the throat inlet and the throat outlet are coaxially arranged, that is, the throat inlet area 1001 and the recovery area 1003 are coaxially arranged, and the length of the recovery area 1003 is relatively long. Therefore, the turbulence degree of the cryogenic propellant in the recovery area 1003 can be reduced, thereby achieving steady flow and high-precision flow control of the cryogenic propellant, and avoiding large pressure losses at the inlet and outlet.

[0083] It should be understood by those skilled in the art that the above embodiments or implementation plans of the present invention may be combined with each other and have corresponding technical effects.

[0084] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A thrust regulating valve for a cryogenic propellant rocket engine, characterized in that: It comprises a middle shell (5), a motor base (4) and a rear end cover (6) respectively mounted on both ends of the middle shell (5), and a motor (1) mounted on the motor base (4), wherein: The middle shell (5) is provided with a propellant inlet (7) and a flow cavity (10) that are interconnected, and the rear end cover (6) is provided with a propellant outlet (8) that is connected to an end of the flow cavity (10) away from the propellant inlet (7); The output end of the motor (1) is located in the motor base (4) and is transmission-matched with an adjusting cone (9), the adjusting cone (9) is slidingly matched with the inner wall of the motor base (4), and at least two first anti-leakage mechanisms are provided along the axial direction of the adjusting cone (9) at the sliding match between the two. A first one-way exhaust mechanism is installed on the motor base (4), and a first exhaust duct (14) is opened on the motor base (4); a sliding fit between the adjustment cone (9) and the inner wall of the motor base (4) is connected to an end of the first exhaust duct (14) close to the adjustment cone (9); an end of the first exhaust duct (14) away from the adjustment cone (9) is connected to the first one-way exhaust mechanism; and two first leak-proof mechanisms are respectively located between the flow cavity (10) and the first exhaust duct (14), and between the motor (1) and the first exhaust duct (14); The flow cavity (10) includes a throat and a recovery area (1003), and the regulating cone (9) includes a tapered area (901), and the tapered area (901) is configured to be able to contact and cooperate with the throat to regulate the flow rate of the cryogenic propellant.

2. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 1, characterized in that: The output end of the motor (1) is equipped with a screw nut pair, and the output end of the motor (1) is in transmission cooperation with the adjusting cone (9) through the screw nut pair; The screw-nut pair comprises a screw (2) and an outer nut (23) threadedly engaged with the screw (2), the screw (2) and the outer nut (23) are both located in the motor base (4), and the output end of the motor (1), the screw (2), the outer nut (23) and the adjusting cone (9) are all coaxially arranged; One end of the outer sleeve nut (23) close to the motor (1) is connected to the output end of the motor (1), and one end of the lead screw (2) away from the motor (1) is fixedly connected to the adjusting cone (9); The lead screw (2) is provided with a milled flat surface along its axial direction, and a rotation limiting block (24) is fixedly installed in the motor base (4). The rotation limiting block (24) is slidably engaged with the milled flat surface to prevent the lead screw (2) from rotating. The rotation limiting block (24) is located between the adjusting cone (9) and the outer sleeve nut (23).

3. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 1, wherein: The rear end cover (6) is provided with a movable cavity (16) coaxially arranged with the adjustment cone (9); an end of the adjustment cone (9) close to the rear end cover (6) is located in the movable cavity (16) and is in sliding engagement with the movable cavity (16); A second anti-leakage mechanism is installed at the sliding fit between the adjusting cone (9) and the rear end cover (6); A second exhaust duct (15) is provided on the rear end cover (6), and a second one-way exhaust mechanism is installed on the rear end cover (6). An end of the second exhaust duct (15) close to the regulating cone (9) is connected to the movable cavity (16), and an end of the second exhaust duct (15) away from the regulating cone (9) is connected to the second one-way exhaust mechanism. The second anti-leakage mechanism is located between the recovery area (1003) and the second exhaust duct (15).

4. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 3, wherein: The first anti-leakage mechanism and the second anti-leakage mechanism both include at least a Variseal seal ring (13), wherein: The universal seal ring (13) of the first anti-leakage mechanism is installed on the motor base (4), the inner ring of the universal seal ring (13) of the first anti-leakage mechanism abuts against the outer wall of the adjustment cone (9), and the two universal seal rings (13) of the first anti-leakage mechanism are respectively located between the flow cavity (10) and the first exhaust duct (14), and between the motor (1) and the first exhaust duct (14); The Pan-Seal seal ring (13) of the second anti-leakage mechanism is mounted on the rear end cover (6), the inner ring of the Pan-Seal seal ring (13) of the second anti-leakage mechanism abuts against the outer wall of the regulating cone (9), and the Pan-Seal seal ring (13) of the second anti-leakage mechanism is located between the recovery area (1003) and the second exhaust duct (15).

5. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 3, characterized in that: The first one-way exhaust mechanism and the second one-way exhaust mechanism both comprise at least an exhaust valve housing (17), wherein: A third exhaust passage (18) is provided in the exhaust valve housing (17), and the third exhaust passage (18) includes a through-blocking cavity (22) provided in the middle thereof. A spring (19) is provided in the through-blocking cavity (22), and the top end of the spring (19) is connected to the inner wall of the top end of the through-blocking cavity (22). A spherical block (20) is installed at the bottom end of the spring (19), and the outer wall of the spherical block (20) is slidably matched with the inner wall of the through-blocking cavity (22). A branch air channel (21) is further provided in the exhaust valve housing (17), the bottom end of the branch air channel (21) being connected to the bottom end of the through-blocking cavity (22), and the top end of the branch air channel (21) being connected to the third exhaust channel (18); The spherical block (20) is configured to block the bottom end of the branch airway (21) to achieve one-way discharge of gas from the branch airway (21); The bottom end of the third exhaust duct (18) of the first one-way exhaust mechanism is connected to the first exhaust duct (14), and the bottom end of the third exhaust duct (18) of the second one-way exhaust mechanism is connected to the second exhaust duct (15).

6. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 1, wherein: The throat comprises a throat inlet area (1001) and a throat middle area (1002), wherein the throat middle area (1002) is located between the throat inlet area (1001) and the recovery area (1003); The throat inlet area (1001) is connected to the propellant inlet (7), and the recovery area (1003) is connected to the propellant outlet (8); The throat inlet region (1001) is configured to be in contact with and cooperate with the conical region (901) to regulate the flow of the cryogenic propellant.

7. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 6, wherein: The conical area (901), the throat inlet area (1001) and the recovery area (1003) are all truncated cone structures; The included angle of the inner side wall of the axial section of the recovery zone (1003) is 6°-40°, the included angle of the inner side wall of the axial section of the throat inlet zone (1001) is 40°-60°, and the included angle of the outer side wall of the axial section of the tapered zone (901) is smaller than the included angle of the inner side wall of the axial section of the throat inlet zone (1001).

8. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 4, wherein: The first anti-leakage mechanism and the second anti-leakage mechanism also each comprise at least a pressure cover (11) and a retaining spring (12), wherein: The pressure cover (11) and the retaining spring (12) of the first anti-leakage mechanism are both mounted on the motor base (4), and the pressure cover (11) and the retaining spring (12) of the first anti-leakage mechanism are used to fix the universal seal ring (13) of the first anti-leakage mechanism on the motor base (4) to prevent the universal seal ring (13) of the first anti-leakage mechanism from generating axial displacement; The pressure cover (11) and the retaining spring (12) of the second anti-leakage mechanism are both mounted on the rear end cover (6). The pressure cover (11) and the retaining spring (12) of the second anti-leakage mechanism are used to fix the universal seal ring (13) of the second anti-leakage mechanism on the rear end cover (6) to prevent the universal seal ring (13) of the second anti-leakage mechanism from generating axial displacement.

9. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 1, wherein: A motor mounting frame (3) is mounted on the motor (1), and one end of the motor mounting frame (3) away from the motor (1) is mounted on the motor base (4), and the motor (1) is connected to the motor base (4) via the motor mounting frame (3).

10. The thrust regulating valve for a cryogenic propellant rocket engine according to claim 9, characterized in that: Static sealing layers are installed at the connections between the motor mounting frame (3) and the motor base (4), between the motor base (4) and the middle housing (5), and between the middle housing (5) and the rear end cover (6).

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