CN105818998B - Aircraft and its indoor auxiliary locator - Google Patents
Aircraft and its indoor auxiliary locator Download PDFInfo
- Publication number
- CN105818998B CN105818998B CN201610350330.2A CN201610350330A CN105818998B CN 105818998 B CN105818998 B CN 105818998B CN 201610350330 A CN201610350330 A CN 201610350330A CN 105818998 B CN105818998 B CN 105818998B
- Authority
- CN
- China
- Prior art keywords
- probe
- aircraft
- apparatus body
- wiring board
- shock absorber
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
Abstract
The disclosure is directed to a kind of aircraft and its indoor auxiliary locators, which may include: apparatus body；Image collection assembly is fixedly arranged in the apparatus body, and the camera of described image acquisition component is located at the first default opening on the apparatus body bottom surface, to acquire external image；Ranging component, the ranging component include: the wiring board being fixedly arranged in the apparatus body；At least one probe being installed on the wiring board, the probe are located at the second default opening on the apparatus body bottom surface, to receive and dispatch distance measuring signal to outside；Wherein, the outside of the probe is additionally provided with the shock absorber part wrapped up from non-signal transmit-receive position the probe.By the technical solution of the disclosure, aircraft can be reduced and shake interference caused by range finding probe, to promote the accuracy of indoor positioning.
Description
Technical field
This disclosure relates to field of terminal technology more particularly to a kind of aircraft and its indoor auxiliary locator.
Background technique
Indoor auxiliary locator can make aircraft in no GPS signal feelings by image vision positioning, elevation carrection etc.
Extreme low-altitude or indoor stabilized flight or hovering etc. are realized under condition.
In the related art, since indoor auxiliary locator is to rigidly fix company by screw etc. and aircraft body
It connects, so that the vibration of generation in flight course, can be passed directly to indoor auxiliary locator, thus right by aircraft body
The elevation carrection of indoor auxiliary locator affects greatly, or even causes aircraft to fall due to that can not accurately measure
It ruins etc. unexpected.
Summary of the invention
The disclosure provides a kind of aircraft and its indoor auxiliary locator, to solve deficiency in the related technology.
According to the first aspect of the embodiments of the present disclosure, a kind of indoor auxiliary locator of aircraft is provided, comprising:
Apparatus body；
Image collection assembly is fixedly arranged in the apparatus body, and the camera of described image acquisition component is located at described set
The first default opening on standby ontology bottom surface, to acquire external image；
Ranging component, the ranging component include:
The wiring board being fixedly arranged in the apparatus body；
At least one probe being installed on the wiring board, the probe are located at second on the apparatus body bottom surface
Default opening, to receive and dispatch distance measuring signal to outside；Wherein, the outside of the probe is additionally provided with from non-signal transmit-receive position to institute
State the shock absorber part that probe is wrapped up.
Optionally, the shock absorber part includes: the flexible glue casing wrapped up the side wall of the probe.
Optionally, the shock absorber part further include: the flexible glue gasket between the bottom surface and the wiring board of the probe.
Optionally, the flexible glue casing includes silica gel sleeve pipe, and the flexible glue gasket includes silica gel pad.
Optionally, the soft rubber cushion on piece is equipped with the pin stretched out with the probe bottom surface several via holes correspondingly,
The pin of the probe is plugged on the wiring board after passing through corresponding via hole.
Optionally, the outside of the probe be additionally provided with the probe is wrapped up from non-signal transmit-receive position interference every
Off member.
Optionally, the interference and insulation part includes: to be made to what the side wall of the probe was wrapped up of absorbing material
Suction wave casing.
Optionally, the suction wave casing includes foam casing.
Optionally, the interference and insulation part is wrapped on the outside of the shock absorber part.
According to the second aspect of an embodiment of the present disclosure, a kind of aircraft is provided, comprising:
Aircraft body；
The indoor auxiliary locator of aircraft as described in any in above-described embodiment, is installed on the aircraft body
Bottom.
The technical scheme provided by this disclosed embodiment can include the following benefits:
As can be seen from the above embodiments, damping is set outside the range finding probe that the disclosure passes through auxiliary locator indoors
Part, the especially shock absorber part can wrap up the probe, to can reduce flight when the probe executes distance measurement function
Device shakes caused by it, to promote the accuracy of measurement of the probe, thus assist aircraft realize indoor scene under safety,
Stabilized flight.
It should be understood that above general description and following detailed description be only it is exemplary and explanatory, not
The disclosure can be limited.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows the implementation for meeting the disclosure
Example, and together with specification for explaining the principles of this disclosure.
Fig. 1 is that a kind of indoor auxiliary locator shown according to an exemplary embodiment is cooperated with aircraft body
Schematic diagram.
Fig. 2 is a kind of schematic perspective view of indoor auxiliary locator shown according to an exemplary embodiment.
Fig. 3 is a kind of decomposition texture schematic diagram of ranging component shown according to an exemplary embodiment.
Fig. 4 is a kind of schematic perspective view of ranging component shown according to an exemplary embodiment.
Specific embodiment
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment
Described in embodiment do not represent all implementations consistent with this disclosure.On the contrary, they be only with it is such as appended
The example of the consistent device and method of some aspects be described in detail in claims, the disclosure.
Fig. 1 is that a kind of indoor auxiliary locator shown according to an exemplary embodiment is cooperated with aircraft body
Schematic diagram, as shown in Figure 1, aircraft can be made by the bottom that indoor auxiliary locator 2 is installed on to aircraft body 1
Under state of flight, the detection of the parameters such as visual pattern and height is realized by the interior auxiliary locator 2, thus
In the case where without GPS signal, the accurate positioning realized to the aircraft, to control steady under aircraft realization indoor design condition
Fixed flight, hovering etc..
Fig. 2 is a kind of schematic perspective view of indoor auxiliary locator shown according to an exemplary embodiment, such as
Shown in Fig. 2, which may include:
Apparatus body 20；
Image collection assembly 21 is fixedly arranged in the apparatus body 20, and the camera of the image collection assembly 21 is set positioned at this
At the first default opening (not indicated in figure) on standby 20 bottom surface of ontology so that the interior auxiliary locator 2 be installed in it is winged
Behind the bottom of row device ontology 1, the external image of aircraft bottom can be acquired, and recognise that there are barrier,
Follow airbound target etc.；
Ranging component 22 is fixedly arranged in the apparatus body 20, and at least one on the ranging component 22 is popped one's head in be located at and be set
At the second default opening (not indicated in figure) on standby 1 bottom surface of ontology；Such as in the embodiment shown in Figure 2, the ranging component
22 may include the first probe 221 and the second probe 222, so that the interior auxiliary locator 2 is installed in aircraft body 1
Bottom after, can to the object of aircraft bottom carry out ranging, to determine the current flying altitude etc. of aircraft, to realize
Stabilized flight or hovering under such as ultralow dummy status, and avoid colliding with respective objects or user etc., promote aircraft
With both sides' safety of user.
Fig. 3 is a kind of decomposition texture schematic diagram of ranging component shown according to an exemplary embodiment, as shown in figure 3,
The ranging component 22 may include:
The wiring board 223 being fixedly arranged in the apparatus body 1, the wiring board 223 can be fixed on by screw 32 etc.
On apparatus body 20；
At least one probe being installed on the wiring board 223, than embodiment as explained in connection with fig.2, the ranging component
May include the first probe 221 and the second probe 222 etc. in 22, and for ease of description, this sentence for the first probe 221 into
Row explanation, the second 222 corresponding fit structures of probe can be with reference to first probes 221.
In conjunction with Fig. 2 it is found that indoor auxiliary locator 2 needs to realize just by screw 31 etc. with aircraft body 1
Property connection, to ensure being bonded to the interior auxiliary locator 2, but top of the aircraft body 1 in flight course
Vibration can be conducted therewith to indoor auxiliary locator 2 caused by winnowing with a dustpan, shaking, so that first in such as ranging component 22 is visited
First 221, second probe 222 etc. can be affected by it, and it is inaccurate to lead to the data measured, be missed such as due to generating biggish data
Normal flight that is poor and influencing aircraft body 1, in some instances it may even be possible to aircraft body 1 and ground object, user etc. be caused to touch
It hits, there are great security risks.
Therefore, it as shown in figure 3, being based on above-mentioned security risk, can be set in the outside of the such as first probe 221 from non-letter
The shock absorber parts 4 that number transmit-receive position wraps up first probe 221.For example for the first probe 221 shown in Fig. 3, this
One probe 221 receives and dispatches distance measuring signal, such as ultrasonic signal, infrared signal etc. by its top surface 221A outward, to realize survey
Acquisition away from data, then the direction of top surface 221A direction is the signal transmitting and receiving direction of first probe 221A, should be avoided pair
It is wrapped up at the 221A of the top surface, to avoid the normal transmitting-receiving for influencing distance measuring signal.
And the first probe 221 further includes side wall 221B and bottom surface 221C, bottom surface 221C passes through two or other quantity
Pin is plugged on wiring board 223；Since side wall 221B, bottom surface 221C are unrelated with the transmitting-receiving of distance measuring signal, thus can pass through
Shock absorber part 4 wraps up at least one of side wall 221B and bottom surface 221C, thus when aircraft body 1 generates vibration, it should
Shock absorber part 4 can absorb vibration, and to reduce the influence waited the first probe 221, it is accurate can to promote corresponding ranging
Degree, it is ensured that aircraft body 1 realizes more accurately indoor flight.
As shown in figure 3, corresponding to the side wall 221B of the first probe 221, shock absorber part 4 may include carrying out to side wall 221B
The flexible glue casing 41 of package, such as the flexible glue casing 4 can be silicone tube or rubber tube elastomeric material.Further, corresponding
In the bottom surface 221C of the first probe 221, due to the bottom surface 221C of the first probe 221 carry out with wiring board 223 it is mating, thus
Shock absorber part 4 can also include the flexible glue gasket 42 between bottom surface 221C and wiring board 223, such as the flexible glue gasket 42 can
Think silica gel piece or sheet rubber elastomeric material；Wherein, the top surface of flexible glue gasket 42 can be with the bottom margin of flexible glue casing 41
Cooperated, to realize the closing of the side wall 221B and bottom surface 221C to the first probe 221, realizes best damping effect.
In addition, after indoor auxiliary locator 2 is installed in aircraft body 1, due to also being set inside aircraft body 1
There is communication module etc., the electromagnetic wave of generation is likely to interfere the transmitting-receiving of the distance measuring signal of ranging component 22, thus
As shown in figure 3, can be arranged in the external of first probe 221 from non-signal transmit-receive position pair still by taking the first probe 221 as an example
The interference and insulation part 5 that first probe 221 is wrapped up, to reduce interference of the above-mentioned electromagnetic wave to first probe 221.
Wherein, interference and insulation part 5 can be made of the absorbing materials such as foam, thus by transmitting to this first
Electromagnetic wave etc. near probe 221 is absorbed, it is avoided to interfere first probe 221.For example, interference and insulation
What part 5 can be wrapped up for the side wall 221B to first probe 221 uses suction wave casing made of absorbing material.
So, when 221 outside of the first probe is simultaneously equipped with the flexible glue casing 41 in shock absorber part 4 and as interference and insulation part 5
Suction wave casing when, the ranging component 22 that assembly as shown in Figure 4 is completed, the suction wave casing can be wrapped in outside soft rubber cover pipe 41
Side.
Those skilled in the art will readily occur to its of the disclosure after considering specification and practicing disclosure disclosed herein
Its embodiment.This application is intended to cover any variations, uses, or adaptations of the disclosure, these modifications, purposes or
Person's adaptive change follows the general principles of this disclosure and including the undocumented common knowledge in the art of the disclosure
Or conventional techniques.The description and examples are only to be considered as illustrative, and the true scope and spirit of the disclosure are by following
Claim is pointed out.
