CN220470077U - Thrust chamber structure, liquid rocket engine and thrust simulation test device - Google Patents
Thrust chamber structure, liquid rocket engine and thrust simulation test device Download PDFInfo
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- CN220470077U CN220470077U CN202322305696.6U CN202322305696U CN220470077U CN 220470077 U CN220470077 U CN 220470077U CN 202322305696 U CN202322305696 U CN 202322305696U CN 220470077 U CN220470077 U CN 220470077U
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Abstract
The embodiment of the application discloses a thrust chamber structure, a liquid rocket engine and a thrust simulation test device, and relates to the technology of liquid rocket engines. The thrust chamber structure includes a thrust mechanism, a first connector, a vector assembly, and a drive mechanism. The first connecting piece is provided with a first connecting surface. The vector assembly is provided with a second connection face. The connection part of the first connecting surface and the second connecting surface is in a ring shape or a round shape coaxial with the first direction, so that the thrust mechanism can rotate around the first direction relative to the vector assembly through the first connecting piece under the drive of the driving mechanism, and the first connecting surface is obliquely arranged relative to the extending direction of the first connecting piece, so that the extending direction of the first connecting piece also rotates around the first direction when the first connecting piece rotates around the first direction, and the swing angle of the thrust mechanism is changed. The relative inclination angles of the first connecting surface and the second connecting surface are changed, so that the swing angle range of the thrust mechanism is improved, and the requirements of different thrust directions of the liquid rocket engine and the thrust simulation test device are met.
Description
Technical Field
The present application relates to, but not limited to, liquid rocket engine technology, and more particularly to a thrust chamber structure, a liquid rocket engine, and a thrust simulation test device.
Background
Liquid rocket engines are often provided with a vectoring mechanism based on a deflectable/gimbal load carrier for achieving an adjustable angular change of the thrust, through which the angle of oscillation of the thrust mechanism (combustion chamber and nozzle) is controlled. At present, the liquid rocket engine adopting the vector mechanism has a smaller swing angle, generally about +/-4 degrees, and partial commercial aerospace and related field pre-research can achieve swing angle swing of +/-25 degrees in a plane, but the swing angle range is still smaller, so that certain use scene of the liquid rocket engine is limited.
Disclosure of Invention
The application provides a thrust chamber structure, a liquid rocket engine and a thrust simulation test device, and aims to solve the technical problem that a swing angle of a thrust mechanism in the existing thrust chamber structure is smaller.
To achieve the above object, the present application provides a thrust chamber structure, including:
a thrust mechanism;
the first connecting piece is arranged on the thrust mechanism and is provided with a first connecting surface, and the first connecting surface is obliquely arranged relative to the extending direction of the first connecting piece;
the vector assembly is provided with a second connecting surface parallel to the first connecting surface, the second connecting surface is obliquely arranged relative to the extending direction of the vector assembly, the first connecting piece can be rotationally connected with the second connecting surface through the first connecting surface, and the joint of the first connecting surface and the second connecting surface is in a circular ring shape or a round shape coaxial with the first direction; and
And the driving mechanism is arranged to drive the first connecting piece to rotate around the first direction relative to the vector assembly, so that the thrust mechanism rotates around the first direction relative to the vector assembly through the first connecting piece.
To achieve the above object, the present application further provides a liquid rocket engine, including:
a supply and control system; and
In the thrust chamber structure, the vector component is arranged on a corresponding liquid rocket engine bearing mechanism.
In order to achieve the above object, the present application further provides a thrust simulation test device, including:
a test bed; and
In the thrust chamber structure, the vector component is arranged on the test bed force bearing mechanism.
Implementation of the embodiment of the application has the following beneficial effects:
the thrust chamber structure of the scheme is applied to the liquid rocket engine and the thrust simulation test device, not only the liquid rocket engine and the thrust simulation test device have excellent power efficiency, but also the swing angle range of the thrust mechanism can be improved, so that the angle range of the thrust direction of the thrust mechanism is larger, the actual control effect of the liquid rocket engine is improved, and the use scene of the liquid rocket engine is increased. Specifically, the thrust chamber structure comprises a thrust mechanism, a first connecting piece arranged on the thrust mechanism, a vector component and a driving mechanism. The first connecting piece is provided with a first connecting surface which is obliquely arranged relative to the extending direction of the first connecting piece. The vector assembly is provided with a second connecting surface which is obliquely arranged relative to the extending direction of the vector assembly and is parallel to the first connecting surface. The connection part of the first connecting surface and the second connecting surface is in a ring shape or a round shape coaxial with the first direction, so that the thrust mechanism can rotate around the first direction relative to the vector assembly through the first connecting piece under the driving of the driving mechanism. Meanwhile, the inclination angles of the first connecting surface and the second connecting surface can be changed to improve the swing angle range of the thrust mechanism, so that different thrust direction requirements of the liquid rocket engine and the thrust simulation test device can be met. Meanwhile, the vector assembly and the connection position of the vector assembly and the first connecting piece are far away from the thrust mechanism, so that the influence of high-temperature fuel gas on the connection position of the vector assembly and the first connecting piece is reduced, and the precision of the swing angle of the thrust mechanism is ensured. The thrust chamber structure can increase the attitude adjustment capability of the liquid rocket engine, reduce the intervention of an attitude control system, and be beneficial to reducing the redundant quality and increasing the maneuverability and flexibility of an aircraft/spacecraft. In addition, the swing angle of the thrust mechanism can not be changed, so that the original performance of the thrust mechanism is kept unchanged, and the efficiency loss caused by changing the direction of fuel gas after accelerating the fuel gas to supersonic speed is eliminated.
Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application. Other advantages of the present application may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The accompanying drawings are included to provide an understanding of the technical aspects of the present application, and are incorporated in and constitute a part of this specification, illustrate the technical aspects of the present application and together with the examples of the present application, and not constitute a limitation of the technical aspects of the present application.
FIG. 1 is a schematic view of a thrust chamber structure in an embodiment of the present application;
FIG. 2 is a front view of a thrust chamber configuration in an embodiment of the present application;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a schematic view of a first coupling member in a thrust chamber configuration according to an embodiment of the present disclosure, the first coupling surface being viewed from the perspective;
FIG. 5 is a schematic view of a first vector component of a thrust chamber configuration according to an embodiment of the present application, the view being directed toward a second interface;
FIG. 6 is a schematic view of a first vector component of a thrust chamber configuration according to an embodiment of the present application, the view being directed toward a third interface;
FIG. 7 is a schematic view of a second vector component of a thrust chamber configuration according to an embodiment of the present application, the view being directed toward a fourth interface;
FIG. 8 is a schematic diagram of an exploded view of a thrust chamber structure in an embodiment of the present application;
FIG. 9 is a schematic view of another perspective explosion configuration of a thrust chamber configuration in accordance with an embodiment of the present application;
FIG. 10 is a schematic view of a first coupling member in a thrust chamber configuration according to an embodiment of the present disclosure rotated relative to a vector assembly;
FIG. 11 is a schematic view of a thrust chamber structure according to an embodiment of the present disclosure with a first coupling member rotated relative to a vector assembly and a first vector member rotated relative to a second vector member;
FIG. 12 is a side view of a thrust chamber configuration in accordance with another embodiment of the present application;
FIG. 13 is a front view of a thrust chamber configuration in accordance with another embodiment of the present application;
FIG. 14 is a schematic view of a thrust mechanism coupled to a support assembly in a thrust chamber configuration according to another embodiment of the present disclosure.
Reference numerals illustrate:
10. a thrust mechanism; 11. a combustion chamber; 12. a spray pipe; 20. a first connector; 21. a first connection surface; 30. a vector component; 31. a first vector member; 311. a second connection surface; 312. a third connection surface; 32. a second vector member; 321. a fourth connection surface; 40. a support assembly; 41. a cylinder; 42. a push rod; 43. a universal joint; 50. and a second connecting piece.
The realization, functional characteristics and advantages of the present application will be further described with reference to the embodiments, referring to the attached drawings.
Detailed Description
The present application describes a number of embodiments, but the description is illustrative and not limiting and it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the embodiments described herein. Although many possible combinations of features are shown in the drawings and discussed in the detailed description, many other combinations of the disclosed features are possible. Any feature or element of any embodiment may be used in combination with or in place of any other feature or element of any other embodiment unless specifically limited.
The present application includes and contemplates combinations of features and elements known to those of ordinary skill in the art. The embodiments, features and elements of the present disclosure may also be combined with any conventional features or elements to form a unique inventive arrangement as defined in the claims. Any feature or element of any embodiment may also be combined with features or elements from other inventive arrangements to form another unique inventive arrangement as defined in the claims. Thus, it should be understood that any of the features shown and/or discussed in this application may be implemented alone or in any suitable combination. Accordingly, the embodiments are not to be restricted except in light of the attached claims and their equivalents. Further, various modifications and changes may be made within the scope of the appended claims.
Furthermore, in describing representative embodiments, the specification may have presented the method and/or process as a particular sequence of steps. However, to the extent that the method or process does not depend on the particular order of steps described herein, the method or process should not be limited to the particular order of steps described. Other sequences of steps are possible as will be appreciated by those of ordinary skill in the art. Accordingly, the particular order of the steps set forth in the specification should not be construed as limitations on the claims. Furthermore, the claims directed to the method and/or process should not be limited to the performance of their steps in the order written, and one skilled in the art can readily appreciate that the sequences may be varied and still remain within the spirit and scope of the embodiments of the present application.
Liquid rocket engines are often provided with a vectoring mechanism based on a deflectable/gimbal load carrier for achieving an adjustable angular change of the thrust, through which the angle of oscillation of the thrust mechanism (combustion chamber and nozzle) is controlled. At present, the liquid rocket engine adopting the vector mechanism has a smaller swing angle, generally about +/-4 degrees, and partial commercial aerospace and related field pre-research can achieve swing angle swing of +/-25 degrees in a plane, but the swing angle range is still smaller, so that certain use scene of the liquid rocket engine is limited.
In order to solve the technical problems, the embodiment of the application provides a thrust chamber structure, a liquid rocket engine and a thrust simulation test device.
Referring to fig. 1 to 5 and fig. 8 to 10, a liquid rocket engine according to an embodiment of the present application will be described. The liquid rocket engine includes a supply and control system and a thrust chamber structure. The thrust chamber structure includes a thrust mechanism 10, a first link 20, a vector assembly 30, and a drive mechanism (not shown). The thrust mechanism 10 includes a combustion chamber 11 and a nozzle 12, and fuel is combusted in the combustion chamber 11, and formed fuel gas is ejected from the nozzle 12 to generate thrust. The shape of the spout 12 includes, but is not limited to, a cone shape (as shown in fig. 1-3, 8-11) or a bell shape (as shown in fig. 12).
The first connector 20 is provided on the thrust mechanism 10. The first connection piece 20 is provided with a first connection surface 21. The first connecting surface 21 is disposed obliquely with respect to the extending direction of the first connecting member 20.
The vector assembly 30 is provided with a second connection surface 311 parallel to the first connection surface 21. The second connection surface 311 is disposed obliquely with respect to the extending direction of the vector unit 30. The first connector 20 can be rotatably connected to the second connecting surface 311 through the first connecting surface 21, and a connection portion between the first connecting surface 21 and the second connecting surface 311 is in a circular shape or a circular shape coaxial with the first direction. In this embodiment, the first direction is parallel to the direction indicated by the arrow X in fig. 3.
