CN111255854A - Dynamic anti-resonance vibration absorption device and unmanned helicopter - Google Patents
Dynamic anti-resonance vibration absorption device and unmanned helicopter Download PDFInfo
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- CN111255854A CN111255854A CN202010178345.1A CN202010178345A CN111255854A CN 111255854 A CN111255854 A CN 111255854A CN 202010178345 A CN202010178345 A CN 202010178345A CN 111255854 A CN111255854 A CN 111255854A
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- 238000010521 absorption reaction Methods 0.000 title abstract description 21
- 230000001681 protective effect Effects 0.000 claims description 28
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 description 7
- 230000033001 locomotion Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000002955 isolation Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000005284 excitation Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- 229910000639 Spring steel Inorganic materials 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 210000004556 brain Anatomy 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a dynamic anti-resonance vibration absorption device, which comprises a first connecting structure, a second connecting structure and a vibration absorption device, wherein the first connecting structure is used for fixing a flight controller; the first connecting structure is used for connecting the helicopter main body which generates vibration load in flight, and the first connecting structure can only move along the vertical direction relative to the second connecting structure; the buffer structure is elastically connected with the first connecting structure and the second connecting structure along the vertical direction; and the mass block is elastically hung on the first connecting structure and can generate vertical vibration relative to the first connecting structure. The invention enables the flight controller to have only one degree of freedom in the vertical direction; meanwhile, the vibration energy of the flight controller is transferred to the mass block by utilizing the principle of dynamic antiresonance, so that the vibration load transmitted to the flight controller by the helicopter in flight is reduced, and the control precision of the flight controller is improved. The invention also discloses an unmanned helicopter with the dynamic anti-resonance vibration absorption device.
Description
Technical Field
The invention relates to the technical field of helicopter vibration isolation, in particular to a dynamic anti-resonance vibration absorption device and an unmanned helicopter comprising the same.
Background
In a helicopter, the engine is subjected to vibration caused by the motion process of a piston during the combustion of gasoline, the deviation between an output shaft and a connecting piece and the like, and the helicopter rotor blades are subjected to alternating load generated by unsteady aerodynamic force during the operation. The two vibration sources enable the helicopter to always bear continuous periodic vibration load.
The flight controller is the 'brain' of the helicopter, and the helicopter can automatically fly by means of the flight controller. And the excessive vibration of the flight controller can cause the automatic control difficulty of the flight controller to be higher, the precision to be lower and even out of control, and the performance of the cross double-rotor helicopter is influenced.
In the conventional vibration isolation technique, the six degrees of freedom of the flight controller are released, and the vibration of the flight controller is reduced by adjusting the system natural frequency using an elastic element or a spring as a medium. But the dynamic loads generated in flight in the various degrees of freedom are coupled together and cannot effectively isolate the vibration.
In summary, how to reduce the vibration load transmitted to the flight controller during the flight of the helicopter and further improve the control accuracy of the flight controller becomes a problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In view of the above, the present invention is directed to a dynamic anti-resonance vibration absorption apparatus for reducing the vibration load transmitted to a flight controller during flight of a helicopter, thereby improving the control accuracy of the flight controller.
The invention also aims to disclose an unmanned helicopter with the dynamic anti-resonance vibration absorption device.
In order to achieve the purpose, the invention discloses the following technical scheme:
a dynamic anti-resonance vibration absorbing apparatus comprising:
the first connecting structure is used for fixing the flight controller;
a second connecting structure for connecting a helicopter body generating a vibration load in flight, the first connecting structure being movable only in a vertical direction relative to the second connecting structure;
the buffer structure is used for elastically connecting the first connecting structure and the second connecting structure along the vertical direction;
and the mass block is elastically hung on the first connecting structure and can generate vibration in a vertical direction relative to the first connecting structure.
