CN111677813A - Vibration damper on spacecraft - Google Patents
Vibration damper on spacecraft Download PDFInfo
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- CN111677813A CN111677813A CN202010562377.1A CN202010562377A CN111677813A CN 111677813 A CN111677813 A CN 111677813A CN 202010562377 A CN202010562377 A CN 202010562377A CN 111677813 A CN111677813 A CN 111677813A
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- 238000013016 damping Methods 0.000 claims abstract description 73
- 230000000694 effects Effects 0.000 abstract description 10
- 230000035939 shock Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 5
- 230000009467 reduction Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000001965 increasing effect Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
- F16F15/067—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs using only wound springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
- F16M11/02—Heads
- F16M11/04—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Remote Sensing (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The application relates to a vibration damper on a spacecraft, and belongs to the technical field of spaceflight. The device includes: the damping device includes a first case, a second case, and an anti-damping member. The first shell is provided with a first inner cavity capable of containing a component to be anti-vibration, first slots are formed in two opposite sides of the first shell, which are far away from the first inner cavity, and the opening direction of the first slots is far away from the first inner cavity. The second casing is equipped with the second inner chamber that is used for holding first casing, and the second casing is equipped with the second fluting towards being equipped with on the relative both sides inner wall of first fluting, and the fluting opening direction of second is towards first fluting. The anti-damping component is used for slowing down the impact of external acting force on the vibration damping device, two ends of the anti-damping component are respectively arranged in the first open slot and the second open slot, and two ends of the anti-damping component can slide in the first open slot and the second open slot, so that the distance between the first shell and the second shell is adjusted. The vibration damping device has the advantages that the vibration damping effect can be effectively achieved through the anti-damping part, and the problem that the part to be subjected to vibration damping is easy to loosen and even fall off can be effectively solved.
Description
Technical Field
The application belongs to the technical field of spaceflight, and particularly relates to a vibration damper on a spacecraft.
Background
The components in the existing spacecraft are generally connected with each other in a bolt and washer mode or fixed on a bearing device in the spacecraft, and although the fixing mode has a simple structure and low cost, the fixing mode has the following defects easily in some special scenes such as the situation of receiving high-frequency vibration or shock (such as the situation that the spacecraft carries other launching devices to the space): first, the connection between these components and other components or fixed platforms may loosen or even fall off; secondly, the parts may shift due to loose connections; thirdly, the connection of the internal parts in the parts is loosened or dropped and even damaged due to vibration or large vibration.
If the above problems occur when the components of the radio frequency device, the camera, the gyroscope and the like in the spacecraft encounter vibration or shock with high frequency, the whole spacecraft can not effectively carry out space tasks due to the functional characteristics and the like of the components.
Disclosure of Invention
In view of this, embodiments of the present disclosure provide a vibration damping device for a spacecraft, so as to solve the problems of displacement, loose connection, and even connection and detachment of components caused by the conventional fixing method when subjected to vibration or shock.
The embodiment of the application is realized as follows:
the embodiment of the application provides a damping device on spacecraft, includes: a first housing, a second housing, an anti-damping member; the first shell is provided with a first inner cavity capable of accommodating a component to be subjected to vibration resistance, two opposite sides of the first shell, which are far away from the first inner cavity, are provided with first slots, and the opening direction of the first slots is far away from the first inner cavity; the second shell is provided with a second inner cavity for accommodating the first shell, second open grooves are formed in the inner walls of two opposite sides of the second shell facing the first open grooves, and the opening direction of the second open grooves faces the first open grooves; the anti-damping component is used for slowing down the impact of external acting force on the vibration damping device on the spacecraft, two ends of the anti-damping component are respectively arranged in the first open slot and the second open slot, and two ends of the anti-damping component can slide in the first open slot and the second open slot, so that the distance between the first shell and the second shell is adjusted.
In the embodiment of the application, the first shell and the second shell are connected through the anti-damping component, and the anti-damping component has a vibration damping effect, so that when the vibration damping device on the spacecraft is vibrated or vibrated, the anti-damping component can slow down the impact brought to the first shell by the vibration or the vibration, and further slow down the impact brought to the component to be anti-vibrated in the first shell by the vibration or the vibration. And the two ends of the anti-vibration component can slide in the first slot and the second slot, so that the distance between the first shell and the second shell can be adjusted, and the anti-vibration strength of the anti-vibration component can be adjusted at the same time, so that the anti-vibration strength of the anti-vibration component can be adjusted according to the application scene of the anti-vibration component to be treated, and further the impact of the anti-vibration component to be treated can be effectively relieved when the vibration reduction device on the spacecraft encounters vibration or shock. Therefore, through the vibration damper on the spacecraft provided by the application, the displacement of the part to be anti-vibration fixed in the first shell can be avoided, and the problem that the part to be anti-vibration is connected with other parts loosely or even falls off can be effectively reduced.
In one possible embodiment, the anti-damping member includes: the first connecting shaft, the second connecting shaft, the spring and the lever shaft; the first connecting shaft and the second connecting shaft are connected through the lever shaft and are in an X shape; one end of the first connecting shaft is connected with one end, close to the second spring, of the first spring, the other end of the first connecting shaft is connected with one end, close to the fourth spring, of the third spring, one end of the second connecting shaft is connected with one end, close to the first spring, of the second spring, and the other end of the second connecting shaft is connected with one end, close to the third spring, of the fourth spring.
In the embodiment of the application, the anti-damping component similar to a scissor lever is adopted to connect the first shell and the second shell so as to increase the vibration reduction effect, furthermore, after one side of the scissor lever is stressed, the first connecting shaft and/or the second connecting shaft slide along the stress direction, the spring in the stress direction is stressed and compressed, otherwise, the spring on the other side is stretched by the tension force, and the two sides are restricted mutually, so that the effect of enhancing the vibration reduction is achieved.
In a possible implementation manner, two opposite sides of the second shell, which are away from the first shell, are respectively provided with a third open slot and a fourth open slot, wherein the side where the third open slot is located is different from the side where the second open slot is located; two ends of the lever shaft respectively penetrate through the third open groove and the fourth open groove to extend out of the second shell, and the lever shaft can reciprocate in the third open groove and the fourth open groove to adjust an included angle between the two connecting shafts, so that the distance between the first shell and the second shell is adjusted. In the embodiment of the application, the third open groove and the fourth open groove are respectively formed in the two opposite sides of the second shell, which are away from the first shell, so that the two ends of the lever shaft respectively penetrate through the third open groove and the fourth open groove to extend out of the second shell, the lever shaft can reciprocate in the third open groove and the fourth open groove to adjust the included angle between the two connecting shafts, the anti-vibration level of the anti-vibration component is adjusted, the anti-vibration component can be suitable for different anti-vibration requirements, and the impact on the anti-vibration component to be treated can be effectively reduced.
In a possible embodiment, the anti-damping part further includes a plurality of fixing devices, and both ends of the lever shaft are respectively fixed to the second housing by at least one of the fixing devices. In the embodiment of the application, be fixed in the second casing through fixing device with the lever axle on, avoid the lever axle to drop at the in-process that removes, simultaneously, restrict the contained angle between two connecting axles through fixed lever axle for vibration damper on this spacecraft when receiving vibration or vibrations, the anti vibration rank of anti damping part can not make a round trip to fluctuate, thereby can effectively slow down the impact of treating the anti vibration part.
In a possible embodiment, each of said fixing means comprises: the limiting part comprises a shaft sleeve and a limiting part arranged on the shaft sleeve, the shaft sleeve is sleeved on the lever shaft close to the outer side wall of the second shell, and the limiting part is abutted against the outer side wall of the second shell and used for limiting the rotation and/or movement of the lever shaft; the locking nut is sleeved on the lever shaft and abutted against the shaft sleeve, and is used for abutting the limiting part against the outer side wall of the second shell. In the embodiment of the application, through adopting the fixing device comprising the lock nut and the limiting part, the lever shaft which can be very convenient and fast is fixed on the second shell, and is very easy to detach.
In a possible implementation manner, a plurality of first positioning holes are further formed in the outer side wall, close to the third slot, of the second housing, and the plurality of first positioning holes are arranged at intervals along the length direction of the third slot; a plurality of second positioning holes are further formed in the outer side wall, close to the fourth slot, of the second shell, and the second positioning holes are arranged at intervals along the length direction of the fourth slot; when the fixing device is used for fixing the lever shaft, the limiting part of the fixing device, which is positioned at one end of the lever shaft, is positioned in one of the first positioning holes, and the limiting part of the fixing device, which is positioned at the other end of the lever shaft, is positioned in one of the second positioning holes. In the embodiment of the application, through set up a plurality of first locating holes along its grooved length direction interval on the grooved lateral wall of third, and set up a plurality of second locating holes along its grooved length direction interval on the grooved lateral wall of fourth, when fixed lever shaft, select a first locating hole from a plurality of first locating holes and fix the spacing portion that is located the fixing device of lever shaft one end, select a second locating hole from a plurality of second locating holes and fix the spacing portion that is located the fixing device of the lever shaft other end, with the reinforcing fixed effect, avoid in the in-process that uses, the lever shaft is not hard up, also be convenient for adjust the anti vibration level of anti-damping part simultaneously.
In one possible embodiment, the first housing includes: the first side plate and the second side plate are arranged oppositely, and the first adjusting shaft and the second adjusting shaft are arranged oppositely; a plurality of first through holes and a plurality of second through holes are respectively formed in the first side plate and the second side plate; two ends of the first adjusting shaft respectively penetrate through the first through hole and the second through hole to be connected with the first side plate and the second side plate; two ends of the second adjusting shaft respectively penetrate through the first through hole and the second through hole to be connected with the first side plate and the second side plate; the first side plate and the second side plate can move on the first adjusting shaft and the second adjusting shaft and are used for adjusting the distance between the first side plate and the second side plate; the cavity enclosed by the first adjusting shaft, the first side plate, the second adjusting shaft and the second side plate is the first inner cavity. In the embodiment of the application, the first shell formed by combining the first side plate and the second side plate which are arranged oppositely and the first adjusting shaft and the second adjusting shaft which are arranged oppositely is adopted to install the component to be subjected to vibration resistance, so that the distance between the first side plate and the second side plate can be adjusted according to the size of the component to be subjected to vibration resistance, the application range of the first shell is wider, and the components to be subjected to vibration resistance with different sizes can be installed.
In a possible implementation manner, the first shell further comprises a plurality of second locking nuts, the first adjusting shaft and the second adjusting shaft are both provided with threads, and a plurality of scales are marked at intervals along the axial direction of the first adjusting shaft and the second adjusting shaft; every two second locking nuts are respectively sleeved on one side, close to the second shell, of the first adjusting shaft and are respectively abutted against one sides, close to the second shell, of the first side plate and the second side plate, and are used for adjusting the distance between the first side plate and the second side plate; every two second lock nuts are respectively sleeved on the second adjusting shaft and close to one side of the second shell, and are respectively abutted against the first side plate and one side of the second side plate close to the second shell, so that the distance between the first side plate and the second side plate can be adjusted. In the embodiment of the application, through set up the screw thread on first regulating spindle and second regulating spindle to and set up a plurality of scales along its axial direction interval, so that when adjusting the distance between first curb plate and the second curb plate, according to the scale alright adjust the distance between the curb plate both ends to equal fast, adjust the distance of first curb plate upper end distance second curb plate upper end and the distance of first curb plate lower extreme distance second curb plate lower extreme to equal if fast.
In a possible embodiment, the first housing further includes a plurality of first cover plates, and each two first cover plates are respectively covered on two ends of the first slot, so as to limit the two springs in the first slot from moving in the first slot. In the embodiment of the application, the first cover plates are covered at the two ends of the first open slot to limit the two springs in the first open slot to move in the first open slot, so that the vibration reduction effect is enhanced.
In a possible embodiment, the second housing further includes a plurality of second cover plates, and each two of the second cover plates are respectively covered on two ends of the second slot, so as to limit the two springs in the second slot from moving in the second slot. In the embodiment of the application, the second cover plates are covered at the two ends of the second open slot to limit the two springs in the second open slot to move in the second open slot, so that the vibration reduction effect is enhanced.
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 the practice of the embodiments of the application. The objectives and other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts. The foregoing and other objects, features and advantages of the application will be apparent from the accompanying drawings. Like reference numerals refer to like parts throughout the drawings. The drawings are not intended to be to scale as practical, emphasis instead being placed upon illustrating the subject matter of the present application.
Fig. 1 shows a schematic structural diagram of a vibration damping device on a spacecraft according to an embodiment of the present application.
Fig. 2 shows a schematic view of a damping device on the spacecraft shown in fig. 1 from a first viewing angle.
Fig. 3 shows a schematic view of the vibration damping device on the spacecraft shown in fig. 1 from a second viewing angle.
Fig. 4 shows a schematic connection relationship between the first connection shaft and the lever shaft and between the second connection shaft and the lever shaft provided by the embodiment of the present application.
Fig. 5 shows a schematic view of another connection relationship between the first connection shaft and the lever shaft and the second connection shaft provided by the embodiment of the present application.
Fig. 6 shows a schematic structural diagram of a fixing device provided in an embodiment of the present application.
Figure 7 shows a schematic view of the fastening device shown in figure 6 from a first perspective.
Icon: 100-vibration damping devices on spacecraft; 10-a first housing; 11-first grooving; 12-a first lumen; 13-a first side panel; 14-a second side panel; 15-a first adjustment shaft; 16-a second adjustment shaft; 17-a first cover plate; 18-mounting holes; 20-a second housing; 21-a second lumen; 22-second grooving; 23-third grooving; 24-fourth grooving; 25-a second cover plate; 26-a first locating hole; 30-an anti-damping member; 31-a first connecting shaft, 32-a second connecting shaft; 33-a lever shaft; 34-a first spring; 35-a second spring; 36-a third spring; 37-a fourth spring; 38-fixing means.
