CN205186539U - 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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- CN205186539U CN205186539U CN201520442872.3U CN201520442872U CN205186539U CN 205186539 U CN205186539 U CN 205186539U CN 201520442872 U CN201520442872 U CN 201520442872U CN 205186539 U CN205186539 U CN 205186539U
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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: spring unit, spring unit is connected to respectively inertia measuring unit with the frame construction of aircraft is in order to absorb the vibrations that the aircraft produced. 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:
Spring assembly, described spring assembly is connected to the framed structure of described Inertial Measurement Unit and described aircraft respectively, to absorb the vibrations that described aircraft produces.
Optionally, described spring assembly comprises:
First spring, the bottom of described first spring is connected with the top end face of described Inertial Measurement Unit, and the top of described first spring is connected with the top of described framed structure;
Second spring, the top of described second spring is connected with the bottom end face of described Inertial Measurement Unit, and the bottom of described second spring is connected with the bottom of described framed structure.
Optionally, also comprise:
First support, the top of described first spring is connected with the top of described framed structure by described first support;
Second support, the bottom of described second spring is connected with the bottom of described framed structure by described second support.
Optionally, described first spring and described second spring are Compress Spring.
Optionally, when described spring assembly and described Inertial Measurement Unit complete assembling, described first spring and described second spring are in compression set state.
Optionally, described first spring and described second spring-compressed deformation degree and described aircraft motor speed are in the course of the work inverse correlation.
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 spring assembly between Inertial Measurement Unit and the framed structure of aircraft, vibrations making spring assembly can absorb Inertial Measurement Unit to be subject to, thus extend the service life of Inertial Measurement Unit.Meanwhile, because the 26S Proteasome Structure and Function of the spring assembly of same way manufacture is stable, difference is little, the build-up tolerance of spring assembly can be reduced, promote assembly precision and damping effect.In addition, because spring assembly 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.
By providing stable working environment in aircraft, contributing to IMU and keeping good working order in the course of the work.But aircraft, in flight course, along with electric machine rotation can cause whole aircraft to produce vibrations, in order to avoid vibration influence IMU working process, needs to carry out shock-absorbing protecting to IMU.
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:
Spring assembly 3, described spring assembly 3 is connected to the framed structure 1 of described Inertial Measurement Unit 2 and described aircraft respectively, to absorb the vibrations that described aircraft produces.
In this embodiment, the assembly that namely spring assembly 3 is made up of 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, IMU2 comprises top end face and bottom end face, then spring assembly 3 simultaneously at top end face and the bottom end face of IMU2, can carry out damping to IMU2; Or spring assembly 3 also between either party and the framed structure 1 only in the top end face or bottom end face of IMU2, can carry out damping to IMU2.
As an exemplary embodiment, when spring assembly 3 is positioned at top end face and the bottom end face of IMU2 simultaneously, as shown in Figure 3, this spring assembly 3 can comprise:
First spring 31, the described bottom of the first spring 31 is connected with the top end face of IMU2, and the top of described first spring 31 is connected with the top of described framed structure 1;
Second spring 32, the top of described second spring 32 is connected with the bottom end face of IMU2, and the bottom of described second spring 32 is connected with the bottom of described framed structure 1.
In this embodiment; by arranging the first spring 31 and the second spring 32; make, in the either direction of IMU2 in the vertical direction, all can obtain corresponding shock-absorbing protecting, namely the first spring 31 and the second spring 32 can carry out the energy of absorbing vibration generation by deformation.Meanwhile, due to the behavior of structure of spring itself, make the antitorque effect that it also can realize to a certain extent in the horizontal direction, thus the comprehensive shock-absorbing protecting to IMU2 can be realized.
Wherein, the first spring 31 and the second spring 32 can be Compress Spring, and when spring assembly 3 completes assembling with IMU2, the first spring 31 and the second spring 32 are all in compression set state; And, when aircraft motor speed is in the course of the work low, the vibration frequency produced is lower, amplitude is larger, thus the first spring 31 and the compression set degree of the second spring 32 under compression set state high (namely the first spring 31 and the second spring 32 compression set degree and aircraft motor speed are in the course of the work inverse correlation), thus by the application force to IMU2, IMU2 can be helped to maintain the stabilized conditions of self.
Visible, 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.
When spring assembly 3 only comprises the first spring 31 and the second spring 32, the top of framed structure 1 and bottom need to arrange supporting connection structure, such as when the end of the first spring 31 and the second spring 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 33, the top of described first spring 31 is connected with the top of described framed structure 1 by described first support 33;
Second support 34, the bottom of described second spring 32 is connected with the bottom of described framed structure 1 by described second support 34.
In this embodiment, first support 33 and the second support 34 can be in the form of sheets, thus directly the first support 33 and the second support 34 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.
In addition, 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 41 and the second damping body 42 can be comprised, wherein the first damping body 41 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 41 are connected with the top end face of IMU2, the top of framed structure 1 respectively, second damping body 42 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 42 are connected with the bottom end face of IMU2, the bottom of framed structure 1 respectively.As an exemplary embodiment, the central hollow position that the first damping body 41 can be arranged at the central hollow position of the first spring 31, the second damping body 42 can be arranged at the second spring 32, thus reduce the space hold in framed structure 1.
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 (9)
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:
Spring assembly, described spring assembly is connected to the framed structure of described Inertial Measurement Unit and described aircraft respectively, to absorb the vibrations that described aircraft produces.
2. shock-damping structure according to claim 1, is characterized in that, described spring assembly comprises:
First spring, the bottom of described first spring is connected with the top end face of described Inertial Measurement Unit, and the top of described first spring is connected with the top of described framed structure;
Second spring, the top of described second spring is connected with the bottom end face of described Inertial Measurement Unit, and the bottom of described second spring is connected with the bottom of described framed structure.
3. shock-damping structure according to claim 2, is characterized in that, also comprises:
First support, the top of described first spring is connected with the top of described framed structure by described first support;
Second support, the bottom of described second spring is connected with the bottom of described framed structure by described second support.
4. shock-damping structure according to claim 2, is characterized in that, described first spring and described second spring are Compress Spring.
5. shock-damping structure according to claim 4, is characterized in that, when described spring assembly and described Inertial Measurement Unit complete assembling, described first spring and described second spring are in compression set state.
6. shock-damping structure according to claim 5, is characterized in that, described first spring and described second spring-compressed deformation degree and described aircraft motor speed are in the course of the work inverse correlation.
7. shock-damping structure according to claim 1, is characterized in that, also comprises:
Damping body, be arranged between described Inertial Measurement Unit and described framed structure, comprise the first damping body and the second damping body, wherein the first damping body is arranged between the top end face of Inertial Measurement Unit and the top of framed structure, and the two ends of the first damping body are connected with the top end face of Inertial Measurement Unit, the top of framed structure respectively, second damping body is arranged between the bottom end face of Inertial Measurement Unit and the bottom of framed structure, and the two ends of the second damping body are connected with the bottom end face of Inertial Measurement Unit, the bottom of framed structure respectively.
8. 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 1-7.
9. an aircraft, is characterized in that, comprising: the shock-damping structure according to any one of claim 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520442872.3U CN205186539U (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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| CN201520442872.3U CN205186539U (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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| CN205186539U true CN205186539U (en) | 2016-04-27 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908961A (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 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908961A (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 |
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| C14 | Grant of patent or utility model | ||
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| 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: 20160427 Pledgee: Silicon Valley Bank Co., Ltd. Pledgor: GUANGZHOU FEIMI ELECTRONIC TECHNOLOGY CO., LTD. Registration number: 2018310000008 |