CN116104896A - Suspension type two-stage vibration damper and use method thereof - Google Patents
Suspension type two-stage vibration damper and use method thereof Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
- F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted
- F16F7/112—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted on fluid springs
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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
- F16F7/00—Vibration-dampers; Shock-absorbers
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- F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted
- F16F7/116—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted on metal springs
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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
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/14—Vibration-dampers; Shock-absorbers of cable support type, i.e. frictionally-engaged loop-forming cables
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Abstract
The embodiment of the invention discloses a suspension type two-stage vibration damper and a use method thereof, which are connected between an aircraft and a load and have an axial direction, wherein the suspension type two-stage vibration damper comprises: the connecting assembly comprises a plurality of connecting rods and a load hook, wherein the connecting rods are used for being connected with the aircraft, and the load hook is used for being connected with a load; the frame body assembly comprises a first fixed plate, a second fixed plate and a third fixed plate; the primary vibration reduction assembly comprises at least one primary vibration isolator; the secondary vibration reduction assembly comprises at least one secondary vibration isolator; the first fixed plate, the first vibration isolator, the second fixed plate, the second vibration isolator and the third fixed plate are sequentially connected in the axial direction, the connecting rod is further connected with the third fixed plate in the axial direction, and the load hook is further connected with the first fixed plate in the axial direction. According to the invention, the common primary vibration isolator and the common secondary vibration isolator are combined into a type of vibration isolator which can bear the tensile force generated when the load is hung so as to realize the vibration reduction effect.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle vibration reduction devices, in particular to a suspension type two-stage vibration reduction device and a using method thereof.
Background
With the development of unmanned aerial vehicle technology, unmanned aerial vehicles are increasingly widely applied to military and civil fields, such as unmanned operation for carrying various equipment for investigation, photographing, searching and the like. The unmanned aerial vehicle can generate a series of complex vibration phenomena due to the rotation of an engine, the change of the flying speed and the gesture, the take-off and landing and other movements during the flying, and the frequency spectrum of the vibration phenomena is wider, so that the vibration phenomena can have adverse effects on the carried equipment. For some precision devices, the effect of such vibration phenomenon may cause the device to fail to work properly, and therefore an effective vibration damping device must be installed between the unmanned aerial vehicle and the mounted device.
According to different vibration sources, two vibration isolation modes with different properties are generally divided: an active vibration isolation and a passive vibration isolation. The device itself is a vibration source that is isolated from the foundation to reduce its impact on the surroundings, known as active vibration isolation. If the vibration source comes from the foundation, the vibration isolation measures taken to prevent or reduce the transmission of external vibrations into the equipment are called passive vibration isolation.
With respect to passive vibration isolation, most unmanned aerial vehicle load mounting interfaces are designed below the belly or on both sides of the landing gear, and thus loads are typically mounted by hanging below the unmanned aerial vehicle. However, most of the currently used vibration dampers or vibration damping pads are press-fit, i.e. the vibration damping effect is relatively good when bearing a ballast load. It is therefore desirable to design a structure that achieves the vibration damping effect of the load in the suspended state by using a press-fit type vibration damper in combination.
Disclosure of Invention
The embodiment of the invention provides a suspension type two-stage vibration damper and a use method thereof, wherein a common primary vibration isolator and a common secondary vibration isolator are combined into a tensile force which can bear the tensile force generated when a load is suspended so as to realize the vibration damping effect; the primary vibration isolator and the secondary vibration isolator can perform vibration reduction twice, and bad and even serious influences of the vibration on load operation are avoided.
In order to solve the technical problems, the embodiment of the invention discloses the following technical scheme:
in one aspect, a suspension type two-stage vibration damper is provided for connection between an aircraft and a load, having an axial direction, the suspension type two-stage vibration damper comprising:
the connecting assembly comprises a plurality of connecting rods and a load hook, wherein the connecting rods are used for being connected with the aircraft, and the load hook is used for being connected with the load;
the frame body assembly comprises a first fixed plate, a second fixed plate and a third fixed plate;
the primary vibration reduction assembly comprises at least one primary vibration isolator;
the secondary vibration reduction assembly comprises at least one secondary vibration isolator;
the first fixing plate, the first-stage vibration isolator, the second fixing plate, the second-stage vibration isolator and the third fixing plate are sequentially connected in the axial direction, the connecting rod is further connected with the third fixing plate in the axial direction, and the load hook is further connected with the first fixing plate in the axial direction.
In addition to or in lieu of one or more of the features disclosed above, the primary vibration isolator includes a wire rope vibration isolator comprising: a first fixing base and a second fixing base opposite to each other in the axial direction; and
the plurality of steel wire ropes are connected between the first fixing seat and the second fixing seat;
the first fixing seat is connected with the first fixing plate, and the second fixing seat is connected with the second fixing plate.
In addition to or in lieu of one or more of the features disclosed above, the first fixing base is provided with a first mounting hole at a position opposite to the first fixing plate; and second mounting holes are formed in the positions, opposite to the second fixing base and the second fixing plate, of the second fixing base.
In addition to or in lieu of one or more of the features disclosed above, the secondary vibration isolator includes an air damping vibration isolator having a first mounting face and a second mounting face opposite each other in the axial direction, the first mounting face being connected to the second mounting plate and the second mounting face being connected to the third mounting plate.