Preferably, in the above dynamic antiresonance vibration absorbing apparatus, the mass block is fixed to the first connecting structure through a spring plate, and the spring plate has a rigidity in a horizontal direction greater than a rigidity in a vertical direction;
or the mass block is fixed on the first connecting structure through an elastic frame or an elastic column.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, the first connecting structure and the second connecting structure are connected by a linear bearing set;
the linear bearing set includes:
a guide bar arranged in a vertical direction;
the linear bearing is slidably sleeved on the guide rod in a sleeving manner, and the guide rod and the linear bearing are respectively arranged on the first connecting structure and the second connecting structure.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, four linear bearing sets are arranged in a rectangular shape;
or, the number of the linear bearing sets is two or three.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, the buffer structure is a coil spring, an elastic column or a compression spring, and two ends of the buffer structure are respectively connected to the first connecting structure and the second connecting structure.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, four buffer structures are provided, and are arranged at four connecting corners of the first connecting structure and the second connecting structure in a rectangular shape and located outside the linear bearing set; or the linear bearing groups are arranged in a staggered mode;
or, the number of the buffer structures is three.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, the first connecting structure is provided with a protective shell, and the flight controller is embedded in the protective shell;
the protective housing is provided with a mounting hole for inserting the flight controller and an auxiliary hole convenient for taking out the flight controller, and the mounting hole and the auxiliary hole are located on two opposite surfaces of the protective housing.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, the first connecting structure includes an upper connecting plate, and the protective shell is disposed above the upper connecting plate;
the second connecting structure is a lower-layer connecting plate;
the upper layer connecting plate and the lower layer connecting plate are both high-rigidity light plates.
Preferably, in the dynamic anti-resonance vibration absorbing apparatus, two or four of the mass blocks are symmetrically disposed on two sides of the first connecting structure.
From the above technical solution, the dynamic anti-resonance vibration absorbing apparatus disclosed in the present invention comprises: the first connecting structure is used for fixing the flight controller; the first connecting structure is used for connecting the helicopter main body which generates vibration load in flight, and the first connecting structure can only move along the vertical direction relative to the second connecting structure; the buffer structure is elastically connected with the first connecting structure and the second connecting structure along the vertical direction; and the mass block is elastically hung on the first connecting structure and can generate vertical vibration relative to the first connecting structure.
The invention discloses a dynamic anti-resonance vibration absorption device which is used for realizing the connection of a flight controller and a helicopter main body. When the helicopter main body connecting structure is used, the flight controller is fixed on the first connecting structure, and the second connecting structure is connected with the helicopter main body.
In this way, the vibration load generated by the helicopter main body in flight is transferred to the first connecting structure through the second connecting structure and finally transferred to the flight controller; in the process, under the buffer action of the buffer structure, the first connecting structure moves in the vertical direction relative to the second connecting structure, and meanwhile, the mass block generates vibration in the vertical direction relative to the first connecting structure, so that the vibration energy of the flight controller is transferred to the mass block, the energy of basic vibration of the flight controller is dissipated by the mass block, and the purpose of reducing the vibration is achieved.
In summary, the dynamic anti-resonance vibration absorption device provided by the invention enables the flight controller to have only one degree of freedom in the vertical direction, so that the flight controller can only receive the dynamic load in the vertical direction; meanwhile, the vibration energy of the flight controller is transferred to the mass block by utilizing the principle of dynamic antiresonance, so that the vibration load transmitted to the flight controller by the helicopter in flight is reduced, and the control precision of the flight controller is improved.
The invention also discloses an unmanned helicopter, which comprises a helicopter main body generating vibration load in flight, a flight controller controlling the helicopter main body and any one of the dynamic anti-resonance vibration absorption devices, wherein the flight controller is connected with the helicopter main body through the dynamic anti-resonance vibration absorption device.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a dynamic anti-resonance vibration absorbing apparatus according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a spring plate and a mass according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a linear bearing set disclosed in the embodiment of the invention.
In FIGS. 1-3:
1-protective shell, 2-flight controller, 3-spring mass system, 31-spring plate, 32-mass block, 4-linear bearing group, 41-support, 42-guide rod, 43-linear bearing, 5-spiral spring, 6-upper connecting plate and 7-lower connecting plate.
Detailed Description
The embodiment of the invention discloses a dynamic anti-resonance vibration absorption device, which reduces the vibration load transferred to a flight controller by a helicopter in flight and further improves the control precision of the flight controller.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-3, a dynamic anti-resonance vibration absorption apparatus according to an embodiment of the present invention includes: a first connecting structure for fixing the flight controller 2; the first connecting structure is used for connecting the helicopter main body which generates vibration load in flight, and the first connecting structure can only move along the vertical direction relative to the second connecting structure; the buffer structure is elastically connected with the first connecting structure and the second connecting structure along the vertical direction; a mass 32 resiliently suspended from the first connecting structure, the mass 32 being capable of generating vertical vibrations relative to the first connecting structure.
It should be noted that the flight controller 2 of the present invention is specifically an intelligent microcomputer, and can implement autonomous flight of the unmanned aerial vehicle. The vertical direction is a direction perpendicular to the horizontal direction.
The dynamic anti-resonance vibration absorption device disclosed by the embodiment is used for realizing the connection of the flight controller 2 and the helicopter main body. When the helicopter main body connecting structure is used, the flight controller 2 is fixed on the first connecting structure, and the second connecting structure is connected with the helicopter main body.
In this way, the vibration load generated by the helicopter main body in flight is transmitted to the first connecting structure through the second connecting structure and finally transmitted to the flight controller 2; in the process, under the buffer action of the buffer structure, the first connection structure moves in the vertical direction relative to the second connection structure, and meanwhile, the mass block 32 generates vertical vibration relative to the first connection structure, so that the vibration energy of the flight controller 2 is transferred to the mass block 32, the energy of the basic vibration of the flight controller 2 is dissipated by the mass block 32, and the purpose of reducing the vibration is achieved.
In summary, the dynamic anti-resonance vibration absorption apparatus provided by the present invention enables the flight controller 2 to have only one degree of freedom in the vertical direction, so that the flight controller 2 only receives the dynamic load in the vertical direction; meanwhile, the vibration energy of the flight controller 2 is transferred to the mass block 32 by utilizing the principle of dynamic antiresonance, so that the vibration load transmitted to the flight controller 2 by the helicopter in flight is reduced, and the control precision of the flight controller 2 is improved.
In a specific embodiment, the mass 32 is fixed to the first connecting structure by the spring plate 31, and the spring plate 31 has a rigidity in the horizontal direction that is greater than a rigidity in the vertical direction. The spring plate 31 used in the present invention is a metal plate having a certain rigidity, and two through holes are provided at one end connected to the first connecting structure.
As shown in fig. 1-2, one end of the spring plate 31 is fixed to the first connecting structure, and the other end is fixed to the mass block 32; the spring plate 31 has one end carrying the mass 32 extending outward, so that the mass 32 is suspended on the spring plate 31 in a cantilever manner.
The present embodiment forms a spring-mass system 3 with a mass 32 and a spring plate 31. The frequency of the unmanned helicopter to the body is basically determined. The flight controller 2 and the spring mass system 3 are connected with each other by utilizing the principle of dynamic antiresonance, and the vibration energy of the flight controller 2 can be transferred to the mass block 32 by adjusting the relationship between the mass block 32 and the spring piece 31; the energy of the basic vibration of the flight controller 2 is dissipated by the additional mass 32, achieving the purpose of reducing the vibration.
During debugging, the second connecting structure needs to be connected and fixed on the excitation equipment; the excitation equipment is equipment capable of providing periodic frequency bands and provides the frequency of the unmanned helicopter to the body.
The dynamic anti-resonance vibration absorption device has adjustable parameters, can achieve the best vibration absorption effect, and improves the performance of the whole machine.
The spring plate 31 is not limited to spring steel, and other materials may be used as long as the design conditions are met.
The spring piece 31 of the embodiment is not easy to deform and has long service life. Of course, the mass 32 may also be fixed on the first connecting structure through an elastic component such as an elastic frame, an elastic column, etc., so that the mass 32 can generate vertical vibration relative to the first connecting structure.
Preferably, the first connecting structure and the second connecting structure are connected through a linear bearing set 4; the linear bearing group 4 includes a guide rod 42 provided in the vertical direction; a linear bearing 43 slidably sleeved on the guide rod 42, the guide rod 42 and the linear bearing 43 being respectively arranged on the first connecting structure and the second connecting structure.
To facilitate assembly, the guide bar 42 is mounted on the first or second attachment structure by means of a support 41. The holder 41 has a flange and a holding hole. The holding hole of the holder 41 holds one end of the guide rod 42; the support 41 is provided with a pretensioned screw, by means of which the guide rod 42 is clamped, the cross section of the guide rod 42 perpendicular to the axis being flush with the flange surface of the support 41.
To reduce the friction experienced by the first and second connection structures during relative movement, the guide rod 42 is preferably a smooth rod, i.e., having a smooth surface.
As shown in fig. 3, the linear bearing 43, the guide rod 42 and the support 41 form a group, that is, the linear bearing group 4. The other end of the guide rod 42 is inserted into the center hole of the linear bearing 43, so that the first connecting structure, the flight controller 2, the protective shell 1, the mass block 32, and the spring piece 31 can slide with a certain displacement in the vertical direction.
Specifically, the guide rod 42 is disposed in the first connection structure, and the linear bearing 43 is disposed in the second connection structure, which may be interchanged.
This embodiment realizes through linear bearing group 4 that can first connection structure along vertical direction motion relative second connection structure, and the structure is fairly simple, and is better to the restriction effect of direction of motion moreover. Of course, the linear bearing set 4 may be replaced by the matching of a slide block and a guide rail.
In a further technical scheme, the number of the linear bearing sets 4 is four, the linear bearing sets are arranged in a rectangular shape, and the relative rotation of the first connecting structure and the second connecting structure can be prevented. Four supports 41 and four guide rods 42 are fixed below the first connecting structure; the second connecting structure fixes four linear bearings 43 to form four groups which are symmetrically distributed in a space formed by the first connecting structure and the second connecting structure, so that the motion guiding effect is better.
In practical situations, two or three linear bearing sets 4 may be used, and may be adjusted according to actual requirements.
In order to simplify the structure, the buffer structure is a coil spring 5, and two ends of the coil spring 5 are respectively connected with the first connecting structure and the second connecting structure. The first connecting structure is connected with the second connecting structure through the spiral spring 5, the spiral spring 5 is placed between the first connecting structure and the second connecting structure, one end of the spiral spring 5 is fixed with the first connecting structure through a bolt, and the other end of the spiral spring 5 is fixed with the second connecting structure through a bolt.
The natural frequency of the system can be changed by adjusting the rigidity of the spiral spring 5 and the weight of other parts arranged on the first connecting structure, so that the fundamental frequency is 2 times greater than the natural frequency of the system, and vibration isolation can be realized; meanwhile, by adjusting the relationship between the spring piece 31 and the mass block 32, the vibration energy of the flight controller 2 is transferred to the mass block 32, and under the condition of no damping, the vibration isolation effect of the system is one hundred percent, so that the performance of the unmanned helicopter is improved.
The coil spring 5 has good elasticity, and can better buffer the vibration received by the first connecting structure. Alternatively, the buffer structure may be an elastic column, a pressure spring, or the like.
The four spiral springs 5 are arranged at four connecting corners of the first connecting structure and the second connecting structure in a rectangular shape and are positioned outside the linear bearing set 4.
The protective case 1, the flight controller 2, the spring piece 31, the mass 32, and the first connecting structure are separated from the second connecting structure by using four coil springs 5.
Four coil springs 5 are respectively placed at four corners of a layer formed by the first connecting structure and the second connecting structure, and eight groups of bolts and nuts are used by the coil springs 5. In the above-described layering, four identical linear bearing sets 4 are fixed.
Of course, the number of the coil springs 5 may be other, such as three; the helical springs 5 may also be staggered with respect to the linear bearing sets 4.
Preferably, the first connecting structure is provided with a protective shell 1, and the flight controller 2 is embedded in the protective shell 1; the protective shell 1 is provided with a mounting hole for inserting the flight controller 2 and an auxiliary hole convenient for taking out the flight controller 2, and the mounting hole and the auxiliary hole are located on two opposite surfaces of the protective shell 1.
The protective case 1 is used to protect the flight controller 2. The appearance of the flight controller 2 is of a three-dimensional rectangular structure, four threaded holes are formed in the upper portion of the flight controller, the flight controller 2 is matched with the four threaded holes, and the flight controller 2 is fixed in the protective shell 1 through four bolts and is convenient to disassemble and assemble.
The protective shell 1 is a rectangular shell, and is provided with a through hole for connection in order to be fixed with other components. An outer ring through hole of the protective shell 1 is used for connecting a first connecting structure, and an inner ring through hole is used for fixing the flight controller 2; the protective shell 1 is a hexahedron; one surface is provided with a mounting hole, and the opposite surface is provided with an auxiliary hole; the flight controller 2 is inserted into the protective case 1 through a mounting hole, and the auxiliary hole is used for taking out the flight controller 2.
Specifically, four through holes are formed in the protective shell 1, matched through holes matched with the first connecting structure are formed in the protective shell 1, and the protective shell 1 and the first connecting structure are fastened through bolts and nuts.
This application can also not set up above-mentioned protective housing 1, with flight controller 2 snap-on first connection structure.
In order to simplify the structure, the first connecting structure comprises an upper connecting plate 6, and the protective shell 1 is arranged above the upper connecting plate 6; the second connecting structure is a lower connecting plate 7.
The flight controller 2 and the protective shell 1 are fixed above the upper layer connecting plate 6. The upper layer connecting plate 6 is a square body; the through-hole that upper layer connecting plate 6 outermost periphery was equipped with is used for fixed coil spring 5 one end, and the second circle through-hole is used for fixed protective housing 1, and two a set of through-holes innermost are used for fixing support 41.
Four supports 41 are arranged below the upper layer connecting plate 6, and flanges of the supports 41 are attached to the lower layer plane of the upper layer connecting plate 6 and fastened by bolts and nuts; enough space is left at the binding face of the protective shell 1 and the upper connecting plate 6, and the bolts for connecting the flange of the support 41 and the upper connecting plate 6 do not interfere.
The lower layer connecting plate 7 is provided with four circles of through holes, and the first circle of through holes from outside to inside is connected with the spiral spring 5; the second circle of through holes are not connected with any part and play a role in positioning during machining or assembling; the third circle of through holes is used for fixing the linear bearing 43; the fourth circle of through holes are central holes and are used for inserting bolts and fixing excitation equipment for test and test.
Four linear bearings 43 are arranged on the lower connecting plate 7, one side of each linear bearing 43 is provided with a flange with four through holes, and the linear bearings 43 are fixed with the lower connecting plate 7 through the flanges.
In the invention, the upper-layer connecting plate 6 and the lower-layer connecting plate 7 are both high-rigidity light plates, and the materials are not limited to aluminum materials. The material can be other materials according to the design requirements, so that the material can meet the rigidity required by the design. While the lighter the material used the better.
The first connecting structure and the second connecting structure can also be other structures, such as connecting brackets, connecting blocks and the like.
Specifically, two masses 32 are symmetrically disposed on two sides of the first connecting structure. Spring pieces 31 and mass blocks 32 are respectively fixed on two opposite surfaces of the upper layer connecting plate 6, namely the left side and the right side of the flight controller 2.
The number of the mass blocks 32 can be adjusted according to the actual design requirement, such as four.
The dynamic anti-resonance vibration absorption device has the advantages of compact structure, symmetrical layout, adjustable parameters, convenient assembly and disassembly, improvement on the performance of the whole machine and the like.
The embodiment of the invention also discloses an unmanned helicopter, which comprises a helicopter main body generating vibration load in flight, a flight controller 2 controlling the helicopter main body and the dynamic anti-resonance vibration absorption device provided by any one of the embodiments, wherein the flight controller 2 is connected with the helicopter main body through the dynamic anti-resonance vibration absorption device, so that the vibration load transmitted to the flight controller 2 by the helicopter in flight is reduced, and the control precision of the flight controller 2 is further improved.
Specifically, the unmanned helicopter of the present embodiment is a cross twin-rotor unmanned helicopter, and may also be in other structural forms.
The invention has simple structure and light weight, can adjust the transmission efficiency of the system and is beneficial to improving the performance of the cross double-rotor unmanned helicopter.
It should be noted that in this specification, positional terms such as above, below, peripheral, and inside are used merely to distinguish one entity from another and to more specifically describe spatial positions between structures. And do not necessarily require or imply any actual relationship or order between the entities.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A dynamic anti-resonance vibration absorbing apparatus, comprising:
a first connection structure for fixing the flight controller (2);
a second connecting structure for connecting a helicopter body generating a vibration load in flight, the first connecting structure being movable only in a vertical direction relative to the second connecting structure;
the buffer structure is used for elastically connecting the first connecting structure and the second connecting structure along the vertical direction;
a mass (32) resiliently suspended on the first connection structure, the mass (32) being capable of generating a vertical vibration relative to the first connection structure.
