CN204750584U - Structure and aircraft are measured to shock -absorbing structure , inertia that has a shock -absorbing function - Google Patents
Structure and aircraft are measured to shock -absorbing structure , inertia that has a shock -absorbing function Download PDFInfo
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- CN204750584U CN204750584U CN201520442832.9U CN201520442832U CN204750584U CN 204750584 U CN204750584 U CN 204750584U CN 201520442832 U CN201520442832 U CN 201520442832U CN 204750584 U CN204750584 U CN 204750584U
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Abstract
The utility model relates to a structure and aircraft are measured to shock -absorbing structure, inertia that has a shock -absorbing function, shock -absorbing structure is arranged in carrying out the shock attenuation to the inertia measuring unit of aircraft, shock -absorbing structure includes: first spring assembly, first spring assembly contain set up in inertia measuring unit's top end with a plurality of springs between the frame construction's of aircraft the top, the second spring assembly, the second spring assembly contain set up in inertia measuring unit's bottom end with a plurality of springs between frame construction's the bottom. Through this disclosed technical scheme, can be for a long time, the separation vibrations are to inertia measuring unit's influence steadily.
Description
Technical field
The disclosure relates to vehicle technology field, particularly relates to shock-damping structure, has the inertia measurement structure of shock-absorbing function and aircraft.
Background technology
Inertial Measurement Unit (IMU, Inertialmeasurementunit), for measuring the three-axis attitude angle of object and acceleration/accel, thus has very important effect in the navigation and control process of aircraft.
Utility model content
The disclosure provides shock-damping structure, has the inertia measurement structure of shock-absorbing function and aircraft, to solve the deficiency in correlation technique.
According to the first aspect of disclosure embodiment, provide a kind of shock-damping structure, described shock-damping structure is used for carrying out damping to the Inertial Measurement Unit in aircraft; Described shock-damping structure comprises:
First spring assembly, described first spring assembly comprises the multiple springs between the top being arranged at the top end face of described Inertial Measurement Unit and the framed structure of described aircraft;
Second spring assembly, described second spring assembly comprises the multiple springs between bottom end face and the bottom of described framed structure being arranged at described Inertial Measurement Unit.
Optionally, described first spring assembly and described second spring assembly are symmetrical arranged along the platform residing for described Inertial Measurement Unit.
Optionally, also comprise:
First support, the multiple springs in described first spring assembly are connected with the top of described framed structure by described first support;
Second support, the multiple springs in described second spring assembly are connected with the bottom of described framed structure by described second support.
Optionally, the spring in described first spring assembly and described second spring assembly is extension spring.
Optionally, when described shock-damping structure and described Inertial Measurement Unit complete assembling, the spring in described first spring assembly and described second spring assembly is all in tensile deformation state.
Optionally, tensile deformation degree and the described aircraft motor speed in the course of the work of the spring in described first spring assembly and described second spring assembly are inverse correlation.
Optionally, when described Inertial Measurement Unit is the schistose texture of rectangular in cross-section, described first spring assembly and described second spring assembly comprise four springs respectively, and wherein one end of each spring is connected to the summit place of described Inertial Measurement Unit, the other end is connected to described framed structure.
Optionally, also comprise:
Damping body, is arranged between described Inertial Measurement Unit and described framed structure.
According to the second aspect of disclosure embodiment, a kind of inertia measurement structure with shock-absorbing function is provided, comprises:
Inertial Measurement Unit;
As the shock-damping structure as described in arbitrary in above-described embodiment.
According to the third aspect of disclosure embodiment, a kind of aircraft is provided, comprises: as the shock-damping structure as described in arbitrary in above-described embodiment.
The technical scheme that embodiment of the present disclosure provides can comprise following beneficial effect:
From above-described embodiment, the disclosure by arranging the first and second spring assembly between Inertial Measurement Unit and the framed structure of aircraft, the vibrations making these spring assembly can absorb Inertial Measurement Unit to be subject to, thus the service life extending Inertial Measurement Unit.Meanwhile, because the 26S Proteasome Structure and Function of the spring of same way manufacture is stable, difference is little, the build-up tolerance of the spring assembly be made up of these springs can be reduced, promote assembly precision and damping effect.In addition, because spring is less likely to occur aging, thus can guarantee that shock-damping structure has longer period of service, also correspondingly ensure the service life of Inertial Measurement Unit.
