CN205168877U - Multiaxis aircraft takes precautions against earthquakes - Google Patents
Multiaxis aircraft takes precautions against earthquakes Download PDFInfo
- Publication number
- CN205168877U CN205168877U CN201520861654.3U CN201520861654U CN205168877U CN 205168877 U CN205168877 U CN 205168877U CN 201520861654 U CN201520861654 U CN 201520861654U CN 205168877 U CN205168877 U CN 205168877U
- Authority
- CN
- China
- Prior art keywords
- urceolus
- inner core
- axis aircraft
- flexible connector
- aircraft according
- 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.)
- Expired - Fee Related
Links
Landscapes
- Vibration Dampers (AREA)
Abstract
The utility model provides a multiaxis aircraft takes precautions against earthquakes, including the main frame, the main frame includes base frame, a plurality of bracing piece and loading board, and the base frame is connected through a plurality of bracing pieces with the loading board, wherein, a plurality of bracing pieces and the base adopts damping structure spare to connect. Damping structure spare includes inner tube, urceolus and flexible connectors, and interior barrel casing is established in the urceolus, and the outer wall of inner tube passes through flexible connectors with the inner wall of urceolus and is connected. The utility model discloses adopt damping structure spare to be connected between the base of well main support frame and the bracing piece, the vibrations that produce when touching ground with the base frame are eliminated, have guaranteed that the loading board of bracing piece on and does not produce vibrations, will influence the principal element elimination of connecting the reliability between control module and the control unit of installation on the main support, have promoted the connection reliability, and then have improved the flight stability of multiaxis aircraft.
Description
Technical field
The utility model relates to Multi-axis aircraft technical field, especially shockproof Multi-axis aircraft.
Background technology
Because Multi-axis aircraft structure is simple, and the control of Multi-axis aircraft is also comparatively simple, and its airworthiness is all more stable, makes Multi-axis aircraft be easy to miniaturization, and application popularization speed in recent years improves greatly.Now common Multi-axis aircraft is two axles, three axles, four axles, five axles, six axles and eight axle aircraft, also has the Multi-axis aircraft of more multiaxis, but the most commonly four-axle aircraft.
Multi-axis aircraft comprises hardware and software two parts substantially, and hardware comprises mainframe, one end of connection pole is connected on mainframe, and the other end connects actuating unit.Mainframe is provided with a lot of control modules and control structure, control module is all connected by electric wire with corresponding control structure, and also have connection between each control module, therefore, the reliability of connection is the precondition that Multi-axis aircraft airworthiness is stable.And one of key factor affecting connection reliability is exactly the vibrations of mainframe, especially to take off or in descent, the vibrations that the collision between the mainframe of Multi-axis aircraft and ground brings are inevitable.And the mainframe of existing Multi-axis aircraft is and is rigidly connected, the vibrations that the collision between mainframe and ground brings can not be avoided.
Utility model content
The purpose of this utility model is to provide shockproof Multi-axis aircraft, and the mainframe solving existing Multi-axis aircraft is and is rigidly connected, and can not avoid the vibrations that the collision between mainframe and ground brings, and then affects the technical matters of flight stability of Multi-axis aircraft.
In order to achieve the above object, the utility model provides following technical scheme:
Shockproof Multi-axis aircraft, comprises mainframe, and described mainframe comprises pony sill, multiple strut bar and loading plate, and described pony sill is connected by multiple strut bar with loading plate, and wherein, described multiple strut bar and described base adopt damping structure part to be connected.
Further, described damping structure part comprises inner core, urceolus and Flexible Connector, and described inner core is set in urceolus, and the outer wall of described inner core is connected by described Flexible Connector with the inwall of described urceolus.
Further, described elasticity connection is evenly distributed between described inner core and urceolus.
Further, described strut bar is fixedly connected with described inner core, and described pony sill is fixedly connected with described urceolus.
Further, described inner core is radially offered at least one pair of mutually vertical and fixed orifice run through, described Flexible Connector is worn and is penetrated in described fixed orifice, and the two ends of described Flexible Connector are fixedly connected with the inwall of described urceolus respectively.
Further, the lateral wall of the bottom of described inner core adopts Flexible Connector to be connected with the madial wall of the bottom of described urceolus.
Particularly, described Flexible Connector adopts spring.
Further, described pony sill comprises at least two bottom bars and elastic link, and described bottom bar is connected with strut bar, and the two ends of described elastic link connect from different bottom bars respectively.
Damping structure part is adopted to be connected between pony sill with strut bar in the main support of shockproof Multi-axis aircraft of the present utility model, the vibrations produced when pony sill being touched ground are eliminated, ensure that strut bar and on loading plate do not produce vibrations, eliminate affecting the principal element of connection reliability between control module and function unit that main support is installed, improve connection reliability, and then improve the flight stability of Multi-axis aircraft.
Further, connected by elastic link at each bottom bar of the pony sill of main support, the vibrations that horizontal direction produces are eliminated, more improves the flight stability of Multi-axis aircraft.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the construction profile schematic diagram of the shockproof Multi-axis aircraft of the utility model, omits fulcrum and engine installation in figure;
Fig. 2 be in Fig. 1 A to structural representation;
Fig. 3 is the partial enlarged drawing at B place in Fig. 2;
Fig. 4 is the structural representation of the inner core of a kind of detailed description of the invention of the damping structure part of the shockproof Multi-axis aircraft of the utility model;
Fig. 5 be the shockproof Multi-axis aircraft of the utility model look up structural representation, omit fulcrum and engine installation in figure.
Detailed description of the invention
Below in conjunction with accompanying drawing of the present utility model, be clearly and completely described the technical solution of the utility model, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
According to shown in Fig. 1 to Fig. 4, shockproof Multi-axis aircraft of the present utility model is described, comprise mainframe 1, described mainframe 1 comprises pony sill 11, multiple strut bar 12 and loading plate 13, described pony sill 11 is connected by multiple strut bar 12 with loading plate 13, wherein, described multiple strut bar 12 adopts damping structure part 3 to be connected with described pony sill 11.
The part of damping structure described in the utility model can adopt conventional damping structure part of the prior art, also the damping structure part of designed, designed can be adopted, the utility model gives a kind of damping structure part of designed, designed, as shown in Figure 3, described damping structure part 3 comprises inner core 31, urceolus 32 and Flexible Connector 33, described inner core 31 is set in urceolus 32, and the outer wall of described inner core 31 is connected by described Flexible Connector 33 with the inwall of described urceolus 32.Described Flexible Connector 33 specifically can adopt spring, by being weldingly fixed on respectively at the two ends of spring on the outer wall of inner core 31 and the inwall of urceolus 32, is connected by inner core 31 with urceolus 32.Preferably, described elasticity connects 3 and is evenly distributed between described inner core 31 and urceolus 32, ensures symmetry, increases stability.Be connected by being welded and fixed with described inner core 31 by described strut bar 12, described pony sill 11 is welded and fixed with described urceolus 32 and is connected, and is connected by strut bar 12 with pony sill 11.
The utility model additionally provides a kind of structure of preferred inner core 31, as shown in Figure 4, described inner core 31 is radially offered a pair orthogonal fixed orifice 311 running through inner core 31, described Flexible Connector 33 passes and is fixed in described fixed orifice 311, and the two ends of described Flexible Connector 33 are welded and fixed with the inwall of described urceolus 31 respectively and are connected.Add the Joint strenght of Flexible Connector 33 and inner core 31 and urceolus 32.Orthogonal fixed orifice 311 can repeat to offer vertically, and the axis of often pair of fixed orifice is without the need to overlap.
Preferred technical scheme is that, on the basis of the structure of above-mentioned damping structure part 3, the lateral wall in the bottom of described inner core 31 also adopts Flexible Connector 33 to be connected with the madial wall of the bottom of described urceolus 32 further.From vertically eliminating vibrations.
Above-mentioned Flexible Connector 33 preferably adopts spring.
In the utility model, additionally provide a kind of structure of pony sill 11, described pony sill 11 comprises at least two bottom bars 111 and elastic link 112, described bottom bar 111 is connected with strut bar 12 (adopting above-mentioned connection mode to connect), and the two ends of described elastic link 112 connect from different bottom bars 111 respectively.Concrete described pony sill 11 comprises two bottom bars 111 and two elastic links 112, and described two bottom bars 111 be arranged in parallel, is connected respectively (adopting above-mentioned connection mode to connect) with strut bar 12 as shown in Figure 5, forms mainframe.Two elastic links 112 also be arranged in parallel, and its two ends are connected with two bottom bars 111 be arranged in parallel respectively.The two ends of flexible connecting rod 112 adopt the collar 113 to be connected on two bottom bars 111 respectively, connect reliable.The collar 113 can be one-body molded with flexible connecting rod 112, and other modes also can be adopted to be connected on flexible connecting rod 112, e.g., and colligation etc.
The above; be only detailed description of the invention of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; change can be expected easily or replace, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should described be as the criterion with the protection domain of claim.
Claims (8)
1. shockproof Multi-axis aircraft, comprises mainframe, it is characterized in that, described mainframe comprises pony sill, multiple strut bar and loading plate, described pony sill is connected by multiple strut bar with loading plate, and wherein, described multiple strut bar and described base adopt damping structure part to be connected.
2. shockproof Multi-axis aircraft according to claim 1, it is characterized in that, described damping structure part comprises inner core, urceolus and Flexible Connector, and described inner core is set in urceolus, and the outer wall of described inner core is connected by described Flexible Connector with the inwall of described urceolus.
3. shockproof Multi-axis aircraft according to claim 2, it is characterized in that, described inner core is radially offered at least one pair of mutually vertical and fixed orifice run through, described Flexible Connector is worn and is penetrated in described fixed orifice, and the two ends of described Flexible Connector are fixedly connected with the inwall of described urceolus respectively.
4. shockproof Multi-axis aircraft according to claim 2, is characterized in that, the lateral wall of the bottom of described inner core adopts Flexible Connector to be connected with the madial wall of the bottom of described urceolus.
5. the shockproof Multi-axis aircraft according to any one of claim 2 to 4, is characterized in that, described elasticity connection is evenly distributed between described inner core and urceolus.
6. the shockproof Multi-axis aircraft according to any one of claim 2 to 4, it is characterized in that, described strut bar is fixedly connected with described inner core, described pony sill is fixedly connected with described urceolus.
7. the shockproof Multi-axis aircraft according to any one of claim 2 to 4, is characterized in that, described Flexible Connector adopts spring.
8. shockproof Multi-axis aircraft according to any one of claim 1 to 4, is characterized in that, described pony sill comprises at least two bottom bars and elastic link, and described bottom bar is connected with strut bar, and the two ends of described elastic link connect from different bottom bars respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520861654.3U CN205168877U (en) | 2015-10-30 | 2015-10-30 | Multiaxis aircraft takes precautions against earthquakes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520861654.3U CN205168877U (en) | 2015-10-30 | 2015-10-30 | Multiaxis aircraft takes precautions against earthquakes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205168877U true CN205168877U (en) | 2016-04-20 |
Family
ID=55732894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520861654.3U Expired - Fee Related CN205168877U (en) | 2015-10-30 | 2015-10-30 | Multiaxis aircraft takes precautions against earthquakes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205168877U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109056758A (en) * | 2018-09-19 | 2018-12-21 | 田浩强 | A kind of slope of highway supporting construction and early warning system |
| WO2019061386A1 (en) * | 2017-09-30 | 2019-04-04 | 林燕凤 | Unmanned aerial vehicle fall protection device |
| CN113232835A (en) * | 2021-06-16 | 2021-08-10 | 郭聪 | Multifunctional pesticide sprays unmanned aerial vehicle equipment |
-
2015
- 2015-10-30 CN CN201520861654.3U patent/CN205168877U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019061386A1 (en) * | 2017-09-30 | 2019-04-04 | 林燕凤 | Unmanned aerial vehicle fall protection device |
| CN109056758A (en) * | 2018-09-19 | 2018-12-21 | 田浩强 | A kind of slope of highway supporting construction and early warning system |
| CN113232835A (en) * | 2021-06-16 | 2021-08-10 | 郭聪 | Multifunctional pesticide sprays unmanned aerial vehicle equipment |
| CN113232835B (en) * | 2021-06-16 | 2023-12-01 | 义乌市农业开发有限公司 | Multifunctional pesticide spraying unmanned aerial vehicle equipment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205168877U (en) | Multiaxis aircraft takes precautions against earthquakes | |
| CN205116401U (en) | Semi -rigid power consumption node of bamboo timber structure rapid Assembly formula | |
| CN205875868U (en) | Antidetonation type transmission tower | |
| CN204652843U (en) | Equipment mounting frame and communication cabinet | |
| CN209567075U (en) | A kind of plant protection drone | |
| CN105625219A (en) | Mounting method for buckling type road guardrail | |
| CN204163390U (en) | Scaffold connecting joint structure | |
| CN204488406U (en) | Axle suspension system | |
| CN204983217U (en) | Building antidetonation device | |
| CN204237469U (en) | The connection structure of tower machine driver's cab platform and upper bracket | |
| CN206350252U (en) | Embedded Touch Screen antidetonation fixed structure | |
| CN207279942U (en) | Air conditioner mounting bracket | |
| CN205207533U (en) | Limited harmonious mass damper damping device in horizontal space | |
| CN204826289U (en) | A constructional steel component for in ground | |
| CN202586651U (en) | Novel elevator motor coupling assembly | |
| CN204257552U (en) | The splicing structure of release | |
| CN205153015U (en) | Excavator and energy storage ware fixed structure thereof | |
| CN109025331A (en) | Combinable disk button prefabricated panel support construction | |
| CN204819454U (en) | Pipe fitting rack | |
| CN205298970U (en) | Installation frame in air supporting membrane equipment | |
| CN205100372U (en) | Fixed structure is supported on activity board house roof | |
| CN104018725B (en) | A kind of terminal pole electric pole and push rod attachment structure | |
| CN205381312U (en) | Car sub vehicle frame connection structure assembly | |
| CN210511562U (en) | Protection mechanism of landscape lamp pole | |
| CN203289757U (en) | Container-type data central machine cabinet |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160420 Termination date: 20161030 |