Detailed Description
Technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present application, it should be noted that the terms "upper", "lower", "left", "right", "front", "back", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that are conventionally arranged when products of the application are used, and are used only for convenience in describing the application and simplifying the description, but do not indicate or imply that the devices or elements to be referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the application. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is further noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; may be a mechanical connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In view of the fact that most of components in the traditional spacecraft are directly fixed on a bearing device in the spacecraft in a bolt and washer mode, the connection of the components fixed on the device is easy to loosen and even fall off when the device is vibrated or shocked by the fixing mode, the embodiment of the application provides the vibration damping device on the spacecraft, and the problem is solved.
As shown in fig. 1, the vibration damping device 100 on the spacecraft includes: a first case 10, a second case 20, and an anti-damping member 30. The first housing 10 is provided with a first inner cavity 12 capable of accommodating a component to be damped, two opposite sides of the first housing 10 away from the first inner cavity 12 are provided with first slots 11 for connecting the anti-damping component 30, and an opening direction of the first slots 11 is away from the first inner cavity 12 and faces the second housing 20. The second casing 20 is provided with a second inner cavity 21 for accommodating the first casing 10, the inner walls of the two opposite sides of the second casing 20 facing the first slot 11 are provided with second slots 22 for connecting the anti-damping members 30, and the opening direction of the second slots 22 faces the first slot 11. The anti-damping member 30 is used for buffering the impact of an external force on the vibration damping device on the spacecraft, two ends of the anti-damping member 30 are respectively arranged in the first slot 11 and the second slot 22, the first shell 10 and the second shell 20 are connected through the anti-damping member 30, and the anti-damping member 30 has a vibration damping effect, so that when the vibration damping device 100 on the spacecraft is subjected to vibration or shock, the anti-damping member 30 can buffer the impact of the vibration or shock on the first shell 10, and thus the impact of the vibration or shock on the component to be anti-damped in the first shell 10 is buffered. And the two ends of the anti-vibration component 30 can slide in the first slot 11 and the second slot 22, so that not only can the distance between the first shell 10 and the second shell 20 be adjusted, but also the anti-vibration strength of the anti-vibration component can be adjusted, so that the anti-vibration strength of the anti-vibration component 30 can be adjusted according to the application scene of the component to be anti-vibration, and when the vibration damper 100 on the spacecraft is subjected to vibration or shock, under the action of impact force, the two ends of the anti-vibration component 30 can slide in the first slot 11 and the second slot 22, so as to adjust the distance between the first shell 10 and the second shell 20, thereby enhancing the vibration damping effect, and further avoiding the problems that the component to be anti-vibration fixed in the first shell 10 is displaced, easily loosened, and even falls off.
The first housing 10 may be an integrally formed housing, and a plurality of mounting holes 18 are formed on inner walls of opposite sides thereof for fixing a component requiring vibration resistance (i.e., a component to be vibration-resistant). In one embodiment, as shown in fig. 2, the first housing 10 includes: the first side plate 13 and the second side plate 14 are arranged oppositely, and the first adjusting shaft 15 and the second adjusting shaft 16 are arranged oppositely. The first side plate 13 and the second side plate 14 are respectively provided with a plurality of first through holes and a plurality of second through holes (not shown), for example, two ends of the first side plate 13 are respectively provided with a plurality of first through holes arranged at intervals (for example, arranged at intervals along the short side direction of the first side plate 13), two ends of the second side plate 14 are respectively provided with a plurality of second through holes arranged at intervals (for example, arranged at intervals along the short side direction of the second side plate 14), two ends of the first adjusting shaft 15 respectively penetrate through the first through holes and the second through holes to be connected with the first side plate 13 and the second side plate 14, and two ends of the second adjusting shaft 16 respectively penetrate through the first through holes and the second through holes to be connected with the first side plate 13 and the second side plate 14. A cavity enclosed by the first adjusting shaft 15, the first side plate 13, the second adjusting shaft 16 and the second side plate 14 is a first inner cavity 12. The first side plate 13 and the second side plate 14 can move on the first adjusting shaft 15 and the second adjusting shaft 16, so that the distance between the first side plate 13 and the second side plate 14 can be adjusted, and the vibration-proof device can be further suitable for parts to be subjected to vibration resistance with different sizes.
In order to facilitate the adjustment of the distance between the first side plate 13 and the second side plate 14, optionally, the first adjusting shaft 15 and the second adjusting shaft 16 are both provided with threads, and are marked with a plurality of scales at intervals along the axial direction thereof, and correspondingly, the first casing 10 further includes a plurality of lock nuts for fixing the first adjusting shaft 15 and the second adjusting shaft 16 on the first side plate 13 and the second side plate 14. When the anti-vibration component is fixed, every two locking nuts are respectively sleeved on one side, close to the second shell 20, of the first adjusting shaft 15 and respectively abut against one side, close to the second shell 20, of the first side plate 13 and one side, close to the second shell 20, of the second side plate 14 (namely, the two locking nuts are respectively sleeved on the first adjusting shaft 15, outside the first side plate 13 and the second side plate 14, as shown in fig. 1) and are used for adjusting the distance between the first side plate 13 and the second side plate 14, and when the distance between the two side plates is adjusted to be suitable for the distance needed by the anti-vibration component to be treated, the anti-vibration component is locked through the locking nuts, so that the distance between. Every two second locking nuts are respectively sleeved on one side, close to the second shell 20, of the second adjusting shaft 16 and respectively abut against one side, close to the second shell 20, of the first side plate 13 and the second side plate 14 (namely, the two second locking nuts are respectively sleeved on the second adjusting shaft 16, outside the first side plate 13 and the second side plate 14, as shown in fig. 1), and are used for adjusting the distance between the first side plate 13 and the second side plate 14, and when the distance between the two side plates is adjusted to the distance required by the anti-vibration component to be treated, the two second locking nuts are locked through the locking nuts, so that the distance between the two side plates is prevented from changing again. It should be noted that the first side plate 13 and the second side plate 14 and the first adjusting shaft 15 and the second adjusting shaft 16 may be fixed by other common fixing methods, such as clamping, instead of being fixed by lock nuts.
The number of the first adjusting shafts 15 and the second adjusting shafts 16 is plural (2 or more), and it should be noted that the case shown in fig. 1 including 3 first adjusting shafts 15 and 3 second adjusting shafts 16 cannot be understood as a limitation to the present application.
In the present embodiment, the mounting holes 18 for fixing the component to be vibration-proof may be provided on the first side plate 13 and the second side plate 14, and of course, the mounting holes 18 may also be provided on the first adjusting shaft 15 and the second adjusting shaft 16.
In one embodiment, the first slot 11 is opened on a side of the first side plate 13 and the second side plate 14 facing the second housing 20. Alternatively, the grooving direction of the first groove 11 extends in the short side direction of the first side plate 13 and the second side plate 14.
In which the number of the first slots 11 and the second slots 22 is plural (2 and more), so that the case of including 4 first slots 11 and 4 second slots 22 shown in fig. 1 cannot be understood as a limitation of the present application. In addition, the number of the first slots 11 formed on the two opposite sides of the first casing 10 away from the first inner cavity 12 may be unequal, for example, 1 first slot 11 is formed on one side, and 2 first slots 11 are formed on the other side. Similarly, the number of the second slots 22 opened on the inner walls of the two opposite sides of the second shell 20 facing the first slot 11 may not be equal, for example, 1 second slot 22 is opened on one side, and 2 second slots 22 are opened on the other side. The number of the first slots 11 is the same as that of the second slots 22, and the positions of the first slots and the second slots correspond to each other. Alternatively, the cross-sectional shapes of the front surfaces of the first slot 11 and the second slot 22 are both U-shaped, and the width of the opening is slightly smaller than the diameter of the ellipse of the main body, so that the two ends of the anti-damping part 30 will not slide out of the opening when sliding in the first slot 11 and the second slot 22.
The anti-damping member 30 is used to reduce the impact of external force on the vibration damping device of the spacecraft, and also can enhance the vibration damping effect by adjusting the distance between the first shell 10 and the second shell 20. In one embodiment, the anti-damping member 30 may be an elastic member (e.g., a spring) with a telescopic function, and both ends of the elastic member are spherical and are respectively disposed in the first slot 11 of the first casing 10 and the second slot 22 of the second casing 20. Optionally, the width of the opening of the first slot 11 and the second slot 22 is slightly smaller than the diameter of the sphere, so that the two ends of the elastic member do not slide out of the opening when sliding in the first slot 11 and the second slot 22.
In still another embodiment, the anti-damping part 30 includes: a first connecting shaft 31, a second connecting shaft 32, a spring and a lever shaft 33. Two springs, namely a first spring 34 and a second spring 35, are oppositely arranged in the first slot 11 along the slot direction, and two springs, namely a third spring 36 and a fourth spring 37, are oppositely arranged in the second slot 22 along the slot direction. The first connecting shaft 31 and the second connecting shaft 32 are connected by a lever shaft 33, and are in an X shape, and the connection is schematically shown in fig. 3. One end of the first connecting shaft 31 is connected to one end of the first spring 34 (e.g., located at the upper half of the first housing 10 in fig. 3) close to the second spring 35, the other end is connected to one end of the third spring 36 (e.g., located at the lower half of the second housing 20 in fig. 3) close to the fourth spring 37, one end of the second connecting shaft 32 is connected to one end of the second spring 35 (e.g., located at the lower half of the first housing 10 in fig. 3) close to the first spring 34, and the other end is connected to one end of the fourth spring 37 (e.g., located at the upper half of the second housing 20 in fig. 3) close to the third spring 36. It should be noted that the positional relationship among the first spring 34, the second spring 35, the third spring 36, and the fourth spring 37 is described above for convenience of description and simplification of description, and is described in the positional relationship shown in fig. 3, and therefore, the positional relationship is not to be construed as limiting the present application.
Wherein, in order to prevent the two springs in the first slot 11 from sliding out from the two ends of the first slot 11 during the moving process. The first housing 10 further includes a plurality of first cover plates 17, and every two first cover plates 17 are respectively covered on two ends of the first slot 11, for limiting the two springs in the first slot 11 to move in the first slot 11. Wherein, the one end of the spring of being connected with first apron 17 is the cylinder metal of taking the screw thread, treats the spring mounting back that finishes, through making the spring screw rotatory, makes it fix on first apron 17 to it is spacing to realize. The number of the first cover plates 17 is twice that of the first slots 11. Likewise, to prevent the two springs in the second slot 22 from sliding out of the two ends of the second slot 22 during movement. The second casing 20 further includes a plurality of second cover plates 25, and each two second cover plates 25 are respectively covered on two ends of the second slot 22, for limiting the two springs in the second slot 22 to move in the second slot 22. Wherein, the one end of the spring of being connected with second apron 25 is the cylinder metal of taking the screw thread, treats the spring mounting back that finishes, through making the spring screw rotatory, makes it fix on second apron 25 to it is spacing to realize. The number of the second cover plates 25 is twice that of the second slots 22.
As shown in fig. 4, the middle main body portions of the first connecting shaft 31 and the second connecting shaft 32 are hollow and have a long shape, so that the lever shaft 33 can pass through the hollow portions of the first connecting shaft 31 and the second connecting shaft 32, the hollow portions provide the lever shaft 33 on the sliding spacecraft when the vibration damping device 100 on the spacecraft damps vibration, and further adjust the included angle between the two connecting shafts, so that not only can the distance between the first shell 10 and the second shell 20 be adjusted, but also the anti-vibration strength of the anti-vibration component 30 can be adjusted, and therefore the anti-vibration strength of the anti-vibration component 30 can be adjusted according to the application scene of the component to be anti-vibration.
In a first alternative embodiment, the lever shaft 33 passes through the hollow parts of the first connecting shaft 31 and the second connecting shaft 32, and both ends of the lever shaft respectively pass through the third slot 23 and the fourth slot 24 respectively formed on two opposite sides of the second housing 20 away from the first housing 10, and extend out of the second housing 20 (as shown in fig. 2). Wherein, the opposite two sides of the second casing 20 departing from the first casing 10 are respectively provided with a third open slot 23 and a fourth open slot 24, and the side of the third open slot 23 is different from the side of the second open slot 22. In addition, in another embodiment, one of the third slot 23 and the fourth slot 24 opened at two opposite sides of the second casing 20 may not be a slot penetrating through the side wall of the second casing 20, for example, the third slot 23 is not a slot penetrating through the side wall of the second casing 20, and the fourth slot 24 is a slot penetrating through the side wall of the second casing 20, in which case, one end of the lever shaft 33 is placed in the third slot 23 of the second casing 20, and the other end thereof passes through the fourth slot 24 and protrudes out of the second casing 20.
Alternatively, when the number of the anti-damping members 30 located on the same side is plural, the plural anti-damping members 30 located on the same side may share the same lever shaft 33. In another embodiment, when there are a plurality of anti-damping members 30 located on the same side, instead of the plurality of anti-damping members 30 located on the same side sharing the same lever shaft 33, each anti-damping member 30 corresponds to one lever shaft 33, and different anti-damping members 30 correspond to different lever shafts 33, in this embodiment, two ends of the lever shaft 33 do not pass through the third and fourth slots 23 and 24 opened on opposite sides of the second housing 20, or one end of the lever shaft 33 is not placed in the third slot 23, and the other end does not pass through the fourth slot 24 and extends out of the second housing 20; but only pass through the hollow parts of the first connecting shaft 31 and the second connecting shaft 32, and the two ends of the lever shaft 33 are provided with the locking members to prevent the lever shaft 33 from falling off from the hollow parts. For example, the blocking member may be a limiting pin, and at this time, the lever shaft 33 is provided with a corresponding limiting through hole through which the limiting pin passes; alternatively, the blocking member is a cap, the cap covers two ends of the lever shaft 33, and the diameter of the cap is larger than the opening width of the hollow portion, and the schematic diagram is shown in fig. 5.
It should be noted that the surface on which the anti-damping member 30 is mounted is not exclusive, and may be arranged according to the circumstances, for example, the second slot 22 may be opened on the upper and lower sides of the second casing 20, and the third slot 23 and the fourth slot 24 may be opened on the left and right sides, respectively, and accordingly, the first slot 11 may be positioned on the upper and lower sides of the first casing 10. Therefore, the case where the second slot 22 is opened on both the left and right sides of the second housing 20, and the third slot 23 and the fourth slot 24 are opened on both the upper and lower sides, respectively, in the above example, cannot be understood as a limitation to the present application.
In the first alternative embodiment, in order to better adjust the included angle between the two connecting shafts, optionally, as shown in fig. 6, the anti-damping member 30 further includes a plurality of (2 and more) fixing devices 38, and both ends of the lever shaft 33 are respectively fixed to the second housing 20 by at least one fixing device 38. In one embodiment, the fixing device 38 may comprise: lock nut and locating part. The limiting part comprises a shaft sleeve and a limiting part arranged on the shaft sleeve, when the limiting part is fixed, the shaft sleeve is sleeved on the lever shaft 33 close to the outer side wall of the second shell 20, and the limiting part is abutted on the outer side wall of the second shell 20 and used for limiting the lever shaft 33 to rotate and/or move. The lock nut is sleeved on the lever shaft 33 and abutted against the shaft sleeve for abutting the limiting part on the outer side wall of the second housing 20, so that two ends of the lever shaft 33 are fixed on the second housing 20.
Further, in order to better fix the two ends of the lever shaft 33 on the second housing 20, a plurality of first positioning holes 26 are further formed on the outer side wall of the second housing 20 close to the third slot 23, and the plurality of first positioning holes 26 are arranged at intervals along the length direction of the third slot 23. Correspondingly, a plurality of second positioning holes are further formed in the outer side wall of the second housing 20 close to the fourth slot 24, and the plurality of second positioning holes are arranged at intervals along the length direction of the fourth slot 24. When the fixing device 38 fixes the lever shaft 33, one positioning hole is selected from the first positioning holes 26 and the second positioning holes respectively to limit the limiting portion of the fixing device 38, that is, the limiting portion of the fixing device 38 located at one end of the lever shaft 33 is located in one first positioning hole 26 of the first positioning holes 26 (as shown in fig. 7), and the limiting portion of the fixing device 38 located at the other end of the lever shaft 33 is located in one second positioning hole of the second positioning holes.
It should be noted that the structure of the fixing device 38 is not limited to this, for example, the number of the position-limiting parts is further increased based on the above, such as increasing from the original one (located at the front edge of the slot in fig. 6) to two oppositely arranged (located at the front edge and the rear edge of the slot respectively), or moving the position of the original position-limiting part from the front edge to the rear edge of the slot. In another embodiment, the fixing device 38 may comprise: a limit pin and a lock nut. Accordingly, the lever shaft 33 is provided with a plurality of limit through holes spaced apart in the axial direction thereof so as to facilitate insertion of the limit pins. When the fixing device is fixed, the limiting pin penetrates through the limiting through hole of the lever shaft 33 on the outer side wall of the second shell 20 and abuts against the outer side wall of the second shell 20, and the other end of the limiting pin is sleeved on the lever shaft 33 through the lock nut and abuts against the outer side wall of the second shell 20. Accordingly, the structure of the securing device 38 of the above example should not be construed as limiting the application.
Here, the number of the anti-damping members 30 is plural (2 and more), and therefore the case of including 4 anti-damping members 30 shown in the above example cannot be understood as a limitation of the present application. The number of the anti-damping members 30 is equal to the number of the first slots 11 and the second slots 22.
The second housing 20 may be an integrally formed housing, or may be a housing formed by combining a plurality of side plates. And are not further limited herein. It should be noted that the surfaces on which the second open groove 22, the third open groove 23 and the fourth open groove 24 are formed are not exclusive, and may be arranged according to the circumstances, for example, the second open groove 22 may be formed on the upper and lower sides of the second casing 20, the third open groove 23 and the fourth open groove 24 may be formed on the left and right sides, respectively, and accordingly, the position of the first open groove 11 is the upper and lower sides of the first casing 10. Therefore, the case where the second slot 22 is opened on both the left and right sides of the second housing 20, and the third slot 23 and the fourth slot 24 are opened on both the upper and lower sides, respectively, in the above example, cannot be understood as a limitation to the present application.
It should be noted that, in the present specification, the embodiments are all described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments may be referred to each other.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. A vibration damping device on a spacecraft, comprising:
the vibration-proof device comprises a first shell, a second shell and a third shell, wherein the first shell is provided with a first inner cavity capable of accommodating a component to be subjected to vibration resistance, two opposite sides of the first shell, which are far away from the first inner cavity, are provided with first slots, and the opening direction of the first slots is far away from the first inner cavity;
the second shell is provided with a second inner cavity for accommodating the first shell, second open grooves are formed in the inner walls of two opposite sides, facing the first open grooves, of the second shell, and the opening direction of each second open groove faces the first open groove;
and the two ends of the anti-damping component can slide in the first slot and the second slot, so that the distance between the first shell and the second shell is adjusted.
2. A vibration damping device on a spacecraft as claimed in claim 1, wherein said anti-damping member comprises: the first connecting shaft, the second connecting shaft, the spring and the lever shaft; the first connecting shaft and the second connecting shaft are connected through the lever shaft and are in an X shape;
one end of the first connecting shaft is connected with one end, close to the second spring, of the first spring, the other end of the first connecting shaft is connected with one end, close to the fourth spring, of the third spring, one end of the second connecting shaft is connected with one end, close to the first spring, of the second spring, and the other end of the second connecting shaft is connected with one end, close to the third spring, of the fourth spring.
3. The vibration damping device on the spacecraft of claim 2, wherein a third slot and a fourth slot are respectively arranged on two opposite sides of the second shell, wherein the side where the third slot is arranged is different from the side where the second slot is arranged;
two ends of the lever shaft respectively penetrate through the third open groove and the fourth open groove to extend out of the second shell, and the lever shaft can reciprocate in the third open groove and the fourth open groove to adjust an included angle between the two connecting shafts, so that the distance between the first shell and the second shell is adjusted.
4. A vibration damping device on a spacecraft as claimed in claim 3, wherein said anti-damping member further comprises a plurality of fixing means, and both ends of said lever shaft are respectively fixed to said second housing by at least one of said fixing means.
5. A vibration damping device on a spacecraft as claimed in claim 4, wherein each said fixing device comprises: the limiting part comprises a shaft sleeve and a limiting part arranged on the shaft sleeve, the shaft sleeve is sleeved on the lever shaft close to the outer side wall of the second shell, and the limiting part is abutted against the outer side wall of the second shell and used for limiting the rotation and/or movement of the lever shaft;
the locking nut is sleeved on the lever shaft and abutted against the shaft sleeve, and is used for abutting the limiting part against the outer side wall of the second shell.
6. The vibration damper on the spacecraft of claim 5, wherein a plurality of first positioning holes are further formed on the outer side wall of the second shell, which is close to the third slot, and the plurality of first positioning holes are arranged at intervals along the length direction of the third slot;
a plurality of second positioning holes are further formed in the outer side wall, close to the fourth slot, of the second shell, and the second positioning holes are arranged at intervals along the length direction of the fourth slot;
when the fixing device is used for fixing the lever shaft, the limiting part of the fixing device, which is positioned at one end of the lever shaft, is positioned in one of the first positioning holes, and the limiting part of the fixing device, which is positioned at the other end of the lever shaft, is positioned in one of the second positioning holes.
7. A vibration damping device on a spacecraft as claimed in claim 1, wherein said first housing comprises: the first side plate and the second side plate are arranged oppositely, and the first adjusting shaft and the second adjusting shaft are arranged oppositely;
a plurality of first through holes and a plurality of second through holes are respectively formed in the first side plate and the second side plate;
two ends of the first adjusting shaft respectively penetrate through the first through hole and the second through hole to be connected with the first side plate and the second side plate;
two ends of the second adjusting shaft respectively penetrate through the first through hole and the second through hole to be connected with the first side plate and the second side plate;
the first side plate and the second side plate can move on the first adjusting shaft and the second adjusting shaft and are used for adjusting the distance between the first side plate and the second side plate;
the cavity enclosed by the first adjusting shaft, the first side plate, the second adjusting shaft and the second side plate is the first inner cavity.
8. The vibration damper on a spacecraft of claim 7, wherein the first shell further comprises a plurality of second lock nuts, the first adjusting shaft and the second adjusting shaft are both provided with threads, and a plurality of scales are marked at intervals along the axial direction of the first adjusting shaft and the second adjusting shaft;
every two second locking nuts are respectively sleeved on one side, close to the second shell, of the first adjusting shaft and are respectively abutted against one sides, close to the second shell, of the first side plate and the second side plate, and are used for adjusting the distance between the first side plate and the second side plate;
every two second lock nuts are respectively sleeved on the second adjusting shaft and close to one side of the second shell, and are respectively abutted against the first side plate and one side of the second side plate close to the second shell, so that the distance between the first side plate and the second side plate can be adjusted.
9. The vibration damper on a spacecraft of claim 2, wherein said first housing further comprises a plurality of first cover plates, each two of said first cover plates are respectively covered on two ends of said first slot for limiting the movement of two springs in said first slot.
10. The vibration damper on a spacecraft of claim 2, wherein the second shell further comprises a plurality of second cover plates, each two of the second cover plates are respectively covered on two ends of the second slot, and are used for limiting the two springs in the second slot to move in the second slot.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010562377.1A CN111677813B (en) | 2020-06-17 | 2020-06-17 | Vibration damper on spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010562377.1A CN111677813B (en) | 2020-06-17 | 2020-06-17 | Vibration damper on spacecraft |
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| CN111677813A true CN111677813A (en) | 2020-09-18 |
| CN111677813B CN111677813B (en) | 2021-02-02 |
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| CN111677813B (en) | 2021-02-02 |
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