Should be understood that, it is only exemplary and explanatory that above general description and details hereinafter describe, and can not limit the disclosure.
Accompanying drawing explanation
Accompanying drawing to be herein merged in specification sheets and to form the part of this specification sheets, shows and meets embodiment of the present disclosure, and is used from specification sheets one and explains principle of the present disclosure.
Fig. 1 is the schematic diagram of a kind of shock-damping structure in correlation technique.
Fig. 2 is the schematic diagram of a kind of shock-damping structure according to an exemplary embodiment.
Fig. 3 is the schematic diagram of the another kind of shock-damping structure according to an exemplary embodiment.
Fig. 4 is the schematic diagram of another shock-damping structure according to an exemplary embodiment.
Fig. 5 is the schematic diagram of another shock-damping structure according to an exemplary embodiment.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.Embodiment described in following exemplary embodiment does not represent all embodiments consistent with the disclosure.On the contrary, they only with as in appended claims describe in detail, the example of apparatus and method that aspects more of the present disclosure are consistent.
Fig. 1 is the schematic diagram of a kind of shock-damping structure in correlation technique, as shown in Figure 1, IMU2 is arranged in the framed structure 1 of aircraft, and by being pasted on the sponge 3 ' between IMU2 and framed structure 1, damping is carried out to IMU2, such as in FIG, sponge 3 ' is pasted between the top end face of IMU2 and the top of framed structure 1, between the bottom end face of IMU2 and the bottom of framed structure 1.
But, due to the behavior of structure of sponge 3 ', cause its structure itself not fixed, even if between the same batch of sponge 3 ' generated, also there is very large textural difference, make corresponding build-up tolerance larger.Meanwhile, the service life of sponge 3 ' is very short, especially when operating ambient temperature is higher, is easy to occur aging and follow the string, thus cannot be used for the shock-absorbing function to IMU2.
Therefore, the disclosure by proposing new shock-damping structure, to solve the problems referred to above existed in correlation technique.
Fig. 2 is the schematic diagram of a kind of shock-damping structure according to an exemplary embodiment, and as shown in Figure 2, shock-damping structure can comprise:
First spring assembly 31, described first spring assembly 31 comprises the multiple springs between the top being arranged at the top end face of IMU2 and the framed structure 1 of described aircraft;
Second spring assembly 32, described second spring assembly 32 comprises the multiple springs between bottom end face and the bottom of described framed structure 1 being arranged at IMU2.
In this embodiment, " first " and " second " is for distinguishing two spring assembly being positioned at IMU2 both sides end face.Wherein, each spring assembly comprises multiple spring, utilizes the elasticity of spring to absorb the vibration energy of aircraft.Because the structure of spring is fixed, the spring adopting same way to produce has consistent structure, there is not the structural unstable situation of sponge 3 '; Meanwhile, the service life of spring is very long, and is not easy the impact being subject to working environment, can for a long time, stably for the damping to IMU2.
In this embodiment; by arranging the first spring assembly 31 and the second spring assembly 32; make, in the either direction of IMU2 in the vertical direction, all can obtain corresponding shock-absorbing protecting, namely the first spring assembly 31 and the second spring assembly 32 can carry out the energy of absorbing vibration generation by deformation.Meanwhile, because each spring assembly comprises multiple spring, thus multiple spring can provide corresponding antitorque effect in the horizontal direction, thus can realize the comprehensive shock-absorbing protecting to IMU2.
In this embodiment, multiple springs that each spring assembly comprises, can adopt any-mode to arrange, and there is not inevitable contact between two spring assembly, only need the predeterminated position guaranteeing to be maintained by IMU2 between two spring assembly.Wherein, as an illustrative embodiments, the first spring assembly 31 and the second spring assembly 32 can be made to be symmetrical arranged along the platform residing for IMU2, then only to need to make the first spring assembly 31 and the second spring assembly 32 adopt identical structure and be symmetrical arranged, contribute to the design simplifying shock-damping structure.
1, types of springs
In the above-described embodiments, owing to being respectively arranged with multiple spring in the both sides of IMU2, each spring thus in the first spring assembly 31 and the second spring assembly 32 can be all extension spring.Wherein, when described shock-damping structure and IMU2 complete assembling, the spring in the first spring assembly 31 and the second spring assembly 32 is all in tensile deformation state.
