CN206670647U - A kind of inertia measurement damping device and aircraft - Google Patents
A kind of inertia measurement damping device and aircraft Download PDFInfo
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- CN206670647U CN206670647U CN201720338505.8U CN201720338505U CN206670647U CN 206670647 U CN206670647 U CN 206670647U CN 201720338505 U CN201720338505 U CN 201720338505U CN 206670647 U CN206670647 U CN 206670647U
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- inertia measurement
- damping device
- metal plate
- counter weight
- weight metal
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Abstract
The utility model discloses a kind of inertia measurement damping device and aircraft, and the inertia measurement damping device includes：Inertia measurement circuit board, it which is provided with multiple sensors；Insulating trip, positioned at the lower section of inertia measurement circuit board；Counter weight metal plate, positioned at the lower section of insulating trip；Damping sponge, positioned at the lower section of Counter weight metal plate；Upper lid and lower cover, upper lid fastens to form receiving space with lower cover, for accommodating inertia measurement circuit board, insulating trip, Counter weight metal plate and damping sponge.The aircraft includes：Fuselage main body, fuselage main body be provided with can relative to its rotation in order to horn component before the right side packed up, left front horn component, it is right after horn component and left back horn component, center is provided with inside fuselage main body, storage battery component inside center, Power conversion board, the first pcb board, the second pcb board and above-mentioned inertia measurement damping device, Power conversion board is provided with outside center with battery component to be connected.The utility model is simple in construction, good damping effect.
Description
Technical field
It the utility model is related to the related technical field of kind Inertial Measurement Unit (IMU), more particularly to a kind of inertia
Measure damping device and aircraft.
Background technology
Inertial Measurement Unit IMU (Inertial measurementunit) belongs to strapdown inertia, generally comprises two
Acceleration transducer and three velocity sensors (gyro), acceleration transducer are used for experiencing acceleration of the aircraft relative to ground vertical line
Component is spent, velocity sensor is used for experiencing the angle information of aircraft.
IMU is used in the equipment for needing to carry out motion control mostly, and on automobile and robot, being also used in needs to use posture
Carry out the inertial navigation set of the occasion, such as submarine, aircraft, guided missile and spacecraft of accurate displacement reckoning.
Because IMU is mounted in moving equipment, therefore the damping effect of its installation place is particularly important.
Utility model content
Main purpose of the present utility model is to propose a kind of inertia measurement damping device, it is intended to is IMU dampings, improves and survey
Accuracy of measurement.
To achieve the above object, the utility model proposes a kind of inertia measurement damping device, it is characterised in that including：
Inertia measurement circuit board, it which is provided with multiple sensors；
Insulating trip, positioned at the lower section of the inertia measurement circuit board；
Counter weight metal plate, positioned at the lower section of the insulating trip；
Damping sponge, positioned at the lower section of the Counter weight metal plate；
Upper lid and lower cover, the upper lid fasten to form receiving space with lower cover, for accommodate the inertia measurement circuit board,
The insulating trip, the Counter weight metal plate and the damping sponge.
Alternatively, the edge of the Counter weight metal plate is provided with rib, and the rib protrudes from the upper of the Counter weight metal plate
Surface and lower surface.
Alternatively, the insulating trip is located at the rib and the upper surface of the Counter weight metal plate is surrounded in space.
Alternatively, the damping sponge is at least partially disposed at the rib and the lower surface of the Counter weight metal plate surrounds sky
In.
Alternatively, the inertia measurement circuit board is provided with the first fixed via；The insulating trip is provided with and described the
The second corresponding fixed via of one fixed via；The Counter weight metal plate is provided with corresponding with second fixed via the
Three fixed vias.
Alternatively, the inertia measurement circuit board is provided with two sets of acceleration transducers and two set of three axis angular rate sensing
Device.
Alternatively, the Counter weight metal plate is made of copper.
Alternatively, at least one side wall of the upper lid is provided with the first groove, the side wall of the lower cover be provided with it is described
The second corresponding groove of first groove, form is formed after being fastened for the lid on described and lower cover.
Alternatively, the side wall of the upper lid is provided with the diving board extended under phase, and the diving board, which is provided with, fastens through hole；Under described
It is raised that the side wall of lid is provided with the fastening to match with the fastening through hole.
To achieve the above object, the utility model also provides a kind of aircraft, it is characterised in that including：Fuselage main body, institute
State fuselage main body be provided with can relative to its rotation in order to horn component before the right side packed up, left front horn component, it is right after horn
Component and left back horn component, the fuselage main body inside are provided with center, battery component, the center are stored inside the center
Outside is provided with Power conversion board, the first pcb board, the second pcb board and inertia measurement damping device described in any of the above-described, described
Power conversion board is connected with the battery component.
The utility model proposes inertia measurement damping device and aircraft, simple in construction, good damping effect.
Brief description of the drawings
Fig. 1 is the structural representation before the assembling of the inertia measurement damping device of the utility model embodiment；
Fig. 2 is the structural representation after the assembling of inertia measurement damping device as shown in Figure 1；
Fig. 3 is the schematic diagram for the center that inertia measurement damping device as shown in Figure 1 is arranged on aircraft；
Realization, functional characteristics and the advantage of the utility model purpose will be described further referring to the drawings in conjunction with the embodiments.
Embodiment
It should be appreciated that specific embodiment described herein is not used to limit this only to explain the utility model
Utility model.
As shown in Figure 1 and Figure 2, the utility model proposes a kind of inertia measurement damping device, including upper lid 50 and lower cover 60 with
And inertia measurement circuit board 10, insulating trip 20, Counter weight metal plate 30 and damping sponge 40 between upper lid 50 and lower cover 60.
Wherein, inertia measurement circuit board 10 is provided with multiple sensors 12；Set in the present embodiment on inertia measurement circuit board
There are two sets of acceleration transducers and two set of three axis angular rate sensor.Usually, a set of acceleration transducer contains three lists
The accelerometer of axle, a set of three axis angular rate sensor include the gyro of three single shafts；Accelerometer detection object is sat in carrier
The acceleration signal of independent three axles of mark system, gyro detect angular velocity signal of the carrier relative to navigational coordinate system, measure object
Angular speed and acceleration in three dimensions, and calculate with this posture of object.The inertia measurement circuit board 10 is also set
There is output end, the output end is connected by winding displacement with flying vehicles control unit.
Insulating trip 20 is located at the lower section of inertia measurement circuit board 10；Insulating trip 20 can be formed directly into the form of coating
The lower surface of inertia measurement circuit board 10.
Counter weight metal plate 30 is located at the lower section of insulating trip 20；Counter weight metal plate can be made of copper, naturally it is also possible to be it
His metal, the utility model are not limited to this；When it is implemented, rib can be provided with the edge of Counter weight metal plate 30
32, rib 32 protrudes from the upper surface and lower surface 32 of Counter weight metal plate, in this way, insulating trip 20 can be located at rib with matching somebody with somebody a huge sum of money
The upper surface of category plate is surrounded in space.
Damping sponge 40 is located at the lower section of Counter weight metal plate 30, if the edge of Counter weight metal plate 30 is provided with rib 32, subtracts
The lower surface that shake sponge 40 is at least partially disposed at rib and Counter weight metal plate is surrounded in space.
Upper lid 50 fastens with lower cover 60 and forms receiving space, for accommodating inertia measurement circuit board 10, insulating trip 20, counterweight
Metallic plate 30 and damping sponge 40；In addition, adhered layer at least one can be set, for the inwall with lower cover on damping sponge 40
Or Counter weight metal plate is affixed.
, can also be in order that inertia measurement circuit board 10, insulating trip 20, Counter weight metal plate 30 are preferably combined
Inertia measurement circuit board 10 is provided with least one first fixed via 11, e.g. 3 the first fixed vias 11；Insulating trip 20
It is provided with second fixed via 21 corresponding with the first fixed via 11；Counter weight metal plate 30 is provided with and the second fixed via 21
The 3rd corresponding fixed via 31.Projection can be set in the inside of upper lid 50, for sequentially passing through the inertia measurement circuit
Plate 10, insulating trip 20, Counter weight metal plate 30.
In the present embodiment, at least one side wall of upper lid 50 is provided with the first groove 53, and the side wall of lower cover 60 is provided with and the
The second corresponding groove 63 of one groove 53, the first groove 53 can be formed after upper lid fastens with lower cover with the second groove 63 and regarded
Window, the winding displacement penetrate the form.The bottom of lower cover 60 can set fixed column 62, for being fixed on the battery frame of equipment
On, in addition, the bottom of lower cover 60 directly can link together with battery frame, it is integrally formed.
The side wall of upper lid 50 is provided with the diving board 51 extended under phase, and diving board 51, which is provided with, fastens through hole 52；The side wall of lower cover 60
Provided with the fastening projection 61 to match with fastening through hole；When the fastening projection 61 of lower cover is engaged with the fastening through hole 52 of upper lid
When, upper lid 50 just snaps together with lower cover 60.In the present embodiment, diving board 51, which is arranged on, to be covered in two relative side walls,
Each side wall is at least provided with a diving board.Need, diving board 51 is not typically arranged on same side wall with the first groove 53
On.
The utility model also provides a kind of aircraft, including：Fuselage main body, the fuselage main body is provided with can be relative to it
Rotate in order to horn component before the right side packed up, left front horn component, it is right after horn component and left back horn component, the fuselage
Body interior is provided with center, and battery component is stored inside center；There is provided as shown in figure 3, also including the utility model in aircraft
Inertia measurement damping device, the inertia measurement damping device just be arranged on fuselage main body inside center 100 outside, although
Do not shown in figure, but Power conversion board, the first pcb board, the second pcb board are additionally provided with the outside of center 100, wherein, electricity
Source pinboard is connected with battery component.
The utility model proposes inertia measurement damping device and aircraft, it is simple in construction, can effectively to inertia measurement electricity
Road plate carries out damping.
It should be noted that herein, term " comprising ", "comprising" or its any other variant are intended to non-row
His property includes, so that process, method, article or device including a series of elements not only include those key elements, and
And also include the other element being not expressly set out, or also include for this process, method, article or device institute inherently
Key element.In the absence of more restrictions, the key element limited by sentence "including a ...", it is not excluded that including this
Other identical element also be present in the process of key element, method, article or device.
Preferred embodiment of the present utility model is these are only, not thereby limits the scope of the claims of the present utility model, it is every
The equivalent structure or equivalent flow conversion made using the utility model specification and accompanying drawing content, or be directly or indirectly used in
Other related technical areas, similarly it is included in scope of patent protection of the present utility model.
Claims (10)
- A kind of 1. inertia measurement damping device, it is characterised in that including：Inertia measurement circuit board, it which is provided with multiple sensors；Insulating trip, positioned at the lower section of the inertia measurement circuit board；Counter weight metal plate, positioned at the lower section of the insulating trip；Damping sponge, positioned at the lower section of the Counter weight metal plate；Upper lid and lower cover, the upper lid fasten to form receiving space with lower cover, for accommodating the inertia measurement circuit board, described Insulating trip, the Counter weight metal plate and the damping sponge.
- 2. inertia measurement damping device according to claim 1, it is characterised in that the edge of the Counter weight metal plate is provided with gear Side, the rib protrude from the upper surface and lower surface of the Counter weight metal plate.
- 3. inertia measurement damping device according to claim 2, it is characterised in that the insulating trip is located at the rib and institute The upper surface for stating Counter weight metal plate is surrounded in space.
- 4. inertia measurement damping device according to claim 2, it is characterised in that the damping sponge is at least partially disposed at institute The lower surface for stating rib and the Counter weight metal plate is surrounded in space.
- 5. inertia measurement damping device according to claim 1, it is characterised in that the inertia measurement circuit board is provided with the One fixed via；The insulating trip is provided with second fixed via corresponding with first fixed via；It is described to match somebody with somebody a huge sum of money Category plate is provided with threeth fixed via corresponding with second fixed via.
- 6. inertia measurement damping device according to claim 1, it is characterised in that the inertia measurement circuit board is provided with two Cover acceleration transducer and two set of three axis angular rate sensor.
- 7. inertia measurement damping device according to claim 1, it is characterised in that the Counter weight metal plate is made of copper.
- 8. inertia measurement damping device according to claim 1, it is characterised in that at least one side wall of the upper lid is provided with First groove, the side wall of the lower cover are provided with second groove corresponding with first groove, on described lid with Lower cover forms form after fastening.
- 9. inertia measurement damping device according to claim 1, it is characterised in that the side wall of the upper lid, which is provided with phase, to be extended Diving board, the diving board be provided with fasten through hole；It is convex that the side wall of the lower cover is provided with the fastening to match with the fastening through hole Rise.
- A kind of 10. aircraft, it is characterised in that including：Fuselage main body, the fuselage main body be provided with can relative to its rotation with Be easy to horn component before the right side packed up, left front horn component, it is right after horn component and left back horn component, in the fuselage main body Portion is provided with center, and battery component is stored inside the center, Power conversion board, the first pcb board, second are provided with outside the center Inertia measurement damping device any one of pcb board and claim 1-9, the Power conversion board and the battery component It is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720338505.8U CN206670647U (en) | 2017-04-01 | 2017-04-01 | A kind of inertia measurement damping device and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720338505.8U CN206670647U (en) | 2017-04-01 | 2017-04-01 | A kind of inertia measurement damping device and aircraft |
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| CN206670647U true CN206670647U (en) | 2017-11-24 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108105332A (en) * | 2017-12-28 | 2018-06-01 | 成都优艾维智能科技有限责任公司 | A kind of novel I MU damping devices |
| CN108190036A (en) * | 2017-12-25 | 2018-06-22 | 中航联创科技有限公司 | A kind of inertial navigation shock mitigation system of unmanned plane |
| CN108226647A (en) * | 2018-04-13 | 2018-06-29 | 南方电网科学研究院有限责任公司 | A kind of measuring device to power line access point impedance |
| CN108601281A (en) * | 2018-04-24 | 2018-09-28 | 赫星科技有限公司 | Damping device, circuit board and the flight unmanned plane for being provided with the circuit board |
| CN109612461A (en) * | 2018-12-24 | 2019-04-12 | 中国电子科技集团公司第十三研究所 | Isolation damper device and three-axis gyroscope |
| WO2019140659A1 (en) * | 2018-01-19 | 2019-07-25 | 深圳市大疆创新科技有限公司 | Anmanned aerial vehicle |
| CN111016033A (en) * | 2019-12-13 | 2020-04-17 | 武汉迈普时空导航科技有限公司 | IMU shock absorption and heat insulation device based on silica gel and preparation method |
-
2017
- 2017-04-01 CN CN201720338505.8U patent/CN206670647U/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108190036A (en) * | 2017-12-25 | 2018-06-22 | 中航联创科技有限公司 | A kind of inertial navigation shock mitigation system of unmanned plane |
| CN108105332A (en) * | 2017-12-28 | 2018-06-01 | 成都优艾维智能科技有限责任公司 | A kind of novel I MU damping devices |
| WO2019140659A1 (en) * | 2018-01-19 | 2019-07-25 | 深圳市大疆创新科技有限公司 | Anmanned aerial vehicle |
| CN110325438A (en) * | 2018-01-19 | 2019-10-11 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| CN108226647A (en) * | 2018-04-13 | 2018-06-29 | 南方电网科学研究院有限责任公司 | A kind of measuring device to power line access point impedance |
| CN108601281A (en) * | 2018-04-24 | 2018-09-28 | 赫星科技有限公司 | Damping device, circuit board and the flight unmanned plane for being provided with the circuit board |
| CN108601281B (en) * | 2018-04-24 | 2020-11-03 | 赫星科技有限公司 | A damping device, circuit board and flight unmanned aerial vehicle for unmanned aerial vehicle |
| CN109612461A (en) * | 2018-12-24 | 2019-04-12 | 中国电子科技集团公司第十三研究所 | Isolation damper device and three-axis gyroscope |
| CN109612461B (en) * | 2018-12-24 | 2020-06-19 | 中国电子科技集团公司第十三研究所 | Isolation vibration damper and triaxial gyroscope |
| CN111016033A (en) * | 2019-12-13 | 2020-04-17 | 武汉迈普时空导航科技有限公司 | IMU shock absorption and heat insulation device based on silica gel and preparation method |
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