In addition to or in lieu of one or more of the features disclosed above, the first mounting surface is provided with a third mounting hole at a location opposite the second mounting plate; and the second mounting surface and the third fixing plate are provided with fourth mounting holes at opposite positions.
In addition to or in lieu of one or more of the features disclosed above, the connecting rod includes a first end, a shaft, and a second end connected in sequence in the axial direction, the first end being connected to the aircraft, the second end being connected to the third fixed plate.
In addition to or in lieu of one or more of the features disclosed above, the first end is provided with external or internal threads extending in the axial direction and the second end is provided with internal threads extending in the axial direction.
In addition to or in lieu of one or more of the features disclosed above, the suspension type two-stage vibration damping device further has a radial direction perpendicular to the axial direction, the load hanger includes a hanger bar extending in the axial direction and a hanger suspension bar connected to the hanger bar and extending in the radial direction, the hanger bar being connected to the first fixed plate, the hanger suspension bar being connected to the load.
In addition to or in lieu of one or more of the features disclosed above, fifth mounting holes are provided in positions of the hanger bar opposite the first securing plate, and sixth mounting holes are provided in positions of the hanger bar opposite the load.
The circuit of the suspension type two-stage vibration damper in the technical scheme has the following advantages or beneficial effects: the connecting rod is connected with the third fixing plate, and the connecting rod is also connected with the aircraft, so that the aircraft forms a foundation in passive vibration isolation. The load hook is connected with the first fixed plate, and the load hook is also connected with a load, and the load is hung on the load hook. The first fixed plate, the first vibration isolator, the second fixed plate, the second vibration isolator and the third fixed plate are sequentially connected, at this time, the frame body component, the first vibration isolator, the second vibration isolator and the connecting rod are combined with the load hook to form a conjugated structure, the load is hung on the load hook to generate a tensile force, and the tensile force generated by the hung load is converted into a ballast force (pressure) for the first vibration isolator and the second vibration isolator by the conjugated structure. When unmanned operation is performed on the aircraft, vibration is generated, and the vibration is transmitted to the load. The primary vibration isolator and the secondary vibration isolator are connected in series to form a two-stage series vibration reduction structure, and the primary vibration isolator and the secondary vibration isolator are subjected to tensile force generated by a suspension load, namely, the primary vibration isolator and the secondary vibration isolator are subjected to direction-changing ballast force caused by the tensile force generated by the suspension load, so that the primary vibration isolator and the secondary vibration isolator can perform two vibration reduction effects on vibration, and bad or even serious influence on load operation caused by the vibration is avoided. The first-stage vibration isolator plays a role in first-stage vibration reduction, and is used for reducing low-frequency components in vibration. The secondary vibration isolator plays a role in secondary vibration reduction, and is used for reducing high-frequency components in vibration.
The common first-level vibration isolator and the second-level vibration isolator are combined into a type of vibration isolator which can bear the tensile force generated when a load is hung so as to realize the vibration reduction effect. After the first fixed plate, the first vibration isolator, the second fixed plate, the second vibration isolator and the third fixed plate are sequentially connected in the axial direction, a connecting rod installed on the upper part and the aircraft and a load hook connected on the lower part and the load are designed. The load is installed on the aircraft in a suspension mode, a two-stage series vibration reduction structure formed between the first-stage vibration isolator and the second-stage vibration isolator can bear tensile force generated when the load is suspended, the first-stage vibration isolator and the second-stage vibration isolator can well block vibration of the aircraft, the vibration reduction effect is relatively good, and the load is not affected by the vibration to normally operate.
Meanwhile, the vibration reduction effect under different loads and vibration spectrum conditions can be realized through replacing the primary vibration isolator and the secondary vibration isolator with different performance parameters in the device, and the application range is greatly improved.
On the other hand, further discloses a use method of the suspension type two-stage vibration damper, which comprises the following steps:
setting: setting the total mass of the load, the load hook and the first fixing plate as m 1 The method comprises the steps of carrying out a first treatment on the surface of the Setting the monomer mass of the second fixing plate as m 2 The second displacement generated during the movement is x 2 The method comprises the steps of carrying out a first treatment on the surface of the Setting the first rigidity coefficient of the first-stage vibration isolator as k 1 The first damping coefficient is c 1 The first displacement generated during movement is x 1 The method comprises the steps of carrying out a first treatment on the surface of the Setting the second rigidity coefficient of the secondary vibration isolator to be k 2 The second damping coefficient is c 2 The method comprises the steps of carrying out a first treatment on the surface of the Setting the third displacement of the aircraft as a foundation transferred to the suspension type two-stage vibration damper to u, assuming u=u 0 sin ωt, damping coefficient of suspension type two-stage damping device
The step of constructing a formula: establishing a differential equation set:
solving the differential equation set to obtain the product,
Δ＝ (k 1 -m 1 ω 2 +jc 1 ω) [k 1 +k 2 -m 2 ω 2 +jω(c 1 +c 2 )]-(k 1 +jc 1 ω) 2 (3)；
determining the first-stage vibration isolator, the second-stage vibration isolator and the second fixing plate: select T f And m 1 And by combining the values of formula 2 and formula 3, calculate k 1 、c 1 、x 1 、k 2 、c 2 And m 2 Is a numerical value of (2); according to k 1 、c 1 、x 1 、k 2 、c 2 And m 2 The values of the first-stage vibration isolator, the second-stage vibration isolator and the second fixing plate are selected.
The use method of the suspension type two-stage vibration damper in the technical scheme has the following advantages or beneficial effects: vibration reduction effects on vibration sources in different frequency spectrum ranges and different loads can be achieved by adjusting performance parameters of the first-stage vibration isolator and the second-stage vibration isolator and the mass of the second fixing plate. First of all based on the total weight m of the load to be carried by the aircraft, the load hook and the first fixing plate 1 Will m 1 Substituting and combining the formula 2 and the formula 3 to calculate k 1 、c 1 、x 1 、k 2 、c 2 And m 2 According to the value of k 1 、c 1 The performance parameters of the first-stage vibration isolator and the setting quantity of the first-stage vibration isolator are selected according to the value k 2 、c 2 The performance parameters of the secondary vibration isolator and the setting quantity of the secondary vibration isolator are selected according to the value of m 2 The value of (2) is selected from a certain weight of the second fixing plate. When the aircraft is embodied, a group of optimal first-stage vibration isolator, second-stage vibration isolator and second fixing plate are obtained by adopting a test screening method, and finally the first-stage vibration isolator, the second-stage vibration isolator and the second fixing plate are assembled with a connecting rod, a load hook, the first fixing plate and the third fixing plate to obtain the suspension type two-stage vibration damper capable of effectively damping vibration.
The first-stage vibration isolator and the second-stage vibration isolator with different performance parameters and the second fixing plates with different weights in the replacement device realize the vibration reduction effect under different loads and vibration spectrum conditions, and the application range is greatly improved.
Drawings
The technical solution and other advantageous effects of the present invention will be made apparent by the following detailed description of the specific embodiments of the present invention with reference to the accompanying drawings.
FIG. 1 is a schematic illustration of a connection of a suspension type two-stage vibration damping device according to an embodiment of the present invention;
FIG. 2 is an exploded block diagram of a suspension type two-stage vibration damping device according to an embodiment of the present invention;
fig. 3 is a schematic structural view of a wire rope vibration isolator provided according to an embodiment of the present invention;
fig. 4 is a schematic structural view of an air damping vibration isolator provided according to an embodiment of the present invention;
FIG. 5 is a schematic view of a connecting rod according to an embodiment of the present invention;
FIG. 6 is a schematic structural view of a load hook provided in accordance with an embodiment of the present invention;
FIG. 7 is a flow chart of a method of use provided in accordance with an embodiment of the present invention;
fig. 8 is a schematic diagram of a first vibration isolator, a second vibration isolator, and a second stationary plate according to an embodiment of the present invention.
The components of the drawings are identified as follows:
1. a connection assembly; 11. a connecting rod; 111. a first end; 1111. a seventh mounting hole; 112. a shaft;
113. a second end; 12. load hook; 121. a hook vertical rod; 122. a hook suspension rod; 1221. a sixth mounting hole; 123. reinforcing ribs;
2. a frame assembly; 21. a first fixing plate; 211. a first mounting hole; 212. a fifth mounting hole; 213. a first central bore; 22. a second fixing plate; 22a, a first fixing surface; 22b, a second fixing surface; 221. a second mounting hole; 222. a third mounting hole; 223. a second central bore; 23. a third fixing plate; 231. a fourth mounting hole; 232. an eighth mounting hole; 233. a third central bore;
3. a first-stage vibration isolator; 31. a wire rope vibration isolator; 311. a first fixing seat; 312. the second fixing seat;
313. a wire rope;
4. a secondary vibration isolator; 41. an air damping vibration isolator; 411. a first mounting surface; 412. and a second mounting surface.
Detailed Description
In order to make the objects, technical solutions and advantageous effects of the present invention more apparent, the present invention will be further described in detail with reference to the accompanying drawings and detailed description. It should be understood that the detailed description is intended to illustrate the invention, and not to limit the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, the meaning of "plurality" means two or more, unless specifically defined otherwise.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; the connection may be mechanical connection, direct connection or indirect connection through an intermediate medium, and may be internal connection of two elements or interaction relationship of two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is less level than the second feature.
Regarding passive vibration isolation, most load carrying interfaces of unmanned aerial vehicles are designed below the belly or on two sides of the landing gear, and most of the commonly used vibration dampers or vibration damping pads are press-fit, namely, the vibration damping effect is better when bearing ballast load. When the load is suspended below the belly or on both sides of the landing gear, the press-fit shock absorbers or shock absorbing pads used have a poor shock absorbing effect.
In order to solve the problem that the vibration reduction effect of the press-fit type vibration damper or vibration reduction pad is poor when the load is suspended below the belly or at two sides of the landing gear. The embodiment of the invention provides a suspension type two-stage vibration damper and a use method thereof. Fig. 1 to 6 show a schematic structural diagram of a suspension-type two-stage vibration damper, and fig. 7 to 8 show a schematic flow diagram of a method for using the suspension-type two-stage vibration damper.
Referring to fig. 1 and 2, there are shown a schematic connection diagram of a suspension type two-stage vibration damping device and an exploded view of the structure of the suspension type two-stage vibration damping device according to the present embodiment. A suspension type two-stage vibration damper, connect between aircraft and load, this embodiment aircraft selects unmanned aerial vehicle, and load is selected as equipment such as load radar, camera or cloud platform, has mutually perpendicular axial direction Z and radial direction Y, suspension type two-stage vibration damper includes:
the connection assembly 1 comprises a plurality of connection rods 11 and a load hook 12, said connection rods 11 being intended to be connected with said aircraft, said load hook 12 being intended to be connected with said load. The number of the connecting rods 11 and the load is not limited, and a suitable number may be selected according to the actual installation requirement of the suspension type two-stage vibration damping device. In this embodiment, the number of connecting rods 11 is eight, and the number of load hooks 12 is six. The connecting rod 11 is connected with the aircraft, so that the whole suspension type two-stage vibration damper is arranged below the aircraft, and specifically can be arranged below the belly of the unmanned aerial vehicle or on two sides of the landing gear. The load hanger 12 is connected to the load, and the load is suspended on the load hanger 12 so that the load is positioned below the whole suspended two-stage vibration damping device.
The frame assembly 2 includes a first fixing plate 21, a second fixing plate 22, and a third fixing plate 23. The structures of the first fixing plate 21, the second fixing plate 22 and the third fixing plate 23 are designed in accordance with the structures of the aircraft and the load. In the present embodiment, the first fixing plate 21 is annular, and the first fixing plate 21 has a first center hole 213 extending in the axial direction Z; the second fixing plate 22 and the third fixing plate 23 are square, the second fixing plate 22 is provided with a second central hole 223 in the axial direction Z in a penetrating manner, and the third fixing plate 23 is provided with a third central hole 233 in the axial direction Z in a penetrating manner. The "first", "second", and "third" of the first fixing plate 21, the second fixing plate 22, and the third fixing plate 23 are only for distinguishing between the different fixing plates provided on both sides of the primary vibration isolator 3 and the secondary vibration isolator 4, and are not limited to the number or order of the fixing plates.
The primary vibration reduction assembly comprises at least one primary vibration isolator 3; the secondary vibration reduction assembly comprises at least one secondary vibration isolator 4; the number of the first-stage vibration isolator 3 and the second-stage vibration isolator 4 is not limited, and an appropriate number may be selected according to the vibration reduction requirements of the suspension type two-stage vibration reduction device. In the present embodiment, the number of the primary vibration isolators 3 and the number of the secondary vibration isolators 4 are four. The "primary" and "secondary" in the primary vibration isolator 3 and the secondary vibration reduction assembly are only intended to be able to distinguish between different vibration isolators, and are not limitations on the power, performance or sequence of the vibration isolators. The performance parameters of the primary vibration isolator 3 and the secondary vibration isolator 4 are different.
The first fixing plate 21, the first vibration isolator 3, the second fixing plate 22, the second vibration isolator 4 and the third fixing plate 23 are sequentially connected in the axial direction Z, the connecting rod 11 is further connected with the third fixing plate 23 in the axial direction Z, and the load hook 12 is further connected with the first fixing plate 21 in the axial direction Z. Further defining the positions of the first fixing plate 21, the primary vibration isolator 3, the second fixing plate 22, the secondary vibration isolator 4 and the third fixing plate 23, the second fixing plate 22 has a first fixing surface 22a and a second fixing surface 22b opposite to each other in the axial direction Z, the primary vibration isolator 3 is fixed to the first fixing surface 22a, and the first fixing plate 21 is fixed to the side of the primary vibration isolator 3 facing away from the second fixing plate 22; the secondary vibration isolator 4 is fixed to the second fixing surface 22b, and the third fixing plate 23 is fixed to the side of the secondary vibration isolator 4 facing away from the second fixing plate 22. The second fixing plate 22 serves to connect the primary vibration isolator 3 and the secondary vibration isolator 4 in series, so that the primary vibration isolator 3 and the secondary vibration isolator 4 are connected in series to form a two-stage series vibration damping structure. The connecting rod 11, the first fixing plate 21, the first-stage vibration isolator 3, the second fixing plate 22, the second-stage vibration isolator 4, the third fixing plate 23 and the load hook 12 form a two-stage series vibration damping structure.
According to the suspension type two-stage vibration damper, the connecting rod 11 is connected with the third fixing plate 23, and the connecting rod 11 is also connected with the unmanned aerial vehicle, so that the unmanned aerial vehicle forms a foundation in passive vibration isolation. The load hook 12 is connected to the first fixing plate 21, and the load hook 12 is also connected to a load, which is suspended from the load hook 12. The first fixing plate 21, the first vibration isolator 3, the second fixing plate 22, the second vibration isolator 4 and the third fixing plate 23 are sequentially connected, at this time, the frame assembly 2, the first vibration isolator 3, the second vibration isolator 4 and the connecting rod 11 are combined with the load hook 12 to form a conjugate structure, and a tensile force is generated when the load is hung on the load hook 12, and the tensile force generated by the hanging load is converted into a ballast force (pressure) for the first vibration isolator 3 and the second vibration isolator 4 by the conjugate structure. When unmanned operation is performed on the aircraft, vibration is generated, and the vibration is transmitted to the load. Because the primary vibration isolator 3 and the secondary vibration isolator 4 are subjected to tensile force generated by suspension load, namely, the primary vibration isolator 3 and the secondary vibration isolator 4 are subjected to direction-changing ballast force caused by the tensile force generated by suspension load, and because the primary vibration isolator 3 and the secondary vibration isolator 4 are connected in series to form a two-stage series vibration damping structure, the primary vibration isolator 3 and the secondary vibration isolator 4 can perform two vibration damping effects on vibration, and bad or even serious influence on load operation caused by vibration is avoided. The primary vibration isolator 3 plays a role in primary vibration reduction, and the primary vibration isolator 3 in this embodiment is used to reduce low frequency components in vibration. The secondary vibration isolator 4 plays a role of secondary vibration reduction, and the secondary vibration isolator 4 is used for reducing high-frequency components in vibration in the embodiment.
The common primary vibration isolator 3 and the common secondary vibration isolator 4 are combined into a tensile force which can bear the load and is generated when the load is hung so as to realize the vibration reduction effect. After the first fixing plate 21, the first-stage vibration isolator 3, the second fixing plate 22, the second-stage vibration isolator 4 and the third fixing plate 23 are sequentially connected in the axial direction Z, a connecting rod 11 installed to the upper unmanned aerial vehicle and a load hook 12 connected to the lower load are designed. The load is installed on the aircraft in a suspension mode, the two-stage series vibration reduction structure formed between the first-stage vibration isolator 3 and the second-stage vibration isolator 4 can bear tensile force generated when the load is suspended, the first-stage vibration isolator 3 and the second-stage vibration isolator 4 can well block vibration of the aircraft, the vibration reduction effect is relatively good, and the load is not affected by the vibration to normally operate.
Meanwhile, vibration reduction effects under different loads and vibration spectrum conditions can be achieved through replacing the primary vibration isolator 3 and the secondary vibration isolator 4 with different performance parameters in the device, and the application range is greatly improved.
In the embodiment of the present invention, referring to fig. 3, which is a schematic structural diagram of a wire rope vibration isolator 31 of the present embodiment, the primary vibration isolator 3 includes the wire rope vibration isolator 31, and the wire rope vibration isolator 31 is used to reduce low frequency components in vibration.
The wire rope vibration isolator 31 includes: a first fixing seat 311 and a second fixing seat 312 opposite to each other in the axial direction Z; and a plurality of wire ropes 313 connected between the first fixing base 311 and the second fixing base 312; that is, a plurality of steel wires 313 are sleeved between the first fixing base 311 and the second fixing base 312. The first fixing base 311 is connected to the first fixing plate 21, and the second fixing base 312 is connected to the second fixing plate 22.
In the embodiment of the present invention, with continued reference to fig. 3, the first fixing base 311 and the first fixing plate 21 are provided with first mounting holes 211 at positions opposite to each other; the first fixing base 311 and the first fixing plate 21 are locked together by the first mounting hole 211 and the screw. The second fixing base 312 and the second fixing plate 22 are respectively provided with a second mounting hole 221 at the opposite position; the second fixing base 312 and the second fixing plate 22 are locked together by the second mounting hole 221 and the screw. The fixing mode of the first fixing base 311 and the first fixing plate 21, and the fixing mode of the second fixing base 312 and the second fixing plate 22 are simple, and the assembly is convenient.
Wherein, the first mounting hole 211 on the first fixing base 311 and the second mounting hole 221 on the second fixing base 312 are screw holes.
In the embodiment of the present invention, referring to fig. 4, which is a schematic structural diagram of an air damping vibration isolator 41 of the present embodiment, the secondary vibration isolator 4 includes the air damping vibration isolator 41, which can play a role of vibration reduction, and the air damping vibration isolator 41 is used to reduce high frequency components in vibration. The air damping vibration isolator 41 has a first mounting surface 411 and a second mounting surface 412 opposite to each other in the axial direction Z, the first mounting surface 411 being connected to the second fixing plate 22, that is, the air damping vibration isolator 41 being connected to the second fixing plate 22; the second mounting surface 412 is connected to the third fixed plate 23, that is, the air damping vibration isolator 41 is connected to the third fixed plate 23. Compressed air is filled between the first mounting surface 411 and the second mounting surface 412 of the air damping vibration isolator 41, and vibration reduction can be performed.
In the embodiment of the present invention, with continued reference to fig. 4, the first mounting surface 411 and the second fixing plate 22 are provided with third mounting holes 222 at positions opposite to each other; the air damping vibration isolator 41 and the second fixed plate 22 are locked together by the third mounting hole 222 and the screw while the first mounting surface 411 of the air damping vibration isolator 41 is in contact with the second fixed plate 22. The second mounting surface 412 is provided with a fourth mounting hole 231 at a position opposite to the third fixing plate 23; the air damping vibration isolator 41 and the third fixing plate 23 are locked together by the fourth mounting hole 231 and the screw, and the second mounting surface 412 of the air damping vibration isolator 41 is coupled to the third fixing plate 23. The air damping vibration isolator 41 and the second fixing plate 22, and the air damping vibration isolator 41 and the third fixing plate 23 are also simple in fixing manner, and convenient to assemble.
Wherein the fourth mounting hole 231 of the third fixing plate 23 is provided as a screw hole.
In an embodiment of the present invention, referring to fig. 5, which is a schematic structural diagram of the connecting rod 11 of the present embodiment, the connecting rod 11 includes a first end 111, a rod body 112, and a second end 113 sequentially connected in the axial direction Z, the first end 111 is connected to the aircraft, and the second end 113 is connected to the third fixing plate 23.
In an embodiment of the present invention, with continued reference to fig. 5, the first end 111 is provided with a first external thread extending in the axial direction Z, that is, a protruding post is provided at a position of the first end 111 opposite to the aircraft, and the protruding post is provided with a first external thread extending in the axial direction Z. The aircraft is fixedly connected with the first end 111 of the connecting rod 11 by means of a first external thread and a connecting internal thread on the aircraft.
The first end 111 is provided with a first internal thread extending in the axial direction Z, that is, the positions of the first end 111 opposite to the aircraft are provided with seventh mounting holes 1111, the seventh mounting holes 1111 are provided with first internal threads, and the aircraft and the first end 111 of the connecting rod 11 are fixedly connected together through the first internal threads and external threads on the aircraft.
The second end 113 is provided with a second internal thread extending in the axial direction Z, that is, the positions of the second end 113 opposite to the third fixing plate 23 are provided with eighth mounting holes 232, the eighth mounting holes 232 are provided with second internal threads, and the third fixing plate 23 and the second end 113 of the connecting rod 11 are locked together through the second internal threads and screws. Wherein the eighth mounting hole 232 on the third fixing plate 23 is provided as a screw hole.
In the embodiment of the present invention, referring to fig. 6, which is a schematic structural view of the load hanger 12 of the present embodiment, the load hanger 12 includes a hanger bar 121 extending in the axial direction Z and a hanger bar 122 connected to the hanger bar 121 and extending in the radial direction Y, the hanger bar 121 is connected to the first fixing plate 21, and the hanger bar 122 is connected to the load.
In the embodiment of the present invention, with continued reference to fig. 6, the positions of the hook upright 121 opposite to the first fixing plate 21 are provided with fifth mounting holes 212, and the hook upright 121 and the first fixing plate 21 are locked together through the fifth mounting holes 212 and screws. The positions of the hanger suspension rods 122 opposite to the load are respectively provided with a sixth mounting hole 1221, and the hanger suspension rods 122 and the load are locked together through the sixth mounting holes 1221 and screws.
Wherein the fifth mounting hole 212 of the hook pole 121 is a threaded hole. The sixth mounting hole 1221 of the hanger bar 122 is provided as a threaded hole or through hole.
In the embodiment of the invention, with continued reference to the figure, a reinforcing rib 123 is further connected between the hook upright rod 121 and the hook suspension rod 122, so as to further strengthen the rigidity and strength of the load hook 12 and ensure the stability of the load hanging on the load hook 12. Wherein, couple pole setting 121, couple pole 122 and strengthening rib 123 integrated into one piece.
Referring to fig. 7 and 8, a flow chart of the method of using the present embodiment and a model diagram of the primary vibration isolator 3, the secondary vibration isolator 4, and the second fixing plate 22 are shown, respectively. The embodiment of the invention provides a use method of a suspension type two-stage vibration damper, which comprises the following steps:
setting: setting the total mass of the load, the load hook 12 and the first fixing plate 21 to be m 1 The method comprises the steps of carrying out a first treatment on the surface of the The mass of the second fixing plate 22 is set to be m 2 The second displacement generated during the movement is x 2 The method comprises the steps of carrying out a first treatment on the surface of the Setting a first stiffness of the primary vibration isolator 3The coefficient is k 1 The first damping coefficient is c 1 The first displacement generated during movement is x 1 The method comprises the steps of carrying out a first treatment on the surface of the Setting the second rigidity coefficient of the secondary vibration isolator 4 to be k 2 The second damping coefficient is c 2 The method comprises the steps of carrying out a first treatment on the surface of the Setting the third displacement of the aircraft as a foundation transferred to the suspension type two-stage vibration damper to u, assuming u=u 0 sin ωt, damping coefficient of suspension type two-stage damping device
The step of constructing a formula: establishing a differential equation set:
solving the differential equation set to obtain the product,
Δ＝ (k 1 -m 1 ω 2 +jc 1 ω) [k 1 +k 2 -m 2 ω 2 +jω(c 1 +c 2 )]-(k 1 +jc 1 ω) 2 (3)；
the determination steps of the primary vibration isolator 3, the secondary vibration isolator 4 and the second fixing plate 22 are as follows: select T f And m 1 And by combining the values of formula 2 and formula 3, calculate k 1 、c 1 、x 1 、k 2 、c 2 And m 2 Is a numerical value of (2); according to k 1 、c 1 、x 1 、k 2 、c 2 And m 2 The values of the first vibration isolator 3, the second vibration isolator 4 and the second fixing plate 22 are selected.
The use method of the suspension type two-stage vibration damper comprises the steps that the suspension type two-stage vibration damper forms a two-stage series vibration damper structure, and the vibration damper coefficient T of the suspension type two-stage vibration damper can be obtained by combining the formula 2 and the formula 3 f And a first stiffness coefficient k of the primary vibration isolator 3 1 First damping coefficient c 1 Second stiffness coefficient k of secondary vibration isolator 4 2 Second damping coefficient c 2 Monomer mass m of second fixing plate 22 2 There is a relationship and vibration reduction effects are different for vibration sources of different frequency bands.
