CN206525051U - System for flight control computer - Google Patents
System for flight control computer Download PDFInfo
- Publication number
- CN206525051U CN206525051U CN201720161471.XU CN201720161471U CN206525051U CN 206525051 U CN206525051 U CN 206525051U CN 201720161471 U CN201720161471 U CN 201720161471U CN 206525051 U CN206525051 U CN 206525051U
- Authority
- CN
- China
- Prior art keywords
- circuit board
- flight control
- shock
- main bodies
- control system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
This disclosure relates to a kind of system for flight control computer, including flying control circuit board and flying the sensor circuit board (3) that control circuit board is electrically connected with this, wherein, the winged control circuit board includes upper plate (5) and lower plate (6), and damping device (2) is installed between the upper plate (5) and lower plate (6), the damping device (2) includes the shock-absorbing main bodies (21) for being used to connect the sensor circuit board (3), and the upper and lower surface protrusion of the shock-absorbing main bodies (21) is provided with multiple elastic buffer portions (1).By buffering of the elastic buffer portion for impulsive force, the impulsive force being transmitted on sensor circuit board is effectively reduced, it is ensured that the accuracy of the measurement data of each sensor, so as to ensure that the stable traveling of unmanned plane.
Description
Technical field
This disclosure relates to unmanned plane field, in particular it relates to a kind of system for flight control computer.
Background technology
System for flight control computer be unmanned plane complete to take off, airflight, tasks carrying and the whole flight of recovery etc. of giving an encore
The core system of process.Flight control system generally comprises sensor, airborne computer and servo start equipment three parts, realization
Function mainly has unmanned plane attitude stabilization and control, the management of unmanned plane task device and emergency flight control three major types.Unmanned plane takes off
In normal flight operations, because the reason such as self power source or external pneumatic disturbance can make airframe produce different frequency
Vibrations, and flight control system be arranged on unmanned plane on also vibrate therewith, cause the sensor measurement datas such as accelerometer, gyroscope
Distortion, further result in that unmanned plane theoretical flight pose that flight control computer calculates and practical flight pose produce it is larger partially
Difference.Fly control when this deviation exceedes permissible value to will be unable to accurately control unmanned plane, cause the danger generation such as unmanned plane air crash, so
Damping for the sensor in flight control system is vital link.
Utility model content
The purpose of the disclosure is to provide a kind of system for flight control computer, and the flight control system, which can be effectively reduced, is transmitted to sensing
Jerk power on device circuit board.
To achieve these goals, the disclosure provides a kind of system for flight control computer, including flies control circuit board and fly with this
Control the sensor circuit board of circuit board electrical connection, the winged control circuit board includes upper plate and lower plate, and the upper plate and lower plate it
Between damping device is installed, the damping device includes being used to connect the shock-absorbing main bodies of the sensor circuit board, the shock-absorbing main bodies
Upper and lower surface protrusion be provided with multiple elastic buffer portions.
Alternatively, the center of the lower surface of the shock-absorbing main bodies opens up fluted, and the sensor circuit board is installed
Into the groove, the multiple elastic buffer portion surrounds the groove arranged for interval.
Alternatively, the shock-absorbing main bodies are rectangular, and four corners of the upper and lower surface of the rectangle, which correspond, to be provided with
The elastic buffer portion.
Alternatively, the upper surface of the shock-absorbing main bodies offers the through hole for extending to the groove.
Alternatively, the elastic buffer portion is sponge, and the sponge is adhered to the upper and lower surface of the shock-absorbing main bodies.
Alternatively, the damping device also includes damping box, and the shock-absorbing main bodies, which are installed, to be fixed in the damping box, institute
Damping box is stated to be connected between the upper plate and the lower plate.
Alternatively, the damping box includes the upper lid and the box body on this below lid being connected with each other, multiple bullets
Property buffer part is connected respectively to the roof of the upper lid and the bottom wall of the box body.
Alternatively, offered on the side wall of the box body for connecting the sensor circuit board and the winged control circuit board
The logical wire casing that wire is passed through.
Alternatively, the wire is soft arranging wire.
Alternatively, the periphery of the box body be formed with multiple slots, the periphery of the upper lid be formed with it is the multiple
The corresponding projection of slot.
The beneficial effect of the disclosure is：By the way that sensor circuit board is installed on damping device, elastic buffer portion is utilized
For the buffering of impulsive force, the impulsive force being transmitted on sensor circuit board is efficiently reduced, it is ensured that the measurement number of sensor
According to accurate, so that the control output of flight control system is accurate, it is ensured that the stabilized flight of unmanned plane.
Other feature and advantage of the disclosure will be described in detail in subsequent embodiment part.
Brief description of the drawings
Accompanying drawing is, for providing further understanding of the disclosure, and to constitute a part for specification, with following tool
Body embodiment is used to explain the disclosure together, but does not constitute limitation of this disclosure.In the accompanying drawings：
Fig. 1 is the cut-away view for the damping device that the disclosure is provided.
Fig. 2 is Fig. 1 upward view.
Fig. 3 is Fig. 1 top view.
Fig. 4 is the damping device and the scheme of installation of winged control circuit version that the disclosure is provided.
Fig. 5 is Fig. 4 side view.
Description of reference numerals
The damping device of 1 elastic buffer portion 2
The damping box of 21 shock-absorbing main bodies 22
The box body of lid 222 on 221
3 sensor circuit boards 4 lead to wire casing
The lower plate of 5 upper plate 6
The through hole of 7 wire 211
Embodiment
It is described in detail below in conjunction with accompanying drawing embodiment of this disclosure.It should be appreciated that this place is retouched
The embodiment stated is merely to illustrate and explained the disclosure, is not limited to the disclosure.
In the disclosure, in the case where not making opposite explanation, the noun of locality used such as " inside and outside " is to be directed to corresponding component
Profile for, on " upper and lower " top as shown in accompanying drawing drawing is, under bottom is.
In order that obtaining flight control system ensure that biography when unmanned plane takes off with normal flight operations by impact endurance test shock
The normal work of sensor, it is to avoid occur flight failure.As shown in Figures 1 to 5, the disclosure provides a kind of system for flight control computer,
The flight control system includes flying control circuit board and flies the sensor circuit board 3 that control circuit board is electrically connected with this, wherein, fly control circuit board
Damping device 2 is installed including upper plate 5 and lower plate 6, and between the upper plate 5 and lower plate 6, the damping device 2 includes being used to connect
The shock-absorbing main bodies 21 of sensor circuit board 3 are connect, the upper and lower surface protrusion of the shock-absorbing main bodies 21 is provided with multiple elastic buffer portions 1.
So, when airframe is produced vibrations by the reason such as self power source or external pneumatic disturbance, impulsive force meeting
It is directly transferred on damping device 2, by the buffering in elastic buffer portion 1, can be effectively reduced and be transmitted to sensor circuit board 3
On impulsive force, thereby it is ensured that the normal work of the sensor such as accelerometer, gyroscope so that the measurement number of sensor
According to accurate and effective, the normal operation of flight control system further ensures the flight stability of unmanned plane, it is to avoid the hair of flight failure
It is raw.
Also, the damping device 2 is placed between the upper plate 5 and lower plate 6 for flying control circuit board, takes full advantage of structure empty
Between, so as to save the space of whole flight control system so that overall structure spatial optimization.
In order that obtaining sensor circuit board 3 reaches preferable damping effect, in the present embodiment, such as Fig. 1 and Fig. 2 institutes
Show, the center of the lower surface of shock-absorbing main bodies 21 opens up fluted, and sensor circuit board 3 is installed in groove, multiple elasticity
Buffer part 1 surrounds groove arranged for interval.That is, sensor circuit board 3 is inserted into groove, and positioned at the centre bit of shock-absorbing main bodies 21
Put, while elastic buffer portion 1 is arranged around sensor circuit board 3.So, sensor circuit board 3, shock-absorbing main bodies 21 and multiple
The center of gravity in elastic buffer portion 1 is conllinear, and the damping effect of damping device 2 is played to greatest extent, substantially reduces and is transmitted to sensing
Impulsive force on device circuit board 3, practicality is stronger, and then make it that the output of flight control system is accurate, it is ensured that the stabilization of unmanned plane flies
OK.Wherein, the position of groove can be the lower surface as shown in Figure 2 for being located at shock-absorbing main bodies 21, can also table disposed thereon
Face.
Specifically, as shown in figure 1, shock-absorbing main bodies 21 are rectangular, a pair of four corners one of the upper and lower surface of the rectangle
Elastic buffer portion 1 should be installed.I.e., in the present embodiment, eight elastic buffer portions 1 are provided with altogether, and upper and lower surface difference is equal
It is even to be arranged at intervals with four, and the arrangement in the elastic buffer portion 1 of upper and lower surface is corresponding.So, sensed during vibrations
Device circuit board 3 is each to uniform force so that the vibration displacement of sensor circuit board 3 is smaller, even tends to static state.Need
It is noted that the shape of shock-absorbing main bodies 21 can be designed according to the actual requirements, except above-mentioned rectangle, it can also be waited to be circular
His shape, and elastic buffer portion 1 arrangement can be according to shock-absorbing main bodies 21 shape and the installation position of sensor circuit board 3
Meter is installed, as long as disclosure satisfy that the center of gravity of three is conllinear.
Sensor circuit board 3 mentioned above, which coordinates, to be inserted into the groove of shock-absorbing main bodies 21, therefore, for convenience dismounting and
Sensor circuit board 3 is changed, respective slot is arranged on lower surface, and in the present embodiment, the upper surface of shock-absorbing main bodies 21 is opened up
There is the through hole 211 for extending to groove.So, after needing to dismantle and changing sensor circuit board 3, it can be passed through by instrument logical
Hole 211 applies pressure to sensor circuit board 3, sensor circuit board 3 is separated from groove, convenient disassembly is rationally distributed.
In the present embodiment, elastic buffer portion 1 can be sponge, and the sponge is adhered in shock-absorbing main bodies 21.Sponge sheet
Body has higher elasticity, can play a part of preferable bumper and absorbing shock.Sponge can be glued in shock-absorbing main bodies 21 simultaneously,
The carrying of sensor circuit board 3 is reduced, and it is easy for installation.
It is affected by vibrations in order to further reduce sensor circuit board 3, in the present embodiment, as shown in figure 4, subtracting
Shaking device 2 also includes damping box 22, and shock-absorbing main bodies 21, which are installed, to be fixed in damping box 22, and damping box 22 is connected to upper plate 5 with
Between plate 6.Sensor circuit board 3 is encapsulated in damping box 22 with shock-absorbing main bodies 21.That is, damping box 22 is by sensor circuit
Plate 3 is isolated with extraneous focus so that sensor circuit board 3 is influenceed further to reduce by external shock.In addition, subtract
Shake box 22 can also play the position-limiting action to shock-absorbing main bodies 21, and shock-absorbing main bodies 21 are arranged in damping box 22, equivalent to
Protection shell is set up in outside, can play a part of protection for shock-absorbing main bodies 21 and sensor circuit board 3.
In addition, damping box 22 directly can be installed between upper plate 5 and lower plate 6 by damping device 2, it is easy to the installation in later stage
And dismounting.
Further, damping box 22 includes the upper lid 221 being connected with each other and the box body 222 on this below lid 221, many
Individual elastic buffer portion 1 is connected respectively to the roof of lid 221 and the bottom wall of box body 222.That is, positioned at the upper surface of shock-absorbing main bodies 21
Elastic buffer portion 1 be connected to the roof of lid 221, correspondingly, the elastic buffer portion 1 positioned at lower surface is then connected to box body
222 bottom wall.The form of connection can be bonding, so so that shock-absorbing main bodies 21 form as one with damping box 22, damping master
Body 21 is in relatively free state in damping box 22.The elasticity that sensor circuit board 3 passes through the upper and lower surface of shock-absorbing main bodies 21
The buffering of buffer part 1, reaches preferable damping effect so that measurement data is accurate, it is ensured that the normal work of flight control system.
For the normal connection for ensureing sensor circuit board 3 with flying control circuit board, in the present embodiment, box body 222
Offered on the wall of side for connection sensor circuit board 3 and fly the logical wire casing 4 that the wire 7 of control circuit board is passed through.The one end of wire 7 is connected
Sensor circuit board 3, the other end passes through logical wire casing 4 to be connected on winged control circuit board, so as to ensure the normal of sensor circuit board 3
Work.
Further, in the present embodiment, wire 7 can be soft arranging wire, so, can arbitrarily select according to the actual requirements
Wire count and spacing are selected, on line is more facilitated, reduction uses space, production cost is reduced.
For the ease of the installation and removal of shock-absorbing main bodies 21, in the present embodiment, box body 222 and upper lid 221 are removable
The type of attachment unloaded.Wherein, the periphery of box body 222 could be formed be formed with multiple slots, the periphery of upper lid 221 with it is multiple
The corresponding projection of slot.The raised cooperation with slot, upper lid 221 is installed on box body 222, later stage convenient disassembly is conducive to
The replacing of shock-absorbing main bodies 21.
To sum up, the disclosure provides a kind of system for flight control computer, and sensor circuit board is transmitted to by damping device reduction
On impulsive force, it is ensured that the accuracy of the measurement data of each sensor so that the control output of flight control system is accurate, it is ensured that nothing
The flight of man-machine normal table.
The preferred embodiment of the disclosure is described in detail above in association with accompanying drawing, still, the disclosure is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the disclosure, a variety of letters can be carried out with technical scheme of this disclosure
Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that each particular technique feature described in above-mentioned embodiment, in not lance
In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the disclosure to it is various can
The combination of energy no longer separately illustrates.
In addition, can also be combined between a variety of embodiments of the disclosure, as long as it is without prejudice to originally
Disclosed thought, it should equally be considered as disclosure disclosure of that.
Claims (10)
1. a kind of system for flight control computer, including fly control circuit board and fly the sensor circuit board that control circuit board is electrically connected with this
(3), it is characterised in that the winged control circuit board includes upper plate (5) and lower plate (6), and the upper plate (5) and the lower plate
(6) damping device (2) is installed, the damping device (2) includes the damping master for being used to connect the sensor circuit board (3) between
Body (21), the upper and lower surface protrusion of the shock-absorbing main bodies (21) is provided with multiple elastic buffer portions (1).
2. flight control system according to claim 1, it is characterised in that the centre bit of the lower surface of the shock-absorbing main bodies (21)
Put to form fluted, the sensor circuit board (3) is installed in the groove, the multiple elastic buffer portion (1) surrounds institute
State groove arranged for interval.
3. flight control system according to claim 2, it is characterised in that the shock-absorbing main bodies (21) are rectangular, the rectangle
Four corners of upper and lower surface correspond and are provided with the elastic buffer portion (1).
4. flight control system according to claim 2, it is characterised in that the upper surface of the shock-absorbing main bodies (21), which is offered, prolongs
Reach the through hole (211) of the groove.
5. the flight control system according to any one in claim 1-4, it is characterised in that the elastic buffer portion (1) is
Sponge, the sponge is adhered in the shock-absorbing main bodies (21).
6. flight control system according to claim 1, it is characterised in that the damping device (2) also includes damping box (22),
The shock-absorbing main bodies (21), which are installed, to be fixed in the damping box (22), the damping box (22) be connected to the upper plate (5) and
Between the lower plate (6).
7. flight control system according to claim 6, it is characterised in that the damping box (22) includes the upper lid being connected with each other
(221) box body (222) and on this covered below (221), multiple elastic buffer portions (1) are connected respectively to the upper lid
(221) roof and the bottom wall of the box body (222).
8. flight control system according to claim 7, it is characterised in that offered on the side wall of the box body (222) for connecting
Lead to the logical wire casing (4) that the sensor circuit board (3) and the winged wire (7) for controlling circuit board are passed through.
9. flight control system according to claim 8, it is characterised in that the wire (7) is soft arranging wire.
10. flight control system according to claim 7, it is characterised in that the periphery of the box body (222) is formed with multiple insert
Projection corresponding with the multiple slot is formed with groove, the periphery of the upper lid (221).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720161471.XU CN206525051U (en) | 2017-02-22 | 2017-02-22 | System for flight control computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720161471.XU CN206525051U (en) | 2017-02-22 | 2017-02-22 | System for flight control computer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206525051U true CN206525051U (en) | 2017-09-26 |
Family
ID=59892070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720161471.XU Active CN206525051U (en) | 2017-02-22 | 2017-02-22 | System for flight control computer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206525051U (en) |
Cited By (1)
| 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 | Novel IMU shock attenuation device |
-
2017
- 2017-02-22 CN CN201720161471.XU patent/CN206525051U/en active Active
Cited By (1)
| 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 | Novel IMU shock attenuation device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6502283B2 (en) | Micro inertia measurement device | |
| JP2016117485A (en) | Unmanned aircraft inertia measurement module | |
| CN106871895B (en) | A kind of inertial measuring unit and unmanned vehicle | |
| CN104142150A (en) | Integrated small-size laser gyroscope inertia measurement device | |
| CN209684001U (en) | Mounting structure, flight controller and unmanned plane for Inertial Measurement Unit | |
| CN207487690U (en) | A kind of unmanned aircraft inertia measuring module | |
| CN204666157U (en) | The inertial measurement cluster of vibration isolation in pillar suspension type | |
| CN206813334U (en) | The sensor damping device and unmanned plane of a kind of unmanned plane | |
| CN206446801U (en) | Suitable for the special winged control shock-damping structure of multi-rotor unmanned aerial vehicle | |
| CN206525051U (en) | System for flight control computer | |
| CN106896823A (en) | The control device and unmanned vehicle of unmanned vehicle | |
| CN110654557B (en) | Unmanned aerial vehicle's shock-absorbing structure | |
| CN205333080U (en) | High precision fiber optic is used to lead system at prompt antithetical couplet | |
| CN108694881A (en) | A kind of experiment device for teaching for dynamic vibration absorber performance demonstration | |
| CN209262572U (en) | A kind of inertia measuring module and unmanned vehicle | |
| CN208953964U (en) | A kind of flight control assemblies and unmanned vehicle | |
| CN207466983U (en) | Motion-sensing device assembly and unmanned plane | |
| CN205014987U (en) | Inertial measurement device | |
| CN209414509U (en) | A kind of IMU damping device | |
| CN207864526U (en) | Novel IMU shock attenuation device | |
| CN205510609U (en) | Flight control with shock -absorbing function | |
| CN206038016U (en) | Inertia measurement assembly reaches unmanned vehicles who contains it | |
| CN212259316U (en) | Pickup device shock-absorbing structure and pickup equipment | |
| CN208351334U (en) | A kind of control device and unmanned vehicle for unmanned vehicle | |
| CN205961355U (en) | A damping device and projecting apparatus for multimedia devices |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |