CN204802095U - 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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- CN204802095U CN204802095U CN201520440076.6U CN201520440076U CN204802095U CN 204802095 U CN204802095 U CN 204802095U CN 201520440076 U CN201520440076 U CN 201520440076U CN 204802095 U CN204802095 U CN 204802095U
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- inertial measurement
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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: the subassembly is stablized to the spring, set up in inertia measuring unit with between the frame construction of aircraft, so that inertia measuring unit remains stable in the trend of the state of predetermineeing, the damping body, set up in inertia measuring unit with between the frame construction of aircraft, in order to absorb the aircraft to the vibration energy of inertia measuring unit output. 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 stabilizing component, between the framed structure being arranged at described Inertial Measurement Unit and described aircraft, keeps the trend being stable at preset state to make described Inertial Measurement Unit;
Damping body, between the framed structure being arranged at described Inertial Measurement Unit and described aircraft, to absorb the vibration energy that described aircraft exports to described Inertial Measurement Unit.
Optionally, described spring stabilizing component and described damping body are arranged at the same side of described Inertial Measurement Unit.
Optionally, described spring stabilizing component comprises:
Compress Spring, residing for described Compress Spring and described Inertial Measurement Unit, plane orthogonal is arranged, and the vertical projection of described Compress Spring is positioned at the center of the bottom end face of described Inertial Measurement Unit;
Extension spring group, described extension spring group comprises multiple extension spring arranged around described Compress Spring circumference, and the top of each extension spring is connected with the bottom end face of described Inertial Measurement Unit, the bottom of each extension spring is connected with the bottom of described framed structure.
Optionally, when described shock-damping structure and described Inertial Measurement Unit complete assembling, the spring that described Compress Spring is in compression set state, described extension spring group is all in tensile deformation state.
Optionally, when described Inertial Measurement Unit is the schistose texture of rectangular in cross-section, described extension spring group comprises four springs, 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, described damping body is positioned at the hollow area in the middle of described Compress Spring.
Optionally, also comprise:
Fixed support; Wherein, described Compress Spring is all connected by the bottom of described fixed support with described framework architecture with each extension spring in described extension spring group.
Optionally, described damping body is silica gel block.
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, IMU, by arranging spring stabilizing component between Inertial Measurement Unit and the framed structure of aircraft, can be fixed on preset state by the disclosure, or in vibrations process, keep trending towards the trend of this preset state, thus it is in stable condition to realize IMU.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 stabilizing component be made up of these springs can be reduced, promote assembly precision and stablizing effect.Further, 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.In addition, by arranging damping body, can spring stabilizing component the state of IMU is carried out stable while, effectively can absorb the vibration energy that IMU is subject to, thus avoid IMU to be damaged.
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 perspective view of the another kind of shock-damping structure according to an exemplary embodiment.
Fig. 5 is the perspective view 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:
Spring stabilizing component 3, between the framed structure 1 being arranged at IMU2 and described aircraft, keeps the trend being stable at preset state to make IMU2;
Damping body 4, between the framed structure 1 being arranged at IMU2 and described aircraft, to absorb the vibration energy that described aircraft exports to IMU2.
In the present embodiment, spring stabilizing component 3 and damping body 4 can be arranged at the same side of IMU2, such as in fig. 2 all between the bottom end face and the bottom of framed structure 1 of IMU2, thus contribute to reducing the space hold of shock-damping structure in framed structure 1.Due to aircraft to own vol and weight very responsive, thus by reduce space hold, can avoid impacting and pressure the spatial division in framed structure 1, structural allocation, prevent the working flight affecting aircraft.Certainly, spring stabilizing component 3 and damping body 4 also can adopt other set-up modes, and the disclosure does not limit this.
1, spring stabilizing component 3
IMU2 can be fixed on preset state (being such as positioned at the position shown in Fig. 2) by spring stabilizing component 3, or in vibrations process, keeps the trend trending towards this preset state, thus it is in stable condition to realize IMU.Spring stabilizing component 3 is actually and is made up of multiple spring, because the 26S Proteasome Structure and Function of the spring of same way manufacture is stable, difference is little, can reduces the build-up tolerance of the spring stabilizing component 3 be made up of these springs, promote assembly precision and stablizing effect.Further, 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 IMU2.
As an exemplary embodiment, as shown in Figure 3, spring stabilizing component 3 can comprise:
Compress Spring 31, this Compress Spring 31 is arranged with plane orthogonal residing for IMU2, and the vertical projection of this Compress Spring 31 is positioned at the center of the bottom end face of IMU2; Wherein, when shock-damping structure and IMU2 complete assembling, Compress Spring 31 is in compression set state.
Extension spring group 32, this extension spring group 32 comprises multiple extension spring arranged around Compress Spring 31 circumference, and the top of each extension spring is connected with the bottom end face of IMU2, the bottom of each extension spring is connected with the bottom of described framed structure 1; Wherein, when shock-damping structure and IMU2 complete assembling, the spring in extension spring group 32 is all in tensile deformation state.
In this embodiment, after Compress Spring 31 compression downwards, form power upwards, and extension spring group 32 is after surrounding stretching, form the power that surrounding is downward, IMU2 is made to maintain a metastable state and position, even and if aircraft causes the vibrations of IMU2, also can guarantee that IMU2 keeps returning the trend of this state and position at any time.
Ratio as shown in Figure 4, when IMU2 is the schistose texture of rectangular in cross-section, extension spring group 32 comprises four extension springs, wherein one end of each extension spring is connected to the summit place of IMU2, the other end is connected to framed structure 1, thus pass through the stretching at four summits place, and after coordinating with Compress Spring 31, carry out in stable condition to IMU2.Wherein, one end that each extension spring is connected with framed structure 1, the projection of in the vertical direction is positioned at beyond the view field of IMU2, and residing for each extension spring and IMU2, the angle of plane can be 45 °.
2, damping body
In embodiment of the present disclosure, by arranging damping body 4, can the state of spring stabilizing component 3 couples of IMU2 carry out stable while, effectively can absorb the vibration energy that IMU2 is subject to, thus avoid IMU2 to be damaged.Wherein, damping body 4 or can have arbitrarily the materials such as elastomeric plastic cement by other and makes for silica gel.
In the embodiment shown in Fig. 3-4, damping body 4 can be arranged in the hollow area in the middle of Compress Spring 31, thus avoid additional space and take, contribute to the space planning of framed structure 1 inside of aircraft, prevent the working flight affecting aircraft.
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 Compress Spring 31 in shock-damping structure and extension spring group 32, the bottom of framed structure 1 can arrange supporting connection structure, such as when the spring end in Compress Spring 31 and extension spring group 32 is hook-shaped, the bottom of framed structure 1 can pre-set corresponding hole, thus realizes 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 5, shock-damping structure can also comprise:
Fixed support 5; Wherein, Compress Spring 31 is all connected with the bottom of framework architecture 1 by this fixed support 5 with each extension spring in extension spring group 32.
In this embodiment, fixed support 5 in the form of sheets, thus directly can be affixed to the bottom of framed structure 1 by fixed support 5, can complete the installation of " the inertia measurement structure with shock-absorbing function ", and make respective outer side edges and improvement without the need to framed structure 1.
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:
Spring stabilizing component, between the framed structure being arranged at described Inertial Measurement Unit and described aircraft, keeps the trend being stable at preset state to make described Inertial Measurement Unit;
Damping body, between the framed structure being arranged at described Inertial Measurement Unit and described aircraft, to absorb the vibration energy that described aircraft exports to described Inertial Measurement Unit.
2. shock-damping structure according to claim 1, is characterized in that, described spring stabilizing component and described damping body are arranged at the same side of described Inertial Measurement Unit.
3. shock-damping structure according to claim 1, is characterized in that, described spring stabilizing component comprises:
Compress Spring, residing for described Compress Spring and described Inertial Measurement Unit, plane orthogonal is arranged, and the vertical projection of described Compress Spring is positioned at the center of the bottom end face of described Inertial Measurement Unit;
Extension spring group, described extension spring group comprises multiple extension spring arranged around described Compress Spring circumference, and the top of each extension spring is connected with the bottom end face of described Inertial Measurement Unit, the bottom of each extension spring is connected with the bottom of described framed structure.
4. shock-damping structure according to claim 3, it is characterized in that, when described shock-damping structure and described Inertial Measurement Unit complete assembling, the spring that described Compress Spring is in compression set state, described extension spring group is all in tensile deformation state.
5. shock-damping structure according to claim 3, it is characterized in that, when described Inertial Measurement Unit is the schistose texture of rectangular in cross-section, described extension spring group comprises four springs, 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.
6. shock-damping structure according to claim 3, is characterized in that, described damping body is positioned at the hollow area in the middle of described Compress Spring.
7. shock-damping structure according to claim 3, is characterized in that, also comprises:
Fixed support; Wherein, described Compress Spring is all connected by the bottom of described fixed support with described framework architecture with each extension spring in described extension spring group.
8. shock-damping structure according to claim 1, is characterized in that, described damping body is silica gel block.
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 |
|---|---|---|---|
| CN201520440076.6U CN204802095U (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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| Application Number | Priority Date | Filing Date | Title |
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| CN201520440076.6U CN204802095U (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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| CN204802095U true CN204802095U (en) | 2015-11-25 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104973258A (en) * | 2015-06-24 | 2015-10-14 | 广州飞米电子科技有限公司 | Vibration absorbing structure, inertia measurement structure with vibration absorbing function and aircraft |
| CN107512400A (en) * | 2017-09-04 | 2017-12-26 | 江西洪都航空工业集团有限责任公司 | Certain type tandem two-seater aircraft Full Authority Digital control device distribution mounting structure |
| CN108168547A (en) * | 2018-02-01 | 2018-06-15 | 深圳市固胜智能科技有限公司 | The mounting structure and holder of Inertial Measurement Unit |
-
2015
- 2015-06-24 CN CN201520440076.6U patent/CN204802095U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104973258A (en) * | 2015-06-24 | 2015-10-14 | 广州飞米电子科技有限公司 | Vibration absorbing structure, inertia measurement structure with vibration absorbing function and aircraft |
| CN107512400A (en) * | 2017-09-04 | 2017-12-26 | 江西洪都航空工业集团有限责任公司 | Certain type tandem two-seater aircraft Full Authority Digital control device distribution mounting structure |
| CN108168547A (en) * | 2018-02-01 | 2018-06-15 | 深圳市固胜智能科技有限公司 | The mounting structure and holder of Inertial Measurement Unit |
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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: 20151125 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 |