Simultaneously, when aircraft motor speed is in the course of the work low, the vibration frequency produced is lower, amplitude is larger, thus the compression set degree of spring under compression set state in the first spring assembly 31 and the second spring assembly 32 high (compression set degree and the aircraft motor speed in the course of the work of the spring namely in the first spring assembly 31 and the second spring assembly 32 are inverse correlation), thus by the application force to IMU2, IMU2 can be helped to maintain the stabilized conditions of self.
2, the structure of spring assembly
As an exemplary embodiment, when IMU2 is the schistose texture of rectangular in cross-section, as shown in Figure 3, first spring assembly 31 and the second spring assembly 32 comprise four springs respectively, wherein one end of each spring is connected to the summit place of IMU2, the other end is connected to framed structure 1, thus by stretching while four direction, IMU2 is fixed on the predeterminated position in framed structure 1; Wherein, when the parameter homogeneous phase such as specification, setting angle of each spring while, IMU2 is positioned at the center of these springs.
In this embodiment, to the uniform specification of spring, reduce the difficulty of the aspects such as the manufacture to spring, replacing, assembling, and reduce the design of whole shock-damping structure and assembling difficulty.
3, fixed support
By the shock-damping structure in IMU2 and above-described embodiment, can form relatively independent " having the inertia measurement structure of shock-absorbing function ", this structure is mounted in the framed structure 1 of aircraft, realizes measurement function after can independently producing and assemble.
For the first spring assembly 31 and the second spring assembly 32 in shock-damping structure, the top of framed structure 1 and bottom need to arrange supporting connection structure, such as when the spring end in the first spring assembly 31 and the second spring assembly 32 is hook-shaped, the top of framed structure 1 and bottom can pre-set corresponding hole, thus realize being connected with the cooperation in hole by hook.
In order to the topology requirement to reduction framed structure 1, promote the universality of " having the inertia measurement structure of shock-absorbing function ", as shown in Figure 4, shock-damping structure can also comprise:
First support 41, the multiple springs in described first spring assembly 31 are connected with the top of described framed structure 1 by described first support 41;
Second support 42, the multiple springs in described second spring assembly 32 are connected with the bottom of described framed structure 1 by described second support 42.
In this embodiment, first support 42 and the second support 43 can be in the form of sheets, thus directly the first support 42 and the second support 43 can be affixed to respectively top and the bottom of framed structure 1, the installation of " the inertia measurement structure with shock-absorbing function " can be completed, and make respective outer side edges and improvement without the need to framed structure 1.
4, damping body
In the above-described embodiments, in order to strengthen the damping effect to IMU2, shock-damping structure can also comprise damping body, and this damping body is arranged between IMU2 and framed structure 1.Ratio as shown in Figure 5, the first damping body 51 and the second damping body 52 can be comprised, wherein the first damping body 51 is arranged between the top end face of IMU2 and the top of framed structure 1, and the two ends of the first damping body 51 are connected with the top end face of IMU2, the top of framed structure 1 respectively, second damping body 52 is arranged between the bottom end face of IMU2 and the bottom of framed structure 1, and the two ends of the second damping body 52 are connected with the bottom end face of IMU2, the bottom of framed structure 1 respectively.
In this embodiment, damping body or can have arbitrarily the materials such as elastomeric plastic cement by other and makes for silica gel.By arranging damping body, more effective energy absorbing can be realized, further enhancing the damping effect of shock-damping structure, avoid the impact of aircraft vibrations on IMU2.
The disclosure also proposed a kind of aircraft, comprises the shock-damping structure in above-mentioned any embodiment, thus carries out shock-absorbing protecting to the IMU2 installed in this aircraft.
Those skilled in the art, at consideration specification sheets and after putting into practice disclosed herein disclosing, will easily expect other embodiment of the present disclosure.The application is intended to contain any modification of the present disclosure, purposes or adaptations, and these modification, purposes or adaptations are followed general principle of the present disclosure and comprised the undocumented common practise in the art of the disclosure or conventional techniques means.Specification sheets and embodiment are only regarded as exemplary, and true scope of the present disclosure and spirit are pointed out by claim below.
Should be understood that, the disclosure is not limited to precision architecture described above and illustrated in the accompanying drawings, and can carry out various amendment and change not departing from its scope.The scope of the present disclosure is only limited by appended claim.
Claims (10)
1. a shock-damping structure, is characterized in that, described shock-damping structure is used for carrying out damping to the Inertial Measurement Unit in aircraft; Described shock-damping structure comprises:
First spring assembly, described first spring assembly comprises the multiple springs between the top being arranged at the top end face of described Inertial Measurement Unit and the framed structure of described aircraft;
Second spring assembly, described second spring assembly comprises the multiple springs between bottom end face and the bottom of described framed structure being arranged at described Inertial Measurement Unit.
2. shock-damping structure according to claim 1, is characterized in that, described first spring assembly and described second spring assembly are symmetrical arranged along the platform residing for described Inertial Measurement Unit.
3. shock-damping structure according to claim 1, is characterized in that, also comprises:
First support, the multiple springs in described first spring assembly are connected with the top of described framed structure by described first support;
Second support, the multiple springs in described second spring assembly are connected with the bottom of described framed structure by described second support.
4. shock-damping structure according to claim 1, is characterized in that, the spring in described first spring assembly and described second spring assembly is extension spring.
5. shock-damping structure according to claim 4, is characterized in that, when described shock-damping structure and described Inertial Measurement Unit complete assembling, the spring in described first spring assembly and described second spring assembly is all in tensile deformation state.
6. shock-damping structure according to claim 5, is characterized in that, tensile deformation degree and the described aircraft motor speed in the course of the work of the spring in described first spring assembly and described second spring assembly are inverse correlation.
7. shock-damping structure according to claim 1, it is characterized in that, when described Inertial Measurement Unit is the schistose texture of rectangular in cross-section, described first spring assembly and described second spring assembly comprise four springs respectively, and wherein one end of each spring is connected to the summit place of described Inertial Measurement Unit, the other end is connected to described framed structure.
8. shock-damping structure according to claim 1, is characterized in that, also comprises:
Damping body, is arranged between described Inertial Measurement Unit and described framed structure.
9. there is an inertia measurement structure for shock-absorbing function, it is characterized in that, comprising:
Inertial Measurement Unit;
Shock-damping structure according to any one of claim 1-8.
10. an aircraft, is characterized in that, comprising: the shock-damping structure according to any one of claim 1-8.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520442832.9U CN204750584U (en) | 2015-06-24 | 2015-06-24 | Structure and aircraft are measured to shock -absorbing structure , inertia that has a shock -absorbing function |
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| CN201520442832.9U CN204750584U (en) | 2015-06-24 | 2015-06-24 | Structure and aircraft are measured to shock -absorbing structure , inertia that has a shock -absorbing function |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908963A (en) * | 2015-06-24 | 2015-09-16 | 广州飞米电子科技有限公司 | Damping structure, inertial measurement structure with damping function and air vehicle |
| CN105862234A (en) * | 2016-06-01 | 2016-08-17 | 江苏金铁人自动化科技有限公司 | Rack damping device |
| CN110725888A (en) * | 2019-10-22 | 2020-01-24 | 荆州介太科技有限公司 | IMU lever vibration damper and method thereof |
-
2015
- 2015-06-24 CN CN201520442832.9U patent/CN204750584U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908963A (en) * | 2015-06-24 | 2015-09-16 | 广州飞米电子科技有限公司 | Damping structure, inertial measurement structure with damping function and air vehicle |
| CN105862234A (en) * | 2016-06-01 | 2016-08-17 | 江苏金铁人自动化科技有限公司 | Rack damping device |
| CN110725888A (en) * | 2019-10-22 | 2020-01-24 | 荆州介太科技有限公司 | IMU lever vibration damper and method thereof |
| CN110725888B (en) * | 2019-10-22 | 2021-05-11 | 荆州介太科技有限公司 | IMU lever vibration damper and method thereof |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Damping structure, inertial measurement structure with damping function and air vehicle Effective date of registration: 20180305 Granted publication date: 20151111 Pledgee: Silicon Valley Bank Co., Ltd. Pledgor: GUANGZHOU FEIMI ELECTRONIC TECHNOLOGY CO., LTD. Registration number: 2018310000008 |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right |