It should be understood that the present disclosure is not limited to the precise structures that have been described above and shown in the drawings, and
And various modifications and changes may be made without departing from the scope thereof.The scope of the present disclosure is only limited by the accompanying claims.
Claims (8)
1. a kind of indoor auxiliary locator of aircraft characterized by comprising
Apparatus body；
Image collection assembly is fixedly arranged in the apparatus body, and the camera of described image acquisition component is located at the equipment sheet
The first default opening on body bottom surface, to acquire external image；
Ranging component, the ranging component include:
The wiring board being fixedly arranged in the apparatus body；
At least one probe being installed on the wiring board, second be located on the apparatus body bottom surface of popping one's head in are default
Opening, to receive and dispatch distance measuring signal to outside；Wherein, the outside of the probe is additionally provided with from non-signal transmit-receive position to the spy
The shock absorber part that head is wrapped up；
Interference and insulation part is wrapped in the outside of the shock absorber part along the non-signal transmit-receive position of the probe.
2. the apparatus according to claim 1, which is characterized in that the shock absorber part includes: to carry out to the side wall of the probe
The flexible glue casing of package.
3. the apparatus of claim 2, which is characterized in that the shock absorber part further include: positioned at the bottom surface of the probe
Flexible glue gasket between the wiring board.
4. device according to claim 3, which is characterized in that the flexible glue casing includes silica gel sleeve pipe, the soft rubber cushion
Piece includes silica gel pad.
5. device according to claim 3, which is characterized in that the soft rubber cushion on piece is equipped with stretches out with the probe bottom surface
Pin several via holes correspondingly, the pin of the probe is plugged on the wiring board after passing through corresponding via hole.
6. the apparatus according to claim 1, which is characterized in that the interference and insulation part includes: the side wall to the probe
That is wrapped up inhales wave casing using absorbing material is manufactured.
7. device according to claim 6, which is characterized in that the suction wave casing includes foam casing.
8. a kind of aircraft characterized by comprising
Aircraft body；
Such as the indoor auxiliary locator of aircraft of any of claims 1-7, it is installed on the aircraft body
Bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610350330.2A CN105818998B (en) | 2016-05-24 | 2016-05-24 | Aircraft and its indoor auxiliary locator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610350330.2A CN105818998B (en) | 2016-05-24 | 2016-05-24 | Aircraft and its indoor auxiliary locator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105818998A CN105818998A (en) | 2016-08-03 |
| CN105818998B true CN105818998B (en) | 2019-01-08 |
Family
ID=56530548
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610350330.2A Active CN105818998B (en) | 2016-05-24 | 2016-05-24 | Aircraft and its indoor auxiliary locator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105818998B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106843264A (en) * | 2016-12-28 | 2017-06-13 | 歌尔股份有限公司 | The indoor cruise method and system of unmanned plane |
| CN107472501A (en) * | 2017-09-20 | 2017-12-15 | 湖南基石信息技术有限公司 | Ultrasonic wave anti-interference structure and small-sized pilotless aircraft |
| CN107472523A (en) * | 2017-09-20 | 2017-12-15 | 湖南基石信息技术有限公司 | Ducted propeller and small-sized pilotless aircraft |
| CN109031312B (en) * | 2018-04-26 | 2023-08-22 | 中国计量大学 | Flight platform positioning device and positioning method suitable for chimney internal operation |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102331783A (en) * | 2011-06-17 | 2012-01-25 | 沈阳航空航天大学 | Autopilot for indoor airship |