2. The dynamic antiresonance vibration absorbing apparatus according to claim 1, characterized in that the mass (32) is fixed to the first connecting structure by a spring plate (31), the spring plate (31) having a greater stiffness in the horizontal direction than in the vertical direction;
alternatively, the mass (32) is fixed to the first connecting structure by a flexible frame or a flexible column.
3. The dynamic anti-resonance vibration absorbing apparatus according to claim 1, wherein the first connecting structure and the second connecting structure are connected by a linear bearing set (4);
the linear bearing set (4) comprises:
a guide rod (42) arranged in the vertical direction;
a linear bearing (43) slidably sleeved on the guide rod (42), wherein the guide rod (42) and the linear bearing (43) are respectively arranged on the first connecting structure and the second connecting structure.
4. The dynamic anti-resonance vibration absorbing apparatus according to claim 3, wherein said linear bearing sets (4) are four and arranged in a rectangular shape;
or, the number of the linear bearing sets (4) is two or three.
5. The dynamic antiresonance vibration absorbing apparatus according to claim 3, wherein the buffer structure is a coil spring (5), an elastic column or a compression spring, and both ends of the buffer structure are connected to the first connecting structure and the second connecting structure, respectively.
6. The dynamic anti-resonance vibration absorbing apparatus according to claim 5, wherein said buffer structures are four, and are arranged in a rectangular shape at four connecting corners of said first connecting structure and said second connecting structure, and are located outside said linear bearing group (4); or is arranged in a staggered way with the linear bearing group (4);
or, the number of the buffer structures is three.
7. The dynamic anti-resonance vibration absorbing apparatus according to claim 1, wherein the first connecting structure is provided with a protective shell (1), the flight controller (2) being embedded in the protective shell (1);
the protection shell (1) is provided with a mounting hole for inserting the flight controller (2) and an auxiliary hole convenient for taking out the flight controller (2), and the mounting hole and the auxiliary hole are located on two opposite surfaces of the protection shell (1).
8. The dynamic anti-resonance vibration absorbing apparatus according to claim 7, wherein the first connecting structure comprises an upper connecting plate (6), the protective case (1) being disposed above the upper connecting plate (6);
the second connecting structure is a lower-layer connecting plate (7);
the upper layer connecting plate (6) and the lower layer connecting plate (7) are both high-rigidity light plates.
9. The dynamic antiresonance vibration absorbing device according to claim 1, characterized in that said masses (32) are two or four, symmetrically arranged on both sides of said first connection structure.
10. An unmanned helicopter comprising a helicopter main body which generates a vibration load in flight and a flight controller (2) which controls said helicopter main body, characterized by further comprising a dynamic anti-resonance vibration absorbing apparatus according to any one of claims 1 to 9, said flight controller (2) being connected to said helicopter main body through said dynamic anti-resonance vibration absorbing apparatus.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010178345.1A CN111255854A (en) | 2020-03-13 | 2020-03-13 | Dynamic anti-resonance vibration absorption device and unmanned helicopter |
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| CN202010178345.1A CN111255854A (en) | 2020-03-13 | 2020-03-13 | Dynamic anti-resonance vibration absorption device and unmanned helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113562186A (en) * | 2021-07-26 | 2021-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Aircraft and anti-vibration module thereof |
| CN114934980A (en) * | 2022-06-16 | 2022-08-23 | 广东美芝精密制造有限公司 | Vibration isolation assembly, compressor device, electrical equipment and vehicle |
-
2020
- 2020-03-13 CN CN202010178345.1A patent/CN111255854A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113562186A (en) * | 2021-07-26 | 2021-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Aircraft and anti-vibration module thereof |
| CN114934980A (en) * | 2022-06-16 | 2022-08-23 | 广东美芝精密制造有限公司 | Vibration isolation assembly, compressor device, electrical equipment and vehicle |
| CN114934980B (en) * | 2022-06-16 | 2023-11-24 | 广东美芝精密制造有限公司 | Vibration isolation assembly, compressor device, electrical equipment and vehicle |
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