The drive mechanism is configured to drive the first link 20 to rotate about the first direction relative to the vector assembly 30 to rotate the thrust mechanism 10 about the first direction relative to the vector assembly 30 via the first link 20.
Vector assembly 30 is disposed on a corresponding liquid rocket engine load bearing mechanism. The supply and control system can control the thrust mechanism 10 to control ignition and extinction of fuel, fuel consumption, supply of coolant, and the like. At the same time, the feed and control system can also control the drive mechanism to drive the first link 20 to rotate about the first direction relative to the vector assembly 30 to change the throw angle of the thrust mechanism 10 and change the thrust direction.
In an exemplary embodiment, please also combine fig. 1-5 and fig. 8-10, a thrust simulation test apparatus includes a test stand and a thrust chamber structure. The thrust chamber structure includes a thrust mechanism 10, a first link 20, a vector assembly 30, and a drive mechanism. The thrust mechanism 10 includes a combustion chamber 11 and a nozzle 12, and fuel is combusted in the combustion chamber 11 and ejected from the nozzle 12 to generate thrust. The first connector 20 is provided on the thrust mechanism 10. The first connection piece 20 is provided with a first connection surface 21. The first connecting surface 21 is disposed obliquely with respect to the extending direction of the first connecting member 20.
The vector assembly 30 is provided with a second connection surface 311 parallel to the first connection surface 21. The second connection surface 311 is disposed obliquely with respect to the extending direction of the vector unit 30. The first connector 20 can be rotatably connected to the second connecting surface 311 through the first connecting surface 21, and a connection portion between the first connecting surface 21 and the second connecting surface 311 is in a circular shape or a circular shape coaxial with the first direction. In this embodiment, the first direction is parallel to the direction indicated by the arrow X in fig. 3.
The drive mechanism is configured to drive the first link 20 to rotate about the first direction relative to the vector assembly 30 to rotate the thrust mechanism 10 about the first direction relative to the vector assembly 30 via the first link 20.
The vector assembly 30 is disposed on the test bed load mechanism. The test stand can control the thrust mechanism 10 to control ignition and extinction of fuel, fuel consumption, supply of coolant, and the like. At the same time, the test stand can also control the drive mechanism to drive the first link 20 to rotate about the first direction relative to the vector assembly 30. Therefore, the physical model simulation can be carried out on the thrust chamber structure through the control of the test bed, and the motion curve and the motion range of the axis of the thrust mechanism 10 in space and the offset condition of the thrust line rotating at each angle are calculated through the simulation, so as to calibrate and regulate the thrust chamber structure test.
In summary, implementing the embodiments of the present application will have the following beneficial effects: the thrust chamber structure of the scheme is applied to the liquid rocket engine and the thrust simulation test device, not only the liquid rocket engine and the thrust simulation test device have excellent power efficiency, but also the swing angle range of the thrust mechanism 10 can be improved, so that the angle range of the thrust direction of the thrust mechanism 10 is larger, the actual control effect of the liquid rocket engine is improved, and the use scene of the liquid rocket engine is increased. Specifically, the thrust chamber structure includes a thrust mechanism 10, a first connector 20 disposed on the thrust mechanism 10, a vector assembly 30, and a drive mechanism. Wherein the first connection member 20 is provided with a first connection surface 21 arranged obliquely with respect to its extension direction. The vector assembly 30 is provided with a second connection surface 311 which is arranged obliquely with respect to its extension direction and parallel to the first connection surface 21. The connection part of the first connecting surface 21 and the second connecting surface 311 is in a ring shape or a round shape coaxial with the first direction, so that the thrust mechanism 10 can rotate around the first direction relative to the vector assembly 30 under the driving of the driving mechanism, and the extending direction of the first connecting member 20 rotates around the first direction when the first connecting surface 21 is obliquely arranged relative to the extending direction of the first connecting member 20, so that the thrust mechanism 10 rotates around the first direction relative to the vector assembly 30, and the swing angle of the thrust mechanism 10 is changed. Meanwhile, the inclination angles of the first connecting surface 21 and the second connecting surface 311 can be changed to improve the swing angle range of the thrust mechanism 10, so as to meet the different thrust direction requirements of the liquid rocket engine and the thrust simulation test device. Meanwhile, the vector assembly 30 and the connection position of the vector assembly 30 and the first connecting piece 20 are far away from the thrust mechanism 10, so that the influence of high-temperature fuel gas on the vector assembly 30 and the connection position of the vector assembly 30 and the first connecting piece 20 is reduced, and the precision of the swing angle of the thrust mechanism 10 is ensured. The thrust chamber structure can increase the attitude adjustment capability of the liquid rocket engine, reduce the intervention of an attitude control system, and be beneficial to reducing the redundant quality and increasing the maneuverability and flexibility of an aircraft/spacecraft. In addition, the swing angle of the thrust mechanism 10 is adjusted without changing the structure of the thrust mechanism 10, which is beneficial to keeping the original performance of the thrust mechanism 10 unchanged (for example, the thrust chamber structure needs extremely strong tightness for regenerative cooling due to higher chamber pressure and higher temperature), and the efficiency loss caused by changing the direction of the fuel gas after accelerating the fuel gas to supersonic speed is eliminated.
In an exemplary embodiment, referring to fig. 1, 3, and 6 to 11, the vector assembly 30 includes a plurality of vector members, one of the adjacent vector members is provided with a third connecting surface 312, and the other vector member is provided with a fourth connecting surface 321.
The third connecting surface 312 and the fourth connecting surface 321 are disposed obliquely with respect to the extending direction of the vector assembly 30. The third connecting surface 312 is parallel to the fourth connecting surface 321. The adjacent vector members are rotationally connected through a third connecting surface 312 and a fourth connecting surface 321. The connection between the third connection surface 312 and the fourth connection surface 321 is in a ring shape or a circular shape coaxial with the second direction, so that one of the adjacent vector members can rotate relative to the other vector member around the second direction. The drive mechanism is further arranged to drive one of the adjacent vector members to be rotatable about the second direction relative to the other. In this embodiment, the second direction is parallel to the direction indicated by the arrow Y in fig. 3. The second connecting surface 311 is located on an outermost one of the plurality of vector members. In the embodiment of the application, the driving mechanism comprises, but is not limited to, a gear set matching structure, a gear worm matching structure, a liquid (gas) pressure bar driving structure, a stepping motor direct driving structure and the like.
The extending direction of the vector members is the same as the extending direction of the vector assembly 30, and the third connecting surface 312 is obliquely arranged relative to the extending direction of the vector assembly 30, so that when the adjacent vector members relatively rotate around the second direction, one vector member also rotates around the second direction along the extending direction when rotating around the second direction, and therefore the swing angle of a structure connected with the vector members can be changed, the swing angle range of the thrust mechanism 10 is further increased, and the maneuverability of the thrust mechanism 10 is improved. Meanwhile, the inclination angles of the third connecting surface 312 and the fourth connecting surface 321 can be changed to improve the swing angle range of the vector piece, so that different thrust direction requirements of the liquid rocket engine and the thrust simulation test device can be met.
In the embodiment of the present application, the number of vector elements is two, namely, a first vector element 31 and a second vector element 32. The second connection surface 311 and the third connection surface 312 are located on the first vector 31. The fourth connecting surface 321 is located on the second vector 32. As shown in fig. 10, the first vector member 31 and the second vector member 32 do not rotate relative to each other. The first link 20 rotates about a first direction relative to the vector assembly 30 to cause the thrust mechanism 10 to create a tilt angle. As shown in fig. 11, the first coupling member 20 rotates about the first direction relative to the vector assembly 30, and the first vector member 31 rotates about the second direction relative to the second vector member 32, such that the thrust mechanism 10 creates a greater pivot angle, further enhancing the maneuverability of the thrust mechanism 10. Meanwhile, the swing angle range of the thrust mechanism 10 can be lifted by adjusting the rotation angle of the first vector piece 31 relative to the second vector piece 32 and the rotation angle of the first connecting piece 20 relative to the vector assembly 30, and continuous adjustment of the swing angle of the thrust mechanism 10 in the swing angle range can be realized. The connection structure of the first link 20 and the vector assembly 30 of the present application enables greater yaw adjustment of the thrust mechanism 10, and the adjustment direction is multidirectional (the deflectable/gimbal-based vector mechanism is a unidirectional adjustment) compared to a deflectable/gimbal-based vector mechanism.
In addition, in some exemplary embodiments, the number of vector members may be increased to increase the number of mating structures of the third connecting surface 312 and the fourth connecting surface 321, so as to further increase the range of the swing angle of the thrust mechanism 10, thereby realizing the full-angle swing angle adjustment of the thrust mechanism 10. The dimensions of the first link 20 and the vector assembly 30 and the dimensions of the connection surfaces may be determined according to the dimensions of the thrust mechanism 10 and the structure mounted on the thrust mechanism 10, and the inclination angle of the connection surfaces and the number of vector members may be determined according to the swing angle requirements of the thrust mechanism 10.
In an exemplary embodiment, please also combine fig. 4 to fig. 7, the cross section of the first connecting member 20 perpendicular to the extending direction of the first connecting member 20 and not passing through the first connecting surface 21 is elliptical or elliptical, so that the connection between the first connecting surface 21 and the second connecting surface 311 can be in a circular shape or a circular shape coaxial with the first direction, so that when the first connecting member 20 rotates relative to the vector assembly 30, the connection is always connected, and the connection stability between the first connecting surface 21 and the second connecting surface 311 is ensured.
The cross section of the vector component 30 perpendicular to the extending direction of the vector component 30 and not passing through the second connecting surface 311 is in an elliptical ring shape or an elliptical shape, so that the connection position of the third connecting surface 312 and the fourth connecting surface 321 can be in a ring shape or a circular shape coaxial with the second direction, and when the adjacent vector components relatively rotate, the connection positions are always connected, thereby ensuring the connection stability between the third connecting surface 312 and the fourth connecting surface 321.
In this embodiment, the cross section of the first connecting member 20 perpendicular to the extending direction of the first connecting member 20 and not passing through the first connecting surface 21 is elliptical. The cross section of the vector component 30 perpendicular to the extending direction of the vector component 30 and not passing through the second connecting surface 311 is in an elliptical ring shape, so that the first connecting piece 20 and the vector component 30 are hollow structures, structures connected with the thrust mechanism 10 can be arranged in the hollow structures, and the structures are prevented from being arranged outside the thrust mechanism 10, and damage is caused during use.
It will be appreciated that in other embodiments, as shown in fig. 12, the thrust chamber structure further includes a second connecting member 50, where the second connecting member 50 is connected between the thrust mechanism 10 and the first connecting member 20, so that the installation space of the thrust chamber structure can be increased by the arrangement of the second connecting member 50, and the structure connected to the thrust mechanism 10 can be conveniently arranged. The thrust chamber structure also includes a conduit that is coupled to the thrust mechanism 10 via the vector assembly 30, the first connector 20, and the second connector 50. The tubing includes a hose segment and a hard tube segment in communication with the hose segment, the hose segment being located within the vector assembly 30 and the first connector 20 to avoid interference with the adjustment of the pivot angle by the tubing. Due to the existence of the pipeline, the sealing problem is not required to be considered between the first connecting piece 20 and the vector assembly 30 and between the adjacent vector pieces in the vector assembly 30, and the matching stability between the first connecting piece 20 and the vector assembly 30 and between the adjacent vector pieces in the vector assembly 30 is ensured.
The hard pipe section is installed in the second connecting piece 50 and is connected with the thrust mechanism 10, so that the stability of connection of the pipeline and the thrust mechanism 10 is ensured. The piping includes, but is not limited to, a transmission piping for a control signal, a liquid supply piping for supplying a regenerative cooling liquid to the thrust mechanism 10, and the like. Furthermore, in some embodiments, on-line valve bodies, instrumentation, etc. may also be mounted within the hollow structure.
In an exemplary embodiment, as shown in fig. 12 to 14, the thrust chamber structure further includes a support assembly 40, where the support assembly 40 is connected between the thrust mechanism 10 and a fixed structure (may be a structure corresponding to a liquid rocket engine bearing mechanism, a test stand bearing mechanism, etc.), and the support assembly 40 can support the thrust mechanism 10 after fixing the position of the thrust mechanism 10, so as to improve stability of the thrust mechanism 10 and ensure stability of the adjusted thrust direction. In this embodiment, the number of the supporting components 40 is multiple and is set around the thrust mechanism 10, so as to further improve the stability of the thrust mechanism 10 and the stability of the adjusted thrust direction.
In this embodiment, the support assembly 40 includes a cylinder 41, a push rod 42 and a locking member (not shown), the cylinder 41 is connected with one of the thrust mechanism 10 and the fixing structure through a universal joint 43, the push rod 42 is connected with the other of the thrust mechanism 10 and the fixing structure through the universal joint 43, so that the movement of the thrust mechanism 10 can be prevented from being interfered by the arrangement of the universal joint 43, and the thrust mechanism 10 can be ensured to move to a preset position. The support assembly 40 is configured to change an angle between the thrust mechanism 10 and the fixed structure and an amount of extension and retraction of the push rod 42 according to movement of the thrust mechanism 10, fix the amount of extension and retraction after the position of the thrust mechanism 10 is fixed, and fix the angle by using a locking member. That is, the supporting component 40 can move along with the thrust mechanism 10, so as to adapt to the position change of the thrust mechanism 10 by changing the included angle and the expansion and contraction amount, and avoid interference to the movement of the thrust mechanism 10. At this time, the locking member is separated from the universal joint 43, and interference with the rotational degree of freedom of the universal joint 43 is avoided. After the position of the thrust mechanism 10 is fixed, the position of the push rod 42 relative to the cylinder 41 can be fixed by filling gas or liquid into the cylinder 41, so that the expansion and contraction amount is fixed, and the universal joint 43 is locked by the locking member, so that the included angle is fixed.
In an exemplary embodiment, the vector assembly 30 is rotatably coupled to a corresponding liquid rocket engine bearing mechanism to increase the rotational freedom of the vector assembly 30 as a whole, further increasing the range of the pivot angle of the thrust mechanism 10.
In other exemplary embodiments, the vector assembly 30 is rotatably coupled to the test stand load mechanism to increase the rotational freedom of the vector assembly 30 as a whole to further increase the range of pivot angles of the thrust mechanism 10.
In the description herein, it should be noted that, the terms "upper", "lower", "one side", "another side", "one end", "another end", "side", "opposite", "four corners", "periphery", "mouth" and "letter structure", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the structures referred to have a specific orientation, are configured and operated in a specific orientation, and therefore should not be construed as limiting the present application.
In the description of the embodiments of the present application, unless explicitly specified and limited otherwise, the terms "connected," "directly connected," "indirectly connected," "fixedly connected," "mounted," "assembled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; the terms "mounted," "connected," and "fixedly connected" may be directly connected or indirectly connected through intervening media, and may also be in communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
Although the embodiments disclosed in the present application are described above, the embodiments are only used for facilitating understanding of the present application, and are not intended to limit the present application. It should be noted that the above-described examples or implementations are merely exemplary and not limiting. Accordingly, the present disclosure is not limited to what has been particularly shown and described herein. Various modifications, substitutions, or omissions may be made in the form and details of the implementations without departing from the scope of the disclosure.
Claims (10)
1. A thrust chamber structure, comprising:
a thrust mechanism;
the first connecting piece is arranged on the thrust mechanism and is provided with a first connecting surface, and the first connecting surface is obliquely arranged relative to the extending direction of the first connecting piece;
the vector assembly is provided with a second connecting surface parallel to the first connecting surface, the second connecting surface is obliquely arranged relative to the extending direction of the vector assembly, the first connecting piece can be rotationally connected with the second connecting surface through the first connecting surface, and the joint of the first connecting surface and the second connecting surface is in a circular ring shape or a round shape coaxial with the first direction;
and the driving mechanism is arranged to drive the first connecting piece to rotate around the first direction relative to the vector assembly, so that the thrust mechanism rotates around the first direction relative to the vector assembly through the first connecting piece.
2. The thrust chamber arrangement of claim 1, wherein said vector assembly includes a plurality of vector members, one of adjacent said vector members being provided with a third connecting surface and the other being provided with a fourth connecting surface;
the third connecting surface and the fourth connecting surface are obliquely arranged relative to the extending direction of the vector assembly, the third connecting surface is parallel to the fourth connecting surface, adjacent vector pieces are rotationally connected through the third connecting surface and the fourth connecting surface, the connecting part of the third connecting surface and the fourth connecting surface is in a ring shape or a round shape coaxial with a second direction, so that one of the adjacent vector pieces can rotate relative to the other vector piece around the second direction, and the second connecting surface is positioned on the outermost vector piece of the plurality of vector pieces;
the drive mechanism is further configured to drive one of the adjacent vector members to be rotatable about the second direction relative to the other.
3. The thrust chamber structure of claim 2, wherein a cross section of the first connecting member perpendicular to an extending direction of the first connecting member and not passing through the first connecting surface is elliptical ring-shaped or elliptical, and a cross section of the vector assembly perpendicular to an extending direction of the vector assembly and not passing through the second connecting surface is elliptical ring-shaped or elliptical.
4. A thrust chamber arrangement according to any one of claims 1 to 3, further comprising a support assembly connected between the thrust mechanism and the fixed structure, the support assembly being capable of supporting the thrust mechanism after its position is fixed.
5. The thrust chamber structure of claim 4, wherein said number of support assemblies is a plurality and is disposed around said thrust mechanism.
6. The thrust chamber structure of claim 5, wherein the support assembly includes a cylinder, a push rod and a locking member, the cylinder is connected to one of the thrust mechanism and the fixing structure through a universal joint, the push rod is connected to the other of the thrust mechanism and the fixing structure through a universal joint, the support assembly is configured to be capable of changing an angle between the push rod and the fixing structure and an expansion amount of the push rod according to movement of the thrust mechanism, and fixing the expansion amount after fixing a position of the thrust mechanism, and fixing the angle by the locking member.
7. A liquid rocket engine, comprising:
a supply and control system; and
A thrust chamber arrangement as claimed in any one of claims 1 to 6, the vector assembly being provided on a corresponding liquid rocket engine load bearing mechanism.
8. A liquid rocket engine as recited in claim 7, wherein said vector assembly is rotatably coupled to said force bearing mechanism.
9. A thrust simulation test device is characterized by comprising:
a test bed; and
The thrust chamber arrangement of any one of claims 1 to 6, said vector assembly being disposed on said test bed load mechanism.
10. The thrust simulation test apparatus of claim 9, wherein the vector assembly is rotatably coupled to the test stand.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116988894A (en) * | 2023-08-25 | 2023-11-03 | 清航空天(北京)科技有限公司 | Thrust chamber structure, liquid rocket engine and thrust simulation test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116988894A (en) * | 2023-08-25 | 2023-11-03 | 清航空天(北京)科技有限公司 | Thrust chamber structure, liquid rocket engine and thrust simulation test device |
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