Vibration reduction effects on vibration sources and different loads in different frequency spectrum ranges can be achieved by adjusting the performance parameters of the primary vibration isolator 3 and the secondary vibration isolator 4 and the mass of the second fixing plate 22. First of all based on the total weight m of the load to be carried by the aircraft, the load hook 12 and the first fixing plate 21 1 Will m 1 Substituting and combining the formula 2 and the formula 3 to calculate k 1 、c 1 、x 1 、k 2 、c 2 And m 2 According to the value of k 1 、c 1 The values of the performance parameters of the first-stage vibration isolator 3 and the setting number of the first-stage vibration isolator 3 are selected according to k 2 、c 2 The performance parameters of the secondary vibration isolator 4 and the number of the secondary vibration isolators 4 to be arranged are selected according to m 2 A certain weight of the second fixing plate 22 is selected. When the aircraft is embodied, a group of optimal first-stage vibration isolator 3, second-stage vibration isolator 4 and second fixing plate 22 are obtained by adopting a test screening method, and finally the first-stage vibration isolator 3, the second-stage vibration isolator 4 and the second fixing plate 22 are assembled with the connecting rod 11, the load hook 12, the first fixing plate 21 and the third fixing plate 23, so that a suspension type two-stage vibration damper capable of effectively damping vibration is obtained.
The first-stage vibration isolator 3 and the second-stage vibration isolator 4 with different performance parameters and the second fixing plate 22 with different weights in the replacement device realize the vibration reduction effect under different load and vibration spectrum conditions, and the application range is greatly improved.
The above steps are presented merely to aid in understanding the method, structure, and core concept of the invention. It will be apparent to those skilled in the art that various changes and modifications can be made to the present invention without departing from the principles of the invention, and such changes and modifications are intended to be included within the scope of the appended claims.
Claims (10)
1. A suspension type two-stage vibration damper for connection between an aircraft and a load having an axial direction, said suspension type two-stage vibration damper comprising:
-a connection assembly (1) comprising a plurality of connection rods (11) and a load hook (12), said connection rods (11) being intended to be connected with said aircraft, said load hook (12) being intended to be connected with said load;
a frame assembly (2) comprising a first fixing plate (21), a second fixing plate (22) and a third fixing plate (23);
the primary vibration reduction assembly comprises at least one primary vibration isolator (3);
the secondary vibration reduction assembly comprises at least one secondary vibration isolator (4);
the first fixing plate (21), the first-stage vibration isolator (3), the second fixing plate (22), the second-stage vibration isolator (4) and the third fixing plate (23) are sequentially connected in the axial direction, the connecting rod (11) is further connected with the third fixing plate (23) in the axial direction, and the load hook (12) is further connected with the first fixing plate (21) in the axial direction.
2. A suspension two-stage vibration damping device according to claim 1, characterized in that the primary vibration isolator (3) comprises a wire rope vibration isolator (31), the wire rope vibration isolator (31) comprising: a first fixing base (311) and a second fixing base (312) opposite to each other in the axial direction; and
a plurality of steel wire ropes (313) connected between the first fixing base (311) and the second fixing base (312);
the first fixing seat (311) is connected with the first fixing plate (21), and the second fixing seat (312) is connected with the second fixing plate (22).
3. A suspension type two-stage vibration damping device according to claim 2, characterized in that the first fixing base (311) and the first fixing plate (21) are provided with first mounting holes (211) at opposite positions; the second fixing base (312) and the second fixing plate (22) are provided with second mounting holes (221) at opposite positions.
4. A suspension two-stage vibration damping device according to claim 1, characterized in that the secondary vibration isolator (4) comprises an air damping vibration isolator (41), the air damping vibration isolator (41) having a first mounting face (411) and a second mounting face (412) opposite to each other in the axial direction, the first mounting face (411) being connected to the second fixing plate (22), the second mounting face (412) being connected to the third fixing plate (23).
5. A suspension type two-stage vibration damping device according to claim 4, wherein the first mounting surface (411) and the second fixing plate (22) are each provided with a third mounting hole (222) at a position opposite to each other; the second mounting surfaces (412) and the third fixing plate (23) are provided with fourth mounting holes (231) at positions opposite to each other.
6. A suspension two-stage vibration damper according to claim 1, characterized in that the connecting rod (11) comprises a first end (111), a shaft (112) and a second end (113) connected in sequence in the axial direction, the first end (111) being connected to the aircraft and the second end (113) being connected to the third fixed plate (23).
7. A suspension two-stage vibration damping device according to claim 6, characterized in that the first end (111) is provided with a first external thread or a first internal thread extending in the axial direction, and the second end (113) is provided with a second internal thread extending in the axial direction.
8. A suspension type two-stage vibration damper according to claim 1, wherein the suspension type two-stage vibration damper further has a radial direction perpendicular to the axial direction, the load hanger (12) includes a hanger rod (121) extending in the axial direction and a hanger suspension rod (122) connected to the hanger rod (121) and extending in the radial direction, the hanger rod (121) is connected to the first fixing plate (21), and the hanger suspension rod (122) is connected to the load.
9. The suspension type two-stage vibration damper according to claim 8, wherein fifth mounting holes (212) are provided at positions of the hanger rod (121) opposite to the first fixing plate (21), and sixth mounting holes (1221) are provided at positions of the hanger rod (122) opposite to the load.
10. The use method of the suspension type two-stage vibration damper is characterized by comprising the following steps of:
setting: setting the total mass of the load, the load hook (12) and the first fixing plate (21) to be m 1 The method comprises the steps of carrying out a first treatment on the surface of the Setting the monomer mass of the second fixing plate (22) as m 2 The second displacement generated during the movement is x 2 The method comprises the steps of carrying out a first treatment on the surface of the Setting the first rigidity coefficient of the primary vibration isolator (3) as k 1 The first damping coefficient is c 1 The first displacement generated during movement is x 1 The method comprises the steps of carrying out a first treatment on the surface of the Setting the second rigidity coefficient of the secondary vibration isolator (4) as k 2 The second damping coefficient is c 2 The method comprises the steps of carrying out a first treatment on the surface of the Setting the third displacement of the aircraft as a foundation transferred to the suspension type two-stage vibration damper to u, assuming u=u 0 sin ωt, damping coefficient of suspension type two-stage damping device
The step of constructing a formula: establishing a differential equation set:
solving the differential equation set to obtain the product,
Δ＝ (k 1 -m 1 ω 2 +jc 1 ω) [k 1 +k 2 -m 2 ω 2 +jω(c 1 +c 2 )]-(k 1 +jc 1 ω) 2 (3)；
determining the primary vibration isolator (3), the secondary vibration isolator (4) and the second fixing plate (22): select T f And m 1 And (3) by combining the formula (2) and the formula (3), and calculating k 1 、c 1 、x 1 、k 2 、c 2 And m 2 Is a numerical value of (2); according to k 1 、c 1 、x 1 、k 2 、c 2 And m 2 The values of the first-stage vibration isolator (3), the second-stage vibration isolator (4) and the second fixing plate (22) are selected.
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4742998A (en) * | 1985-03-26 | 1988-05-10 | Barry Wright Corporation | Active vibration isolation system employing an electro-rheological fluid |
| US5310157A (en) * | 1989-08-16 | 1994-05-10 | Minus K Technology, Inc. | Vibration isolation system |
| US20070114707A1 (en) * | 2005-11-18 | 2007-05-24 | Shun-Hsu Tu | Impact resistance vibration isolator |
| CN105605148A (en) * | 2016-03-25 | 2016-05-25 | 东北大学 | Damping system for vehicle-mounted CT (computerized tomography) equipment |
| CN106352012A (en) * | 2016-11-29 | 2017-01-25 | 浙江华飞智能科技有限公司 | Shock-absorbing device and unmanned aerial vehicle |
| JP2017180658A (en) * | 2016-03-30 | 2017-10-05 | 不二ラテックス株式会社 | Vibration control device |
| CN207595259U (en) * | 2017-12-20 | 2018-07-10 | 江苏航丰智控无人机有限公司 | Plant protection unmanned plane |
| CN108386696A (en) * | 2018-04-28 | 2018-08-10 | 厦门南羽科技有限公司 | A kind of camera hanger and carrier arrangement |
| CN209083901U (en) * | 2018-11-06 | 2019-07-09 | 山东智翼航空科技有限公司 | Unmanned machine head damping vibration attenuation platform and its unmanned plane |
| CN111609067A (en) * | 2020-04-16 | 2020-09-01 | 山东省科学院海洋仪器仪表研究所 | Six-degree-of-freedom quasi-zero stiffness vibration isolation device and debugging method and vibration isolation method thereof |
| CN112228488A (en) * | 2020-10-12 | 2021-01-15 | 中国自然资源航空物探遥感中心 | Two-stage vibration damper for domestic strapdown inertial navigation type aerogravimeter |
| CN215673347U (en) * | 2021-07-23 | 2022-01-28 | 成都浩孚科技有限公司 | Photoelectric pod double-layer vibration damping device |
-
2023
- 2023-01-17 CN CN202310090117.2A patent/CN116104896A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4742998A (en) * | 1985-03-26 | 1988-05-10 | Barry Wright Corporation | Active vibration isolation system employing an electro-rheological fluid |
| US5310157A (en) * | 1989-08-16 | 1994-05-10 | Minus K Technology, Inc. | Vibration isolation system |
| US20070114707A1 (en) * | 2005-11-18 | 2007-05-24 | Shun-Hsu Tu | Impact resistance vibration isolator |
| CN105605148A (en) * | 2016-03-25 | 2016-05-25 | 东北大学 | Damping system for vehicle-mounted CT (computerized tomography) equipment |
| JP2017180658A (en) * | 2016-03-30 | 2017-10-05 | 不二ラテックス株式会社 | Vibration control device |
| CN106352012A (en) * | 2016-11-29 | 2017-01-25 | 浙江华飞智能科技有限公司 | Shock-absorbing device and unmanned aerial vehicle |
| CN207595259U (en) * | 2017-12-20 | 2018-07-10 | 江苏航丰智控无人机有限公司 | Plant protection unmanned plane |
| CN108386696A (en) * | 2018-04-28 | 2018-08-10 | 厦门南羽科技有限公司 | A kind of camera hanger and carrier arrangement |
| CN209083901U (en) * | 2018-11-06 | 2019-07-09 | 山东智翼航空科技有限公司 | Unmanned machine head damping vibration attenuation platform and its unmanned plane |
| CN111609067A (en) * | 2020-04-16 | 2020-09-01 | 山东省科学院海洋仪器仪表研究所 | Six-degree-of-freedom quasi-zero stiffness vibration isolation device and debugging method and vibration isolation method thereof |
| CN112228488A (en) * | 2020-10-12 | 2021-01-15 | 中国自然资源航空物探遥感中心 | Two-stage vibration damper for domestic strapdown inertial navigation type aerogravimeter |
| CN215673347U (en) * | 2021-07-23 | 2022-01-28 | 成都浩孚科技有限公司 | Photoelectric pod double-layer vibration damping device |
Non-Patent Citations (1)
| Title |
|---|
| 任晋宇，张二主编: "船艇振动与噪声", vol. 1, 哈尔滨工程大学出版社, pages: 99 - 106 * |
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