CN203666991U - Igniting and flameout device of unmanned aerial vehicle - Google Patents
Igniting and flameout device of unmanned aerial vehicle Download PDFInfo
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- CN203666991U CN203666991U CN201320735565.5U CN201320735565U CN203666991U CN 203666991 U CN203666991 U CN 203666991U CN 201320735565 U CN201320735565 U CN 201320735565U CN 203666991 U CN203666991 U CN 203666991U
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- igniting
- flameout
- swing arm
- switch
- servo
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Abstract
The utility model provides an igniting and flameout device of an unmanned aerial vehicle. The igniting and flameout device comprises a fixing base, a servo, a swinging rod and a signal receiver, wherein the fixing base is basically U-shaped, two vertical ends and one horizontal end of the fixing base are fixedly connected in an inserted mode, and the symmetric positions of the two vertical ends are provided with an igniting switch and a flameout switch respectively; the servo is fixedly installed at the horizontal end of the base, and a rotary shaft of the servo is located between the two vertical ends of the fixing base; the fixed end of the swinging rod is connected with the rotary shaft of the servo, the free end of the swinging rod, the igniting switch and the flameout switch are on the same plane, and when the rotary shaft drives the swinging rod to rotate clockwise and anticlockwise, the free end of the swinging rod can be in contact with a metal shell of the igniting switch and a metal shell of the flameout switch; the signal receiver is connected with the servo and controls the rotary shaft of the servo to rotate when receiving a signal of a remote controller. The igniting and flameout device has the advantages that an igniting control unit and a flameout control unit are uniformly controlled, so the unmanned aerial vehicle used for aerial photographing does not need to be additionally provided with two sets of equipment, and the use cost and the damage probability are both reduced; the igniting and flameout device is convenient to maintain, saves space and is convenient to install, use and maintain.
Description
Technical field
The utility model belongs to distance type unmanned aerial vehicle control system field, especially makes and relates to unmanned plane igniting and blanket.
Background technology
Existing taking photo by plane mainly contains two kinds, manual operation formula and igniting, flameout control device separate control electric by distance type unmanned aerial vehicle igniting and the mode of stopping working.
Manual operation formula is exactly before taking off, and is opened by hand by the engine ignitor carrying on fuselage by operator.After engine starting, operator leaves, and accelerates to make to take off by open the throttle wide.At the same throttle of controlling of landing time, airplane ascensional force is dropped to make the scope of aircraft landing.Aircraft operator after runway stops manually stopping engine running again.
Above-mentioned manual operation formula, when use, waste time and energy, working specification is poor, easily there is maloperation and in manual operation because the properller of point, blanket switch distance High-speed rotation more closely exists potential safety hazard.
Igniting, flame-out control unit separate control electric refer at aircraft fuselage interior and are provided with relatively independent aircraft igniter device and blanket.In operating process, be responsible for separately the igniting of aircraft and stop working.Such design makes the unmanned aerial vehicle for taking photo by plane need extra two complete equipments that increase, and is that the probability that use cost or appearance damage is all multiplied.While two overlaps independently control setup and also need on remote control equipment (RCE), append control interface, strengthens work capacity.
Summary of the invention
Problem to be solved in the utility model is to provide a kind of unmanned plane igniting and blanket, is particularly suitable for the unmanned plane for taking photo by plane.
For solving the problems of the technologies described above, the technical solution adopted in the utility model is:
Unmanned plane igniting and blanket are provided, comprise:
One firm banking, it is roughly U-shaped, and two vertical ends and a horizontal ends are pegged graft fixing, and two vertically hold upper symmetric position to set up ignition lock and flameout switch separately;
One servomechanism, is installed in the horizontal ends of base, and its rotating shaft is at two vertically between end of firm banking;
One swing arm, the fixed end of swing arm is connected with the rotating shaft of servomechanism, at grade, when rotating shaft drives suitable, the left-hand revolution of swing arm, the free end of swing arm can contact with the metal case of ignition lock and flameout switch respectively for the free end of swing arm and ignition lock and flameout switch;
One signal receiver is connected with described servomechanism, controls the rotating shaft of servomechanism and rotate while receiving remote controller signal.
The midperpendicalar of position when further, described swing arm is not worked and ignition lock and flameout switch is harmonious.
Further, described swing arm hunting range is ± 45 °.
Further, described firm banking and swing arm are titanium alloy material.
Further, described servomechanism is only connected with firm banking.
Advantage and the good effect that the utlity model has are: igniting, the unified control of the control unit that stops working, in operating process, a device is responsible for the igniting of aircraft and stops working.Such design makes the unmanned aerial vehicle for taking photo by plane not need additionally to increase by two complete equipments, is that the probability that use cost or appearance damage all reduces greatly.Easy to maintenance, save space, all comparatively convenient in the time installing, use, safeguard.
Accompanying drawing explanation
Fig. 1 is the assembling schematic diagram of this utility model;
Fig. 2 is the birds-eye view of this utility model.
In figure:
1-ignition lock; 2-firm banking; 3-flameout switch; 4-servomechanism; 5-signal receiver; 6-swing arm; 7-rotating shaft.
The specific embodiment
As illustrated in fig. 1 and 2, unmanned plane igniting and blanket, comprising:
One firm banking 2, it is roughly U-shaped, and two vertical ends and a horizontal ends are pegged graft fixing.Two vertically hold upper symmetric position to set up ignition lock 1 and flameout switch 3 separately.The setting of U-shaped is vertically to hold in order to make ignition lock 1 and flameout switch 3 can accurately be symmetricly set on two.In the present embodiment, two of firm banking 2 vertical end faces are provided with through hole, and ignition lock 1 and flameout switch 3 are welded on vertical end through after through hole, can certainly use being fixedly connected with of other modes.The metal case of ignition lock 1 and flameout switch 3 can be realized control by On current.
Described firm banking 2 is fixed in fuselage interior, in the present embodiment, by affixed firm banking 2 metal backing, then metal backing is connected on fuselage with bolt.Metal backing setting is just used for increasing installation strength, can convenient replacing metal backing after occurring using wearing and tearing need to increase cost again and buys firm banking 2.
One servomechanism 4, is installed in the horizontal ends of base 2, and its rotating shaft 7 is at two vertically between end of firm banking.In the present embodiment, rotating shaft is located on the axis of ignition lock 1 and flameout switch 3, and which can guarantee that servomechanism 4 is identical to distance between the two, and controlling to adjust has a middle benchmark.
One swing arm 6, the fixed end of swing arm 6 is connected with the rotating shaft 7 of servomechanism 4, the free end of swing arm 6 and ignition lock 1 and flameout switch 3 are at grade, rotating shaft 7 drives that swing arm 6 is suitable, when left-hand revolution, the free end of swing arm 6 can contact with the metal case of ignition lock 1 and flameout switch 3 respectively.The swing arm of servomechanism 4 alives while work, makes switch energising with ignition lock 1 with the metal case of flameout switch 3 after contacting, and realizes control action.
One signal receiver 5 is connected with described servomechanism 4, controls the rotating shaft rotation of servomechanism 4 while receiving remote controller signal.In original technology, adopt and manually boot, the present embodiment is integrated can control servomechanism 4 and move after remote control.
The midperpendicalar of position when described swing arm 6 is not worked and ignition lock 1 and flameout switch 3 is harmonious.When work, its anglec of rotation to ignition lock 1 or flameout switch 3 is identical.Can realize in the same time and complete and light a fire or flame-out control.
Described swing arm 6 hunting ranges are ± 45 °.Too little angle be likely subject to fuselage jolt pendulum make swing arm false touch to switch, operation makes the mistake.Too large angle also can make control response overlong time, causes the problem of Operation delay, affects equally operating accuracy.
Described firm banking 2 and swing arm are titanium alloy material, and it is high that the material of titanium alloy has intensity, and quality is light, and withstanding corrosion has good anti-stress performance.Be particularly suitable for the uncertain unmanned aerial vehicle of working environment and use, guarantee various jolt and extreme environment can not destroy unmanned plane igniting in this embodiment and safety, the reliability of blanket.
4 of described servomechanisms are connected with firm banking 2.Only be connected with firm banking 2, can at utmost reduce servomechanism 4 and be subject to external force and make it produce the chance of maloperation, reach the requirement of accurate control.
Above embodiment of the present utility model is had been described in detail, but described content is only preferred embodiment of the present utility model, can not be considered to for limiting practical range of the present invention.All equalization variation and improvement etc. of doing according to the utility model scope, within all should still belonging to this patent covering scope.
Claims (5)
1. unmanned plane igniting and blanket, is characterized in that, comprising:
One firm banking (2), it is roughly U-shaped, and two vertical ends and a horizontal ends are pegged graft fixing, and two vertically hold upper symmetric position to set up ignition lock (1) and flameout switch (3) separately;
One servomechanism (4), is installed in the horizontal ends of base (2), and its rotating shaft (7) is at two vertically between end of firm banking;
One swing arm (6), the fixed end of swing arm (6) is connected with the rotating shaft (7) of servomechanism (4), the free end of swing arm (6) and ignition lock (1) and flameout switch (3) are at grade, when rotating shaft (7) drives suitable, the left-hand revolution of swing arm (6), the free end of swing arm (6) can contact with the metal case of ignition lock (1) and flameout switch (3) respectively;
One signal receiver (5) is connected with described servomechanism (4), controls the rotating shaft (7) of servomechanism (4) and rotate while receiving remote controller signal.
2. unmanned plane igniting according to claim 1 and blanket, is characterized in that: the midperpendicalar of position when described swing arm (6) is not worked and ignition lock (1) and flameout switch (3) is harmonious.
3. unmanned plane igniting according to claim 1 and 2 and blanket, is characterized in that: described swing arm (6) hunting range is ± 45 °.
4. unmanned plane igniting according to claim 1 and blanket, is characterized in that: described firm banking (2) and swing arm (6) are titanium alloy material.
5. unmanned plane igniting according to claim 1 and blanket, is characterized in that: described servomechanism (4) is only connected with firm banking (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320735565.5U CN203666991U (en) | 2013-11-20 | 2013-11-20 | Igniting and flameout device of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320735565.5U CN203666991U (en) | 2013-11-20 | 2013-11-20 | Igniting and flameout device of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203666991U true CN203666991U (en) | 2014-06-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320735565.5U Expired - Fee Related CN203666991U (en) | 2013-11-20 | 2013-11-20 | Igniting and flameout device of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203666991U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016145325A1 (en) * | 2015-03-12 | 2016-09-15 | Sikorsky Aircraft Corporation | Conditional engine igniters |
| CN107463109A (en) * | 2016-06-03 | 2017-12-12 | 中国科学院沈阳自动化研究所 | A kind of universal water surface movable robot platform |
-
2013
- 2013-11-20 CN CN201320735565.5U patent/CN203666991U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016145325A1 (en) * | 2015-03-12 | 2016-09-15 | Sikorsky Aircraft Corporation | Conditional engine igniters |
| CN107463109A (en) * | 2016-06-03 | 2017-12-12 | 中国科学院沈阳自动化研究所 | A kind of universal water surface movable robot platform |
| CN107463109B (en) * | 2016-06-03 | 2023-11-14 | 中国科学院沈阳自动化研究所 | General type surface of water mobile robot platform |
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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 |
Granted publication date: 20140625 Termination date: 20181120 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |