CN206502015U - A kind of aircraft center of gravity dynamically balancing device - Google Patents
A kind of aircraft center of gravity dynamically balancing device Download PDFInfo
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- CN206502015U CN206502015U CN201720055024.6U CN201720055024U CN206502015U CN 206502015 U CN206502015 U CN 206502015U CN 201720055024 U CN201720055024 U CN 201720055024U CN 206502015 U CN206502015 U CN 206502015U
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- mobile base
- balancing device
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- gravity
- slide rail
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Abstract
The utility model proposes a kind of aircraft center of gravity dynamically balancing device, including battery, Mobile base, slide rail and leading screw, set above the Mobile base and slide rail and leading screw are set below battery, the Mobile base.Pass through the device that mass density in mobile original aircraft is larger, to reach mass centre changing that trim is brought due to mechanism kinematic, this device is installed simple, materials are less, and balancing device belongs to original place materials, bear a heavy burden less, excessive oil consumption and power consumption will not be increased, aircraft center of gravity reach or the defect moved afterwards are solved well.
Description
Technical field
The utility model belongs to aviation aircraft technical field, especially a kind of aircraft center of gravity dynamically balancing device.
Background technology
Current aviation field rises, and by this carrier of aircraft, many sophisticated equipments can be in extreme circumstances
Work, helps people to complete task, in numerous loading devices, has a class to have the equipment of motility, e.g., mechanical arm, stretches
Stock, rotating mechanism etc., can cause whole body center of gravity to change in motion, and aircraft normally flies can be by center of gravity
Change is disturbed, and which results in this class mechanism and uncoordinated, the normal flight of influence aircraft, it is difficult to practical of body.
Automatic trim is completed under conditions of driver is not involved in by automatic trim system.Automatic trim system includes
Automatic stick force trimming system and Mach trim system.1. automatic stick force trimming system：By trim amplifier and tromming tab unit
Into.Automatic pilot is defeated by the signal of main control surface steering wheel or the output signal of stick force sensor, is driven by trim amplifier
Trim steering wheel, drives trimmer or horizontal stabilizer to make stick force automatic trim.2. Mach trim system：Aircraft transonic flight
When, due to Mach number increase and aerodynamic force retrofocus, make aircraft automatically into underriding, operate the joystick and anti-manipulate now occurs
As.To overcome this danger, it is necessary to using Mach trim system.It is by mach transducer, trim computer and tromming tab
Machine is constituted.When flying speed exceedes critical Mach number, mach transducer just outputs signal to trim computer.Computer
Output order is the function of Mach number, and it drives trim steering wheel to rotate rudder face or horizontal stabilizer, is produced with compensating retrofocus
Raw nose-down pitching moment, autobalance longitudinal moment.
Both the above trim mode can all increase oil consumption or power consumption, so as to reduce endurance, this is in endurance when operation
Inherently very short unmanned plane field, is a kind of very big waste, therefore, researches and develops a kind of environmental protection, energy-conservation, succinct balancing device
It is extremely urgent.
Utility model content
In order to solve the above problems, the utility model provides a kind of aircraft center of gravity dynamically balancing device.
Concrete technical scheme is as follows：
A kind of aircraft center of gravity dynamically balancing device, including battery (1), Mobile base (2), slide rail (3) and leading screw (4), institute
State to set above Mobile base (2) and slide rail (3) and leading screw (4), the leading screw are set below battery (1), the Mobile base (2)
(4) one end connection stepper motor (7).
Preferably, the Mobile base (2) is connected with slide rail (3) by sliding block (5).
Preferably, the connected mode of the sliding block (5) and slide rail (3) is bolt connection.
Preferably, the Mobile base (2) is connected with leading screw (4) by contiguous block (6).
Preferably, the connected mode of the contiguous block (6) and leading screw (4) is bolt connection.
Preferably, the battery (1) is fixedly connected with Mobile base (2).
Preferably, the slide rail (3) is fixed on cabin bottom.
Preferably, the stepper motor (7) is connected by control panel with aircraft control system.
Relative to prior art, a kind of aircraft center of gravity dynamically balancing device described in the utility model has following excellent
Gesture：
The utility model proposes a kind of aircraft center of gravity dynamically balancing device, it is close by quality in mobile original aircraft
The larger device of degree, to reach mass centre changing that trim is brought due to mechanism kinematic, this device installs simple, and materials are less,
And balancing device belongs to original place materials, bears a heavy burden less, will not increase excessive oil consumption and power consumption, flight is solved well and is thought highly of
The defect that the heart moves forward or moved afterwards.
Brief description of the drawings
Fig. 1 be the utility model proposes a kind of aircraft center of gravity dynamically balancing device stereogram；
Fig. 2 be the utility model proposes a kind of aircraft center of gravity dynamically balancing device upward view；
Fig. 3 is the connection figure of slide rail and sliding block；
Fig. 4 state balancing devices aroused in interest of attaching most importance to are placed in installation drawing in aircraft.
Description of reference numerals：
The sliding block of 1 battery, 2 Mobile base, 3 slide rail, 4 leading screw 5
The stepper motor of 6 contiguous block 7
Embodiment
The technical solution of the utility model is further described below in conjunction with embodiment.It should be appreciated that herein
The embodiment of description only to explain the utility model, is not used to limit the utility model.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " on ", " under ",
The orientation or position relationship of the instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of description the utility model and simplifies description, rather than indicate
Or imply that the device or element of meaning must have specific side, with specific azimuth configuration and operation, therefore it is not intended that
To limitation of the present utility model.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in description of the present utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be directly connected to, can also be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, on being understood by concrete condition
State concrete meaning of the term in the utility model.
Describe the utility model in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Fig. 1 and Fig. 2 be the utility model proposes a kind of aircraft center of gravity dynamically balancing device schematic diagram, including battery
(1) battery (1) is set above, Mobile base (2), slide rail (3) and leading screw (4), the Mobile base (2), and Mobile base (2) is groove
Type, battery (1) is fixed on Mobile base (2) by bail, and slide rail (3) and leading screw (4) are set below the Mobile base (2),
Mobile base (2) is connected with slide rail (3) by sliding block (5), and sliding block (5) is fixed on Mobile base (2) below, sliding block (5) and slide rail (3)
Connected mode be bolt connection (as shown in Figure 3), Mobile base (2) is connected with leading screw (4) by contiguous block (6), contiguous block
(6) it is fixed on Mobile base (2) below, the connected mode of contiguous block (6) and leading screw (4) is bolt connection, one end in leading screw (4)
Stepper motor (7) is connected to, stepper motor (7) passes through control panel and aircraft control system by motor seat supports, stepper motor (7)
It is connected.
A kind of aircraft center of gravity dynamically balancing device that the utility model is proposed, the weight of trim is not restricted to battery
(1) combination or the larger object of any mass density of fuel tank or fuel tank and battery, are can also be, such as the goods of transport
Thing etc., in line with the principle of aircraft load is not increased, can select required loaded article in any one aircraft.
Fig. 4 attaches most importance to the installation drawing that state balancing device aroused in interest is placed in aircraft, and two parallel sliding tracks (3) are fixed on cabin bottom
Portion, can be fixed with resin, can also be screwed, fixed form is not limited.In the intermediate arrangement one of two slide rails (3)
Leading screw (4), leading screw (4) is parallel with slide rail (3), and Mobile base (2), Mobile base (2) are set above slide rail (3) and leading screw (4)
Self-contained battery (1) above, one end of leading screw (4) is connected with stepper motor (7), the rotating speed of stepper motor (7) and turning for leading screw (4)
Fast consistent, stepper motor (7) is connected by control panel with aircraft control system, if the center of gravity reach or rear shifting of aircraft, aircraft
Control system adjusts the rotating speed of stepper motor (7), and then the rotating speed of adjusting screw (4) by control panel, makes Mobile base (2) backward
Mobile or forward movement, reaches the purpose of regulation aircraft center of gravity.
The present invention is by the larger device of mobile initial quality density, to reach center of gravity that trim is brought due to mechanism kinematic
Change, implement process as follows：
Mechanism is made up of two slide rails (3), a leading screw (4) and a stepper motor (7).Slide rail (3) is fixed on cabin
Bottom, is fixed by resin or screw, and slide rail (3) is equipped with Mobile base (2) bottom, and sliding block (5) mutually blocks with slide rail (3)
It is embedding, and sliding block (5) can reduce energy loss, in Mobile base (2) bottom, two cunnings on slide rail (3) with minimum resistance slip
Block (5) center, having has screw thread on a contiguous block (6) being connected with leading screw (4), contiguous block (6) inwall, screw thread and leading screw (4)
Screw thread is meshed, while leading screw (4) is rotated, and contiguous block (6) and the movement fixed with contiguous block (6) can be driven by screw thread
Seat (2) does translational motion together, and the connected mode of sliding block (5) and contiguous block (6) and Mobile base (2) is fastenedly connected for bolt.Silk
The front end (disembarking head more nearby) of thick stick (4) is connected with stepper motor (7), the rotating speed of stepper motor (7) and the rotating speed of leading screw (4)
It is consistent, in addition, the signal Access Control plate of stepper motor (7), reaches control signal and enters stepper motor (7) control rotating speed,
Leading screw (4) changes into rotating speed the movement of Mobile base (2), and the larger object of the mass densityes such as battery is put into after Mobile base (2),
The disturbance that trim motion is brought can just be realized.
In summary, the utility model proposes a kind of aircraft center of gravity dynamically balancing device, pass through mobile original flight
The larger device of mass density in device, to reach mass centre changing that trim is brought due to mechanism kinematic, this device installs simple,
Materials are less, and balancing device belongs to original place materials, bears a heavy burden less, will not increase excessive oil consumption and power consumption, solve well
Aircraft center of gravity reach or the defect moved afterwards.
Embodiment above is preferred embodiment of the present utility model, not thereby limits of the present utility model special
Sharp protection domain.Those skilled in the art belonging to any the utility model, it is disclosed in the utility model not departing from
The equivalent structure and the conversion of equivalent step done on the premise of spirit and scope to content of the present utility model each falls within this reality
Within new claimed the scope of the claims.
Claims (8)
1. a kind of aircraft center of gravity dynamically balancing device, it is characterised in that including battery (1), Mobile base (2), slide rail (3) and silk
Set above thick stick (4), the Mobile base (2) and slide rail (3) and leading screw (4) be set below battery (1), the Mobile base (2),
One end connection stepper motor (7) of the leading screw (4).
2. a kind of aircraft center of gravity dynamically balancing device according to claim 1, it is characterised in that the Mobile base (2)
It is connected with slide rail (3) by sliding block (5).
3. a kind of aircraft center of gravity dynamically balancing device according to claim 2, it is characterised in that the sliding block (5) with
The connected mode of slide rail (3) is bolt connection.
4. a kind of aircraft center of gravity dynamically balancing device according to claim 1, it is characterised in that the Mobile base (2)
It is connected with leading screw (4) by contiguous block (6).
5. a kind of aircraft center of gravity dynamically balancing device according to claim 4, it is characterised in that the contiguous block (6)
Connected mode with leading screw (4) is bolt connection.
6. a kind of aircraft center of gravity dynamically balancing device according to claim 1, it is characterised in that the battery (1) with
Mobile base (2) is fixedly connected.
7. a kind of aircraft center of gravity dynamically balancing device according to claim 1, it is characterised in that the slide rail (3) is solid
It is scheduled on cabin bottom.
8. a kind of aircraft center of gravity dynamically balancing device according to claim 1, it is characterised in that the stepper motor
(7) it is connected by control panel with aircraft control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720055024.6U CN206502015U (en) | 2017-01-16 | 2017-01-16 | A kind of aircraft center of gravity dynamically balancing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720055024.6U CN206502015U (en) | 2017-01-16 | 2017-01-16 | A kind of aircraft center of gravity dynamically balancing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206502015U true CN206502015U (en) | 2017-09-19 |
Family
ID=59839215
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720055024.6U Active CN206502015U (en) | 2017-01-16 | 2017-01-16 | A kind of aircraft center of gravity dynamically balancing device |
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| CN (1) | CN206502015U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828886A (en) * | 2017-01-16 | 2017-06-13 | 北京猎鹰无人机科技有限公司 | A kind of aircraft center of gravity dynamically balancing device |
| CN107985601A (en) * | 2017-10-11 | 2018-05-04 | 佛山汇众森泰科技有限公司 | A kind of agricultural uses aerial spraying pesticide device |
| TWI640456B (en) * | 2017-10-18 | 2018-11-11 | 國立虎尾科技大學 | Machine tool system carried by a copter drone |
| CN109186863A (en) * | 2018-09-20 | 2019-01-11 | 兰州空间技术物理研究所 | Spacecraft mass characteristic adjustment mechanism |
| CN109724815A (en) * | 2017-10-31 | 2019-05-07 | 北京精密机电控制设备研究所 | A kind of quasi- loading system of the crank based on rope drive-anti-operating torque of pressure spring type |
| CN110733652A (en) * | 2019-11-01 | 2020-01-31 | 北京德知航创科技有限责任公司 | gravity type split oil tank for small unmanned aerial vehicle |
| CN113570306A (en) * | 2021-07-21 | 2021-10-29 | 天之成科技(上海)有限公司 | Wisdom logistics system |
-
2017
- 2017-01-16 CN CN201720055024.6U patent/CN206502015U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828886A (en) * | 2017-01-16 | 2017-06-13 | 北京猎鹰无人机科技有限公司 | A kind of aircraft center of gravity dynamically balancing device |
| CN107985601A (en) * | 2017-10-11 | 2018-05-04 | 佛山汇众森泰科技有限公司 | A kind of agricultural uses aerial spraying pesticide device |
| TWI640456B (en) * | 2017-10-18 | 2018-11-11 | 國立虎尾科技大學 | Machine tool system carried by a copter drone |
| CN109724815A (en) * | 2017-10-31 | 2019-05-07 | 北京精密机电控制设备研究所 | A kind of quasi- loading system of the crank based on rope drive-anti-operating torque of pressure spring type |
| CN109186863A (en) * | 2018-09-20 | 2019-01-11 | 兰州空间技术物理研究所 | Spacecraft mass characteristic adjustment mechanism |
| CN110733652A (en) * | 2019-11-01 | 2020-01-31 | 北京德知航创科技有限责任公司 | gravity type split oil tank for small unmanned aerial vehicle |
| CN113570306A (en) * | 2021-07-21 | 2021-10-29 | 天之成科技(上海)有限公司 | Wisdom logistics system |
| CN113570306B (en) * | 2021-07-21 | 2023-11-28 | 天之成科技(上海)有限公司 | Wisdom logistics system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200820 Address after: No.4 factory building, Fuyang industrial square, Fuyuan Road, Chengyang street, Xiangcheng economic and Technological Development Zone, Suzhou City, Jiangsu Province Patentee after: Aerospace Zhongxing (Jiangsu) Technology Co., Ltd Address before: Room 1003-1, building 7, No. 98, lianshihu West Road, Mentougou District, Beijing 100039 Patentee before: BEIJING FALCON UAV TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211228 Address after: 102407 466, block D, Beijing fund town building, Fangshan District, Beijing Patentee after: Aerospace Zhongxing (Beijing) Technology Co.,Ltd. Address before: 215137 plant 4, Fuyang industrial square, Fuyuan Road, Chengyang street, Xiangcheng economic and Technological Development Zone, Suzhou City, Jiangsu Province Patentee before: Aerospace Zhongxing (Jiangsu) Technology Co., Ltd |