| CN202579804U (en) * | 2012-05-31 | 2012-12-05 | 中冶集团武汉勘察研究院有限公司 | Inner and outer interlayer type camera damping device for unmanned aerial vehicle |
| EP2679496A2 (en) * | 2012-06-28 | 2014-01-01 | Intertechnique | Passenger service unit with gesture control |
| CN204594468U (en) * | 2015-05-15 | 2015-08-26 | 零度智控（北京）智能科技有限公司 | Aircraft flight error correction device and unmanned vehicle |
| CN104875890A (en) * | 2015-06-01 | 2015-09-02 | 中国人民解放军装甲兵工程学院 | Four-rotor aircraft |
| CN205801537U (en) * | 2016-05-24 | 2016-12-14 | 北京小米移动软件有限公司 | Aircraft and indoor auxiliary locator thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140379178A1 (en) * | 2013-06-24 | 2014-12-25 | Honeywell International Inc. | System and method for fine positioning of vtol stare point |
-
2016
- 2016-05-24 CN CN201610350330.2A patent/CN105818998B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102331783A (en) * | 2011-06-17 | 2012-01-25 | 沈阳航空航天大学 | Autopilot for indoor airship |
| CN202579804U (en) * | 2012-05-31 | 2012-12-05 | 中冶集团武汉勘察研究院有限公司 | Inner and outer interlayer type camera damping device for unmanned aerial vehicle |
| EP2679496A2 (en) * | 2012-06-28 | 2014-01-01 | Intertechnique | Passenger service unit with gesture control |
| CN204594468U (en) * | 2015-05-15 | 2015-08-26 | 零度智控（北京）智能科技有限公司 | Aircraft flight error correction device and unmanned vehicle |
| CN104875890A (en) * | 2015-06-01 | 2015-09-02 | 中国人民解放军装甲兵工程学院 | Four-rotor aircraft |
| CN205801537U (en) * | 2016-05-24 | 2016-12-14 | 北京小米移动软件有限公司 | Aircraft and indoor auxiliary locator thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105818998A (en) | 2016-08-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105818998B (en) | Aircraft and its indoor auxiliary locator | |
| US10642368B2 (en) | Body posture detection system, suit and method | |
| CN108139216B (en) | System and method for providing a simple and reliable inertial measurement unit | |
| CN108917746B (en) | Helmet posture measuring method, measuring device and measuring system | |
| Arens et al. | Measuring 3D indoor air velocity via an inexpensive low-power ultrasonic anemometer | |
| CN105716684A (en) | UAV (Unmanned Aerial Vehicle) liquid level measuring device and UAV liquid level measuring method | |
| KR101815595B1 (en) | Local coordinate measurement value precision detection system for digital map update | |
| BR112012017560B1 (en) | stabilization system for sensors on mobile platforms | |
| CN201993431U (en) | Acoustoelectric and X-ray insulation testing visual movable integrated device for electrical equipment | |
| US20170269203A1 (en) | Point of Reference Displacement and Motion Sensor | |
| CN109032155A (en) | A kind of control device and unmanned vehicle for unmanned vehicle | |
| KR20170033625A (en) | Drone | |
| EP3540445A1 (en) | Information processing device | |
| US10310121B2 (en) | Seismic sensor devices, systems, and methods including noise filtering | |
| US8842494B2 (en) | Apparatus for sensing motion of a surface | |
| JP2016060451A (en) | Underwater information measuring apparatus | |
| WO2018053784A1 (en) | Vibration damper plate, and unmanned aerial vehicle provided with vibration damper plate | |
| CN105973135A (en) | Magnetostrictive displacement sensor and applicable displacement measurement device | |
| CN104019890B (en) | A kind of infrasonic wave detection method and detection device thereof | |
| CN205801537U (en) | Aircraft and indoor auxiliary locator thereof | |
| CN205578605U (en) | Damping structure, inertia detection device and unmanned vehicles | |
| CN101893484B (en) | Black body spherical surface temperature measurement system for external field infrared radiation measurement and correction | |
| CN106323341A (en) | Method and system for automatically correcting attitude measurement device | |
| CN114200470A (en) | Digital photographic laser scanning device | |
| CN106813683B (en) | Bidirectional airborne angle correction device and correction method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |