CN104787298A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN104787298A CN104787298A CN201510162607.4A CN201510162607A CN104787298A CN 104787298 A CN104787298 A CN 104787298A CN 201510162607 A CN201510162607 A CN 201510162607A CN 104787298 A CN104787298 A CN 104787298A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- strut member
- sensing component
- diapire
- attaching parts
- 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.)
- Granted
Links
- 230000000903 blocking effect Effects 0.000 claims description 41
- 238000013016 damping Methods 0.000 claims description 19
- 230000035939 shock Effects 0.000 claims description 18
- 239000006096 absorbing agent Substances 0.000 claims description 17
- 239000011229 interlayer Substances 0.000 claims description 17
- 238000005259 measurement Methods 0.000 claims description 9
- 230000000712 assembly Effects 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 7
- 239000000306 component Substances 0.000 description 33
- 239000006260 foam Substances 0.000 description 13
- 239000000463 material Substances 0.000 description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 3
- 239000000084 colloidal system Substances 0.000 description 3
- 239000000741 silica gel Substances 0.000 description 3
- 229910002027 silica gel Inorganic materials 0.000 description 3
- 229920002379 silicone rubber Polymers 0.000 description 3
- 239000004945 silicone rubber Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 239000013536 elastomeric material Substances 0.000 description 2
- 230000008447 perception Effects 0.000 description 2
- 239000012858 resilient material Substances 0.000 description 2
- 239000005060 rubber Substances 0.000 description 2
- 229920002943 EPDM rubber Polymers 0.000 description 1
- 229920005830 Polyurethane Foam Polymers 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- HIHIPCDUFKZOSL-UHFFFAOYSA-N ethenyl(methyl)silicon Chemical compound C[Si]C=C HIHIPCDUFKZOSL-UHFFFAOYSA-N 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- -1 methyl phenyl vinyl Chemical group 0.000 description 1
- 150000002825 nitriles Chemical class 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Abstract
An aircraft comprises an aircraft body as well as a sensing assembly and a support piece which are arranged in the aircraft body, wherein the aircraft body comprises a main shell, the main shell comprises a bottom wall and side walls connected with the bottom wall, and accommodating space is defined by the side walls and the bottom wall jointly; the sensing assembly and the support piece are accommodated in the accommodating space, the support piece is connected onto the bottom wall, the sensing assembly is arranged on the support piece, and a gap is formed between the sensing assembly and each side wall. According to the aircraft, the sensing assembly is arranged on the bottom wall of the aircraft body by the aid of the support piece, and the gap is reserved between the sensing assembly and each side wall of the aircraft body, so that the vibration which is borne by the sensing assembly and is parallel to the direction of the bottom wall can be effectively reduced or eliminated.
Description
Technical field
The present invention relates to aircraft field, particularly relating to a kind of aircraft for having sensing component.
Background technology
Sensing component, as Inertial Measurement Unit (Inertial Measurement Unit, IMU), is the critical elements of aircraft, for the flight attitude of perception aircraft, orientation and other environmental information.Described sensing component is generally directly fixed on the body shell of aircraft by existing aircraft, but, because aircraft and/or can meet with air-flow and produce vibrations because of the rotation of motor, screw propeller in flight course, this vibrations can be passed to described sensing component by described fuselage special body size, thus affect the perceived accuracy of described sensing component, the execution of the normal tasks of the described aircraft of further impact, severe patient then can cause the damage of described sensing component.
Summary of the invention
In view of this, be necessary to provide a kind of aircraft that effectively can reduce the vibrations that sensing component suffers.
A kind of aircraft, comprise fuselage and the sensing component that is arranged in described fuselage and strut member, described fuselage comprises main casing.The sidewall that described main casing comprises diapire and is connected with described diapire, described sidewall and described diapire surround receiving space jointly.Described sensing component and strut member are contained in described receiving space, and described strut member is connected on described diapire, and described sensing component to be arranged on described strut member and and to have gap between described sidewall.
Further, described aircraft also comprises shock absorber part, and described shock absorber part is arranged between described sensing component and described strut member.
Further, described shock absorber part comprises damping interlayer, described damping interlayer, the side plate that described strut member comprises top board and is connected with described top board, and described top board comprises the end face towards described sensing component, and described damping interlayer is arranged on described end face.
Further, described sensing component comprises attaching parts, described sensing component is connected on described strut member by described attaching parts, and described shock absorber part comprises the first cushion blocking, and described first cushion blocking to be sheathed on corresponding described attaching parts and to be arranged between described sensing component and described strut member.
Further, described sensing component comprises attaching parts, described sensing component is connected on described strut member by described attaching parts, described shock absorber part comprises the second cushion blocking corresponding to described attaching parts, and the described attaching parts of the sheathed correspondence of described second cushion blocking is arranged at described sensing component and deviates from the side of described strut member on the surface.
Further, described sensing component comprises adapter plate and is fixed on the sensing element on described adapter plate, and described adapter plate is connected with described strut member.
Further, described sensing element is Inertial Measurement Unit.
Further, damper element is provided with in described Inertial Measurement Unit.
Further, described diapire offers the first connecting bore, described strut member offers the second connecting bore corresponding to described first connecting bore, be interconnected with described coordinating of second connecting bore by described first connecting bore between described strut member with described diapire.
Further, described aircraft is the rotor craft with rotor assemblies, and described fuselage comprises multiple arm housings, and described arm housing is arranged at around described main casing, for supporting the rotor assemblies of described aircraft.
Relative to prior art, described aircraft, by the diapire adopting strut member described sensing component to be arranged at fuselage makes the sidewall of described sensing component and fuselage keep gap, can effectively reduce or eliminate the vibrations being parallel to described diapire direction that described sensing component is subject to.
Accompanying drawing explanation
Fig. 1 is the three-dimensional exploded view of the aircraft of embodiment of the present invention.
Fig. 2 is another angular views of the aircraft of Fig. 1.
Fig. 3 and Fig. 4 is the assembling schematic diagram of the aircraft of Fig. 1.
Main element nomenclature
| Aircraft | 100 |
| Fuselage | 10 |
| Main casing | 11 |
| Diapire | 111 |
| First connecting bore | 1111 |
| Sidewall | 112 |
| Receiving space | 113 |
| Prop up arm housing | 12 |
| Landing pad | 13 |
| Inertial Measurement Unit assembly | 20 |
| Sensing element | 21 |
| Adapter plate | 22 |
| First surface | 221 |
| Second surface | 222 |
| First through hole | 223 |
| Strut member | 23 |
| Top board | 231 |
| End face | 2311 |
| Joint pin | 2312 |
| Internal thread hole | 2312a |
| Side plate | 232 |
| Connecting strap | 233 |
| Second connecting bore | 2331 |
| Shock absorber part | 24 |
| Damping interlayer | 241 |
| First cushion blocking | 242 |
| Second through hole | 2421 |
| Second cushion blocking | 243 |
| Third through-hole | 2431 |
| Attaching parts | 25 |
| Bar portion | 251 |
| Cap portion | 252 |
| Rotor assemblies | 30 |
| Colloid | 40 |
Following detailed description of the invention will further illustrate the present invention in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Refer to Fig. 1 and Fig. 2, the aircraft 100 described in embodiment of the present invention comprises fuselage 10, sensing component 20, strut member 23 and shock absorber part 24.
Described fuselage 10 is the load bearing component of described aircraft 100, described fuselage 10 outside face and/or inside are for carrying the functional module of described aircraft 100, and described functional module can include but not limited to described Inertial Measurement Unit (not shown), image acquiring module (not shown), rotor assemblies 30, height sensor (not shown), temperature sensor (not shown) etc.
Described fuselage 10 comprises main casing 11, arm housing 12 and landing pad 13.The structure that described main casing 11 and described arm housing 12 all adopt upper and lower two parts mutually to fasten, only shows the latter half of described main casing 11 and described arm housing 12 in figure.In present embodiment, described main casing 11 and described arm housing 12 are formed in one structure, be appreciated that, in other implementations, described main casing 11 can adopt removably to be interconnected with described arm housing 12, such as, be threaded, be connected together, weld, rivet, glue together connection etc.
The sidewall 112 that described main casing 11 comprises diapire 111 and is connected with described diapire.Described diapire 111 is for connecting and carrying described sensing component 20.Described diapire 111 and the X of system of axes, the plane parallel at Y-axis place in figure.Described diapire 111 offers the first connecting bore 1111 for connecting described sensing component 20.Described sidewall 112 is arranged around described diapire 111, and described sidewall 112 surrounds one for accommodating the receiving space 113 of described sensing component 20 jointly with described diapire 111.
Described arm housing 12 is for supporting described rotor assemblies 30.In present embodiment, described aircraft 100 is quadrotor, and therefore the quantity of a described arm housing 12 is four.Be appreciated that, according to different demand, the quantity of described arm housing 12 can do different changes according to the difference of the type of described aircraft 100, such as, six, eight, 12 etc., even, when described aircraft 100 is non-rotor craft, described arm housing 12 also can omit.
Described landing pad 13 is for supporting described aircraft 100 when described aircraft 100 lands.In present embodiment, the quantity of described landing pad 13 is two, and landing pad described in each is roughly " U " shape.
Described sensing component 20 comprises sensing element 21 and adapter plate 22.Described sensing element 21 is the core component of described sensing component 20, can comprise acceleration pick-up, gyroscope (figure does not indicate) and/or or other sensors for aircraft ambient parameters described in perception in it.In present embodiment, described sensing element 21 is Inertial Measurement Unit.Described sensing element 21 ground connection that is electrically connected is arranged on described adapter plate 22.Described adapter plate 22 is for being electrically connected described sensing component with outer member (not shown).Described adapter plate 22 comprises first surface 221 and the second surface 222 opposing with described first surface 221, and described sensing element 21 is arranged on described first surface 221.Described adapter plate 22 offers multiple the first through hole 223 running through described first surface 221 and described second surface 222.In present embodiment, the quantity of described first through hole 223 is four.
Described strut member 23 is for being supported in the described diapire 111 of described fuselage 10 by described sensing component 20.The side plate 232 that described strut member 23 comprises top board 231 and is connected with described top board 231.Described top board 231 comprises an end face 2311 towards described adapter plate 22, described end face 2311 is provided with multiple joint pin 2312 corresponding to described first through hole 223.Described joint pin 2312 is convexly equipped on described end face 2311.Joint pin 2312 described in each offers an internal thread hole 2312a, and the axis of described internal thread hole 2312a is approximately perpendicular to described end face 2311.In present embodiment, joint pin 2312 described in each is roughly in hollow cylindrical.Be appreciated that hollow oval column, hollow prism shape etc. that joint pin 2312 described in each also can be, and the shape of multiple described joint pin 2312 can be the same or different.Described strut member 23 also can be made with elastomeric material, to reach the effect of bumper and absorbing shock, now can save shock absorber part 24.Certainly also when strut member 23 is elastomeric material, can still use shock absorber part 24, coordinate damping by multiple shock-damping structure.
Described side plate 232 roughly falls in the side that described end face 2311 is connected to described top board 231.Side plate 232 described in each arranges a connecting strap 233 away from one end of described top board 231.Described connecting strap 233 is approximately perpendicular to the outer surface that corresponding side plate 232 protrudes from corresponding side plate.Described connecting strap 233 offers the second connecting bore 2331 corresponding to described first connecting bore 1111.
Described shock absorber part 24 is for reducing or eliminating the unexpected vibrations suffered by described sensing component 20.Described shock absorber part 24 comprises damping interlayer 241, first cushion blocking 242 and the second cushion blocking 243.Described damping interlayer 241, first cushion blocking 242 and described second cushion blocking 243 adopt flexible resilient material to make, particularly, described flexible resilient material can be foam, foam, silica gel, rubber etc., and such as PU foam, EPE foam, XPE foam, EPP foam, IXPE foam, PORON foam, CR foam, EVA foam, bridge formation PE foam, SBR foam, EPDM foam, silica gel are methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosioloxane rubber, nitrile silicone rubber etc.The Material selec-tion of described damping interlayer 241, described first cushion blocking 242 and described second cushion blocking 243 is determined according to different demand, and vibration frequency and the vibration amplitude of the vibroseis such as suffered according to described aircraft 100 select suitable vibration-absorptive material.In present embodiment, the material of described damping interlayer 241 is foam, the material of described first cushion blocking 242 and described second cushion blocking 243 is silica gel.
Described damping interlayer 241, for splitting described adapter plate 22 and described strut member 23, avoids described adapter plate 22 directly to contact with described strut member 23.In present embodiment, described damping interlayer 241 is roughly in square frame-shaped.Be appreciated that the embodiment at other, described damping interlayer can be circular, square tabular, oval tabular, polygon tabular etc.In addition, described damping interlayer 241 also can be made up of multiple part be separated from each other.In present embodiment, described damping interlayer 241 is located on the described end face 2311 of described strut member 23 by colloid 40 is sticky.
Described first cushion blocking 242 and described second cushion blocking 243 are all arranged corresponding to described first through hole 223.Wherein, corresponding described first through hole 223 of the first cushion blocking 242 is arranged at second surface 222 side of described adapter plate 22, and corresponding described first through hole 223 of described second cushion blocking 243 is arranged at first surface 221 side of described adapter plate 22.First cushion blocking 242 described in each offers second through hole 2421, and described in each, the second cushion blocking 243 offers a third through-hole 2431.In present embodiment, described first cushion blocking 242 and described second cushion blocking 243 are all in hollow cylindrical, be appreciated that, the hollow that first cushion blocking 242 described in each and described second cushion blocking 243 also can be oval column, hollow prism shape etc., and the shape of multiple described first cushion blocking 242 and/or the second cushion blocking 243 can be the same or different.
Described attaching parts 25 is for being fixedly connected on described strut member 23 by described adapter plate 22.In present embodiment, described attaching parts 25 is bolt, and it comprises bar portion 251 and is positioned at the cap portion 252 of one end, described bar portion 251.Described bar portion 251 is provided with the outside thread (do not indicate) suitable with described internal thread hole 2312a, the diameter in described bar portion 251 is less than the internal diameter of described first cushion blocking 242 and described second cushion blocking 243, and the diameter in described cap portion 252 is greater than the diameter of described second cushion blocking 243.
See also Fig. 3 and Fig. 4, during assembling, described damping interlayer 241 is arranged on the described end face 2311 of described strut member 23 by described colloid 40, be connected by described first connecting bore 1111 and described second cooperatively interacting of connecting bore 2331 between described strut member 23 with described diapire 111, particularly, described strut member 23 is interconnected with described diapire 111 by first connecting bore 1111 that bolt part (not shown) can be adopted to be each passed through the second connecting bore 2331 and correspondence, described attaching parts 25 is through the third through-hole 2431 of the second corresponding cushion blocking 243, second through hole 2421 of the first through hole 223 and the first cushion blocking 242 is threaded with corresponding joint pin 2312, so that described adapter plate 22 is connected on described strut member 23, make described first cushion blocking 242 between the described joint pin of correspondence 2312 and the second surface 222 of described adapter plate 22 simultaneously, described second cushion blocking 243 is between the described cap portion 252 and the first surface 221 of described adapter plate 22 of correspondence, and described adapter plate 22 does not produce with described sidewall 112 and contacts, namely between described adapter plate and described sidewall 112, there is gap, described damping interlayer 241 is between the described end face 2311 and the second surface 222 of described adapter plate 22 of described strut member 23.
When described aircraft 100 works, described diapire 111 can not amplify the vibrations being parallel to X, Y-axis place plane, to be arranged on described diapire 111 by described strut member 23 due to described adapter plate 22 and not contact with described sidewall 112, therefore the vibrations being parallel to X, Y-axis place plane that the sensing element 21 of the sensing component 20 that can effectively reduce or eliminate on described adapter plate 22 and described adapter plate 22 suffers; Additionally by described shock absorber part 24, can reduce or eliminate the vibrations being parallel to Z-direction suffered described in described adapter plate 22, and described first cushion blocking 242 and described second cushion blocking 243 can reduce or eliminate the transmission of the vibrations that the mechanical connection between described adapter plate 22 and described strut member 23 causes.
Be appreciated that described first connecting bore 1111 is nonessential with described second connecting bore 2331, between described diapire 111 and described strut member 23, the modes such as welding, riveted joint, engaging also can be adopted to be interconnected.
Be appreciated that the quantity of described first through hole 223, described first cushion blocking 242, described second cushion blocking 243 and described joint pin 2312 can do different changes depending on actual demand.
Be appreciated that quantity and the shape of described landing pad 13 can change, even described landing pad 13 can omit, and support during using described diapire 111 as described aircraft landing.
Be understandable that, those skilled in the art also can do other change etc. and be used in design of the present invention, as long as it does not depart from technique effect of the present invention in spirit of the present invention.These changes done according to the present invention's spirit, all should be included within the present invention's scope required for protection.
Claims (10)
1. an aircraft, the sensing component that it is characterized in that comprising fuselage and be arranged in described fuselage and strut member, described fuselage comprises main casing, the sidewall that described main casing comprises diapire and is connected with described diapire, described sidewall and described diapire surround receiving space jointly, described sensing component and strut member are contained in described receiving space, and described strut member is connected on described diapire, and described sensing component to be arranged on described strut member and and to have gap between described sidewall.
2. aircraft as claimed in claim 1, it is characterized in that: also comprise shock absorber part, described shock absorber part is arranged between described sensing component and described strut member.
3. aircraft as claimed in claim 2, it is characterized in that: described shock absorber part comprises damping interlayer, the side plate that described strut member comprises top board and is connected with described top board, described top board comprises the end face towards described sensing component, and described damping interlayer is arranged on described end face.
4. aircraft as claimed in claim 2, it is characterized in that: described sensing component comprises attaching parts, described sensing component is connected on described strut member by described attaching parts, described shock absorber part comprises the first cushion blocking, and described first cushion blocking to be sheathed on corresponding described attaching parts and to be arranged between described sensing component and described strut member.
5. aircraft as claimed in claim 2, it is characterized in that: described sensing component comprises attaching parts, described sensing component is connected on described strut member by described attaching parts, described shock absorber part comprises the second cushion blocking corresponding to described attaching parts, and described second cushion blocking to be sheathed on corresponding described attaching parts and to be arranged at described sensing component and deviates from the side of described strut member on the surface.
6. as the aircraft in claim 1-5 as described in any one, it is characterized in that: described sensing component comprises adapter plate and is fixed on the sensing element on described adapter plate, and described adapter plate is connected with described strut member.
7. aircraft as claimed in claim 6, is characterized in that: described sensing element is Inertial Measurement Unit.
8. aircraft as claimed in claim 7, is characterized in that: be provided with damper element in described Inertial Measurement Unit.
9. aircraft as claimed in claim 1, it is characterized in that: described diapire offers the first connecting bore, described strut member offers the second connecting bore corresponding to described first connecting bore, be interconnected with described coordinating of second connecting bore by described first connecting bore between described strut member with described diapire.
10. aircraft as claimed in claim 1, it is characterized in that: described aircraft is the rotor craft with rotor assemblies, described fuselage comprises multiple arm housings, and described arm housing is arranged at around described main casing, for supporting the rotor assemblies of described aircraft.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510162607.4A CN104787298B (en) | 2015-04-08 | 2015-04-08 | Aircraft |
| CN201810504362.2A CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510162607.4A CN104787298B (en) | 2015-04-08 | 2015-04-08 | Aircraft |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810504362.2A Division CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104787298A true CN104787298A (en) | 2015-07-22 |
| CN104787298B CN104787298B (en) | 2018-07-24 |
Family
ID=53552584
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510162607.4A Expired - Fee Related CN104787298B (en) | 2015-04-08 | 2015-04-08 | Aircraft |
| CN201810504362.2A Expired - Fee Related CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810504362.2A Expired - Fee Related CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN104787298B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105509741A (en) * | 2016-01-29 | 2016-04-20 | 深圳市大疆创新科技有限公司 | Flight control assembly and unmanned aerial vehicle |
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| CN202274882U (en) * | 2011-09-02 | 2012-06-13 | 深圳市大疆创新科技有限公司 | Unmanned aircraft inertia measuring module |
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| CN203105021U (en) * | 2012-09-07 | 2013-07-31 | 天津市松正电动汽车技术股份有限公司 | Damping structure for PCB pads of controller |
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2015
- 2015-04-08 CN CN201510162607.4A patent/CN104787298B/en not_active Expired - Fee Related
- 2015-04-08 CN CN201810504362.2A patent/CN108750068B/en not_active Expired - Fee Related
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| US20100037694A1 (en) * | 2008-08-15 | 2010-02-18 | Honeywell International Inc. | Snubbing system for a suspended body |
| CN102771201A (en) * | 2009-11-13 | 2012-11-07 | 鹦鹉股份有限公司 | Electronic navigation card holder for a rotor drone |
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| CN105509741A (en) * | 2016-01-29 | 2016-04-20 | 深圳市大疆创新科技有限公司 | Flight control assembly and unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108750068A (en) | 2018-11-06 |
| CN104787298B (en) | 2018-07-24 |
| CN108750068B (en) | 2021-01-05 |
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