CN214741731U - Carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism - Google Patents
Carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism Download PDFInfo
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- CN214741731U CN214741731U CN202120496809.3U CN202120496809U CN214741731U CN 214741731 U CN214741731 U CN 214741731U CN 202120496809 U CN202120496809 U CN 202120496809U CN 214741731 U CN214741731 U CN 214741731U
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- 230000007246 mechanism Effects 0.000 title claims description 21
- 230000008878 coupling Effects 0.000 claims description 11
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- 238000005859 coupling reaction Methods 0.000 claims description 11
- 238000003754 machining Methods 0.000 claims description 5
- 230000006978 adaptation Effects 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009182 swimming Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 description 1
- 229910052982 molybdenum disulfide Inorganic materials 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006748 scratching Methods 0.000 description 1
- 230000002393 scratching effect Effects 0.000 description 1
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Abstract
The utility model provides a carrier rocket engine sways strutting arrangement, include: the swing shaft is fixed on two sides of the axis of the engine thrust chamber; a sliding bearing mounted on the rocking shaft for providing a bearing for circumferential movement about the rocking shaft; the top of the shaft sleeve is provided with a first semicircular bearing hole for mounting the sliding bearing; the engine comprises a gimbal seat, a frame structure shaft sleeve, a bearing support and a sliding bearing, wherein the bottom of the gimbal seat is provided with a second semicircular bearing hole and is arranged on shaft sleeves on two sides of an engine thrust chamber in a crossing mode and used for bearing support when the engine swings, and the second semicircular bearing hole arranged at the bottom of the gimbal seat is matched with the first semicircular bearing hole to install the sliding bearing. The swing supporting device can reduce the product cost and simplify the product structure.
Description
Technical Field
The utility model relates to a carrier rocket's rocket body structure field, concretely relates to carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism.
Background
The swinging support device is used as an important component of the rocket engine and is used for realizing the swinging of a thrust chamber of the rocket engine and the accurate control of a rocket trajectory. The traditional engine swing mechanism adopts a rolling bearing as a revolute pair between a gimbal seat and a thrust chamber, and has a complex structure.
In view of the above, it is desirable to design a rocket engine sway brace that has a simple structure and can increase the work efficiency.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art not enough, provide a carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism.
The utility model provides a carrier rocket engine sways strutting arrangement, include: the swing shaft is fixed on two sides of the axis of the engine thrust chamber; a sliding bearing mounted on the rocking shaft for providing a bearing for circumferential movement about the rocking shaft; the top of the shaft sleeve is provided with a first semicircular bearing hole for mounting the sliding bearing; the engine comprises a gimbal seat, a frame structure and a bearing support, wherein the frame structure is provided with a second semicircular bearing hole at the bottom and is arranged on shaft sleeves at two sides of an engine thrust chamber in a spanning mode and used for bearing support when the engine swings, and the second semicircular bearing hole arranged at the bottom of the gimbal seat is matched with the first semicircular bearing hole to install the sliding bearing.
According to an embodiment of the present invention, the rocking shaft is fixed to the cylindrical section of the thrust chamber by machining.
According to the utility model discloses an embodiment, the axle is provided with the shaft coupling to rocking for transmit the moment of torsion.
According to the utility model discloses an embodiment, first semicircle dead eye with the edge of second semicircle dead eye has the chamfer.
According to the utility model discloses an embodiment, the axle sleeve vertically divide into first connecting plate and second connecting plate, and first semicircular bearing hole sets up on the first connecting plate, just the length of second connecting plate is less than the length of first connecting plate.
According to the utility model discloses an embodiment, the seat of leveling is "door" font frame construction, and passes through the axle sleeve strides and establishes on the rocking shaft of engine thrust room both sides.
According to an embodiment of the utility model, the up end of the seat that levels is the slope to the adaptation is guaranteed by the inclination of stationary plane the engine is the vertical state.
According to the utility model discloses an embodiment, the lower terminal surface of level seat has two landing legs, and every landing leg sets up two first mounting holes, the axle sleeve first connecting plate up end correspondence sets up two second mounting hole adaptations the first mounting hole of every landing leg of level seat, level seat with the axle sleeve passes through the locating pin and inserts corresponding first mounting hole, second mounting hole and fix each other.
According to the utility model discloses an embodiment, the servo motor that provides the power of swaing is fixed the lateral surface of seat of leveling, the servo motor output with the axle passes through that sways the shaft coupling is fixed.
On the other hand, the utility model also provides a carrier rocket machine wabbler mechanism of swimming, sway strutting arrangement including thrust chamber and foretell carrier rocket engine.
The utility model discloses a carrier rocket engine sways strutting arrangement adopts the slide bearing of combination formula to replace traditional ball bearing through each spare part of structureization, reduces the product cost who sways strutting arrangement, has still simplified the product structure, has simplified the revolute pair structure between seat and the thrust room of having stabilized.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of the specification of the invention, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a front view of a launch vehicle engine sway brace according to one embodiment of the present invention;
FIG. 2 is a side view of a launch vehicle engine sway brace according to one embodiment of the present invention;
FIG. 3 is an elevation view of a launch vehicle engine sway brace according to another embodiment of the present invention;
FIG. 4 is a side view of a gimbal base of a rocket motor sway brace according to an embodiment of the present invention;
FIG. 5 is a schematic view of a bearing block of a launch vehicle engine sway brace according to an embodiment of the present invention;
figure 6 is a front view of a gimbal mount of a launch vehicle engine sway brace according to one embodiment of the invention.
Description of reference numerals:
100-rocking shaft, 200-shaft sleeve, 201-first semicircular bearing hole, 202-second semicircular bearing hole, 203-first connecting plate, 204-second connecting plate, 300-gimbal seat, 301-first mounting hole, 302-second mounting hole, 400-coupler and 500-servo mechanism.
Detailed Description
The features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purposes of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the structures or regions in the figures may be exaggerated relative to other structures or regions to help improve understanding of embodiments of the present invention.
The directional terms appearing in the following description are 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 stated, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as the case may be, by those of ordinary skill in the art.
Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.
FIG. 1 is a front view of a launch vehicle engine sway brace according to one embodiment of the present invention; FIG. 2 is a side view of a launch vehicle engine sway brace according to one embodiment of the present invention; FIG. 3 is an elevation view of a launch vehicle engine sway brace according to another embodiment of the present invention; FIG. 4 is a side view of a gimbal base of a rocket motor sway brace according to an embodiment of the present invention; FIG. 5 is a schematic view of a bearing block of a launch vehicle engine sway brace according to an embodiment of the present invention; figure 6 is a front view of a gimbal mount of a launch vehicle engine sway brace according to one embodiment of the invention.
As shown in fig. 1 and 2, the utility model provides a carrier rocket engine sways strutting arrangement includes: the swing shaft 100 is fixed on two sides of the axis of the engine thrust chamber T; a sliding bearing mounted on the rocking shaft 100 for providing a bearing for circumferential movement about the rocking shaft 100; the top of the shaft sleeve 200 is provided with a first semicircular bearing hole 201 for installing a sliding bearing; the gimbal 300 is a frame structure which has a second semicircular bearing hole 202 at the bottom and is mounted across the shaft sleeves 200 on both sides of the engine thrust chamber T, and is used for bearing support when the engine swings, wherein the second semicircular bearing hole 202 arranged at the bottom of the gimbal 300 is matched with the first semicircular bearing hole 201 to mount a sliding bearing.
Specifically, the rocking shafts 100 of the rocking support device of the carrier rocket engine are positioned at two sides of the thrust chamber T of the carrier rocket, and in order to increase the coaxiality of the rocking shafts 100 at two sides and improve the stability of the thrust chamber T during rocking, the rocking shafts 100 are positioned and fixed at two ends of the thrust chamber T at one time through a machining center. The sliding bearing is mounted on the rocking shaft 100, and the sliding bearing can provide a movement around the circumferential direction of the rocking shaft 100, thereby driving the thrust chamber T to rock. The bushing 200 serves as an intermediate member for connecting the sliding bearing and the gimbal 300, and a first semicircular bearing hole 201 is formed at the top for mounting the sliding bearing, and a mounting hole is formed in the bushing 200 for mounting the gimbal 300. The gimbal 300 is a frame structure and is spanned with shaft sleeves 200 installed on two sides of an engine thrust chamber T, the bottom of the gimbal 300 is provided with a second semicircular bearing hole 202, wherein the second semicircular bearing hole 202 arranged at the bottom of the gimbal 300 is matched with the first semicircular bearing hole 201 to install a sliding bearing, the gimbal 300 can be kept stationary when the engine swings, and the gimbal 300 is connected with a frame in a launch vehicle to maintain the balance of forces when the engine swings.
In the embodiment, the combined sliding bearing is used to replace the conventional ball bearing, which can reduce the product cost of the rocking support device, simplify the product structure, and simplify the structure of the revolute pair between the gimbal 300 and the thrust chamber T.
According to an embodiment of the present invention, the rocking shaft 100 is fixed to the cylindrical section of the thrust chamber T by machining.
Specifically, the thrust chamber T of the launch vehicle engine is roughly divided into a cylindrical section, a convergent section, and an divergent section, and the rocking shaft 100 is fixed to the cylindrical section of the thrust chamber T by machining, so that the top of the gimbal 300 is erected above the cylindrical section of the thrust chamber T.
As shown in fig. 3, according to an embodiment of the present invention, the rocking shaft 100 is provided with a coupling 400 for transmitting torque. For example, one end of the swing shaft 100 is connected to the servo 500 through the coupling 400.
According to an embodiment of the present invention, the servo mechanism 500 providing the rocking force is fixed on the outer side surface of the gimbal 300, and the output end of the servo mechanism 500 is fixed with the rocking shaft 100 through the coupling 400.
Specifically, the servo mechanism 500 driving the sliding bearing to rotate outputs power to the coupling 400, and the output power transmits torque through the coupling 400 because the coupling 400 is connected to the swing shaft 100, thereby driving the thrust chamber T to swing at a certain angle. The servo mechanism 500 is fixedly installed outside the gimbal 300, and an output end thereof transmits force to the rocking shaft 100 through the coupling 400. When the thrust chamber T needs to swing, an action signal is sent to the servo mechanism 500 through the rocket-mounted control system, and the servo mechanism 500 drives the thrust chamber T to complete the swinging action.
As shown in fig. 4, according to an embodiment of the present invention, the edges of the first semicircular bearing hole 201 and the second semicircular bearing hole 202 have a chamfer D.
Specifically, in order to prevent the edges of the first semicircular bearing hole 201 and the second semicircular bearing hole 202 from scratching the rotating shaft of the thrust chamber T, the edges of the first semicircular bearing hole 201 and the second semicircular bearing hole 202 are rounded, so that a chamfer D is formed at the edges of the first semicircular bearing hole 201 and the second semicircular bearing hole 202. After the machining is finished, self-lubricating coatings are sprayed on the inner surfaces of the first semicircular bearing hole 201 and the second semicircular bearing hole 202, for example, molybdenum disulfide is used as the self-lubricating coatings, so that the friction between the self-lubricating coatings and the swinging shaft 100 of the thrust chamber T is reduced, and the working stability and reliability of the swinging process of the thrust chamber T are improved.
As shown in fig. 5, according to an embodiment of the present invention, the shaft sleeve 200 is longitudinally divided into a first connection plate 203 and a second connection plate 204, the first semicircular bearing hole 201 is provided on the first connection plate 203, and the length of the second connection plate 204 is smaller than that of the first connection plate 203.
Specifically, the boss 200 is divided into a first connecting plate 203 and a second connecting plate 204 in the longitudinal direction thereof (as indicated by the arrow of S1 in fig. 5), and the first connecting plate 203 and the second connecting plate 204 are integrally formed. Mounting holes are formed in two sides of the upper end face of the first connecting plate 203 and used for being connected with the leveling seat 300. The first semicircular bearing hole 201 penetrates through the middle position of the upper end face of the first connecting plate 203, the length of the second connecting plate 204 is smaller than that of the first connecting plate 203, and the length of the second connecting plate 204 is larger than the diameter of the first semicircular bearing hole 201, so that the effect of increasing bearing force support can be achieved.
As shown in fig. 6, according to an embodiment of the present invention, the gimbal 300 has a frame structure like a "door" and straddles the swing shaft 100 on both sides of the engine thrust chamber T through the shaft sleeve 200.
Specifically, the gimbal 300 is arranged in a frame structure like a "door" and can be arranged on two sides of the thrust chamber T in a straddling manner, the upper end face of the gimbal 300 is provided with a mounting hole to realize butt joint with the frame, and the lower end face of the gimbal 300 is provided with a mounting hole to realize connection with the shaft sleeve 200.
According to an embodiment of the present invention, the upper end surface of the gimbal 300 is inclined to adapt to the inclination of the fixed surface to ensure that the engine is in a vertical state.
Specifically, since a plurality of engines are simultaneously installed in a frame of a launch vehicle, in order to maintain the balance of forces, the frame, i.e., a fixed surface of an engine sway brace, is arranged to be inclined downward toward the periphery along a central axis, and the installation of the gimbal 300 on the inclined frame requires that the upper end surface of the gimbal 300 be correspondingly arranged to be inclined at the same angle according to the inclination angle, thereby ensuring that the engines are in a vertical state in a non-operating state.
According to the utility model discloses an embodiment, the lower terminal surface of the seat 300 that levels has two landing legs, and every landing leg sets up two first mounting holes 301, and the first connecting plate 203 up end of axle sleeve 200 corresponds the first mounting hole 301 that sets up two second mounting holes 302 adaptation every landing leg of the seat 300 that levels, and the seat 300 that levels is fixed each other with axle sleeve 200 through locating pin insert corresponding first mounting hole 301, second mounting hole 302.
Specifically, locating pin one end is the installation hexagonal, and the other end is the external screw thread, and the mid portion is the cylinder section. The cylindrical section of the positioning pin is assembled with the first mounting hole 301 of the gimbal 300 and the second mounting hole 302 of the shaft sleeve 200, and in order to improve the assembly accuracy as much as possible, the cylindrical section of the positioning pin is designed to be in precise clearance fit with the first mounting hole 301 of the gimbal 300 and the second mounting hole 302 of the shaft sleeve 200. After the positioning pins are arranged in the first mounting hole 301 and the second mounting hole 302 of the gimbal 300 and the shaft sleeve 200, the self-locking nuts are arranged on the external thread sections of the positioning pins, so that the gimbal 300 and the shaft sleeve 200 can be reliably fixed.
On the other hand, the utility model also provides a carrier rocket machine wabbler mechanism, including thrust chamber T and foretell carrier rocket engine sway strutting arrangement.
In this embodiment, when the rocket launcher oscillating mechanism is assembled, first, two shaft sleeves 200 are installed on the oscillating shafts 100 at two ends of the thrust chamber T, then the gimbal 300 and the two shaft sleeves 200 are connected and fixed by using the positioning pins and the self-locking nuts, finally, the servo mechanism 500 is fixed with the gimbal 300, the output end of the servo mechanism 500 is fixed with the thrust chamber T shaft through the coupler 400, and the assembly of the oscillating mechanism is completed.
In the utility model, because the integral sliding bearing is used to replace the ball bearing or the combined sliding bearing of the traditional swing mechanism of the game machine, on one hand, the structure of the rotating pair between the traditional ball bearing-based gimbal 300 and the thrust chamber T is simplified, and the product cost is reduced; on the other hand, the precision of the bearing hole of the combined type swing mechanism of the swimming machine based on the sliding bearing is improved, and the working stability and reliability of the T swing process of the thrust chamber are enhanced.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A launch vehicle engine sway brace apparatus comprising:
the swing shaft is fixed on two sides of the axis of the engine thrust chamber;
a sliding bearing mounted on the rocking shaft for providing a bearing for circumferential movement about the rocking shaft;
the top of the shaft sleeve is provided with a first semicircular bearing hole for mounting the sliding bearing;
the engine comprises a gimbal seat, a frame structure and a bearing support, wherein the frame structure is provided with a second semicircular bearing hole at the bottom and is arranged on shaft sleeves at two sides of an engine thrust chamber in a spanning mode and used for bearing support when the engine swings, and the second semicircular bearing hole arranged at the bottom of the gimbal seat is matched with the first semicircular bearing hole to install the sliding bearing.
2. The launch vehicle engine sway brace of claim 1 wherein the sway shaft is secured to the cylindrical section of the thrust chamber by machining.
3. A launch vehicle engine sway brace apparatus of claim 2 wherein the sway shaft is provided with a coupling for transferring torque.
4. The launch vehicle engine sway brace of claim 1 wherein edges of the first and second semi-circular bearing apertures are chamfered.
5. The launch vehicle engine sway brace of claim 4 wherein the bushing is longitudinally divided into a first web and a second web, a first semi-circular bearing aperture being provided in the first web, and the second web having a length less than the length of the first web.
6. The launch vehicle engine sway brace of claim 5 wherein the gimbal is a "door" frame structure and straddles the sway axis on either side of the engine thrust chamber via the bushings.
7. A launch vehicle engine sway brace apparatus of claim 6 wherein an upper end face of the gimbal is inclined to accommodate the slope of the surface to be secured to ensure that the engine is in a vertical position.
8. The launch vehicle engine sway brace of claim 7 wherein the lower end surface of the gimbal has two legs, each leg having two first mounting holes, the upper end surface of the first connecting plate of the collar having two corresponding second mounting holes adapted to the first mounting holes of each leg of the gimbal, the gimbal and the collar being secured to each other by a locating pin inserted into the corresponding first and second mounting holes.
9. The launch vehicle engine sway brace of claim 3 wherein a servo motor providing a sway force is affixed to an outboard face of the gimbal, the servo motor output being affixed to the sway shaft by the coupling.
10. A launch vehicle yaw mechanism comprising a thrust chamber and a launch vehicle engine yaw support apparatus according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120496809.3U CN214741731U (en) | 2021-03-05 | 2021-03-05 | Carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120496809.3U CN214741731U (en) | 2021-03-05 | 2021-03-05 | Carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214741731U true CN214741731U (en) | 2021-11-16 |
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ID=78592084
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120496809.3U Active CN214741731U (en) | 2021-03-05 | 2021-03-05 | Carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214741731U (en) |
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2021
- 2021-03-05 CN CN202120496809.3U patent/CN214741731U/en active Active
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Effective date of registration: 20240401 Address after: Building H1, AVIC International Plaza, yard 13, Ronghua South Road, Daxing Economic and Technological Development Zone, Beijing 100176 Patentee after: Blue Arrow Space Technology Co.,Ltd. Country or region after: China Address before: 710077 East Building, four floor, aerospace science and technology, civil and integration innovation center, 32 United South Road, Xi'an, Shaanxi Patentee before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Country or region before: China Patentee before: Zhejiang blue arrow Space Technology Co.,Ltd. Patentee before: Blue Arrow Space Technology Co.,Ltd. |