CN101830285A - Aerofoil leading edge deicing device for unmanned aerial vehicle - Google Patents
Aerofoil leading edge deicing device for unmanned aerial vehicle Download PDFInfo
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- CN101830285A CN101830285A CN201010183910A CN201010183910A CN101830285A CN 101830285 A CN101830285 A CN 101830285A CN 201010183910 A CN201010183910 A CN 201010183910A CN 201010183910 A CN201010183910 A CN 201010183910A CN 101830285 A CN101830285 A CN 101830285A
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- ice bar
- steering wheel
- leading edge
- push away
- deicing device
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Abstract
The invention discloses an aerofoil leading edge deicing device for an unmanned aerial vehicle, which comprises a servo steering engine, a pushing mechanism and an ice pushing strip, wherein the pushing mechanism pushes the ice pushing strip under the drive of the servo steering engine; the ice pushing strip is protruded out of the skin surface of an aerofoil of the unmanned aerial vehicle after being jacked up for carrying out deicing work; the pushing mechanism comprises a steering engine rocking arm and a steering engine connecting rod; the steering engine rocking arm is fixed on an output shaft of the servo steering engine and can do circular motion by adopting the output shaft as a circle center; one end of the steering engine connecting rod is connected to the steering engine rocking arm, and the other end is connected with the ice pushing strip; and the steering engine rocking arm, the steering engine connecting rod and the ice pushing strip form a crank rocker mechanism, and the steering engine connecting rod drives the ice pushing strip for realizing jacking up and retracting motions. The aerofoil leading edge deicing device for an unmanned aerial vehicle has simple structure, low cost, safety, reliability, convenient operation and recycling.
Description
Technical field
The invention belongs to the Unmanned Aircraft Systems (UAS) field, particularly a kind of aerofoil leading edge deicing device that is used for unmanned plane of novelty
Background technology
Unmanned plane is a kind of by unpiloted aerocraft on power driven, the machine.It is made up of body, engine installation, flicon and managerial tools, emission reclaiming scrap etc. usually, can remote control or flight automatically, can disposablely use, and also can reclaim, repeated use.It is one of current new-and high-tech weaponry and equipment, is widely used in battlefield investigation, electronic countermeasure, lesion assessment, many warlike operations such as attack over the ground after the war, is the requisite equipment of IT-based warfare.At civil area, fields such as it has been widely used in and has increased rain artificially, air remote sensing, aerial mapping, forest fire protection, coastline patrol.At present, the field that unmanned plane is used is increasing, and the environment of unmanned plane operation is also abominable thereupon.Unmanned plane when flying height surpasses 5000m, flies in the subcooled water in the clouds in operation process often.So-called subcooled water is meant that temperature is lower than 0 ℃, but because of containing the fine water particle that molecule does not freeze.Subcooled water is attached on the unmanned plane wing, form easily and freeze, change wing shapes when light, influence lift, increase oil consumption, significantly change wing shapes when serious, increase aircraft weight and may surpass critical value, jeopardize flight safety, even cause the generation of air crash accident, cause the equipment loss or ground staff and property are worked the mischief.Therefore, it is essential to resolve the wing ice formation issues of unmanned plane.But problems such as the wing deicing device that is used for unmanned plane at present all exists mechanism's complexity, and volume is big, and weight is big, and is difficult in maintenance.
Summary of the invention
The object of the present invention is to provide a kind of simple in structure, cheap, safe and reliable, easy to operate, can repeat nonexpondable unmanned plane aerofoil leading edge deicing device.
The invention discloses a kind of aerofoil leading edge deicing device that is used for unmanned plane, comprise servo steering wheel, pushing mechanism and push away the ice bar, pushing mechanism pushes away the ice bar under the driving of servo steering wheel, protrude unmanned plane wing cover surface after pushing away ice bar jack-up, carries out de-icing work.
Described pushing mechanism comprises steering wheel rocking arm and steering wheel connecting rod, the steering wheel rocking arm is fixed on the output shaft of servo steering wheel, can be that the center of circle moves in a circle with the output shaft, steering wheel connecting rod one end is connected to the steering wheel rocking arm, the other end with push away ice bar be connected, steering wheel rocking arm, steering wheel connecting rod push away the ice bar and constitute a quadric linkage, drive by the steering wheel connecting rod and push away ice bar realization jack-up and the motion of packing up.
Deicer also comprises and pushes away ice bar fixed plate, pushes away ice bar fixed plate and is the L type, and two push away ice bar fixed plate symmetric arrangement, pushes away the ice bar and is arranged on two and pushes away between the ice bar fixed plate.
Push away ice and have a plurality of guide grooves on the bar, a plurality of spacing collars are inserted in the guide groove, and the length of spacing collar is greater than the thickness that pushes away the ice bar.
Spacing collar and push away between the guide groove of ice on the bar and be free-running fit.One holding screw passes and pushes away ice bar fixed plate and spacing collar, with lock nut spacing collar is clamped.
Pushing away ice bar fixed plate is fixed on the covering of unmanned plane aerofoil surface by screw.
All parts of this aerofoil leading edge deicing device all are arranged on unmanned plane wing inside.
The ice that pushes away that pushes away ice bar (5) by manual remote control or the control of unmanned plane autopilot moves.
This unmanned plane wing deicing device has taken into full account the characteristics of unmanned plane when high-altitude flight, adopt the servo steering wheel of unmanned plane special use to push away the ice bar, can push away the ice sheet of the unmanned plane leading edge of a wing broken like this, pushing away broken ice sheet is dispelled by the incoming flow on unmanned plane opposite, and then keep the high-level airworthiness of unmanned plane, prevented the variety of problems of bringing because of freezing.
The characteristics that the present invention gives prominence to are:
1, all structures of this device all are arranged on unmanned plane wing inside, can the aeroperformance of unmanned plane during flying not had any impact;
2, the present invention both can control the action that aerofoil leading edge deicing device pushes away the ice bar by manual remote control, also can be by its action of programming control of unmanned aerial vehicle onboard autopilot;
3, the exhibition that is arranged in unmanned plane wing both sides that aerofoil leading edge deicing device of the present invention can be symmetrical according to the measuring and calculating of flying height, meteorological conditions, flight time etc., can be arranged one or more groups this deicer, to reach the purpose of deicing to the position.
Description of drawings
Fig. 1 is that deicer is opened up to arranging scheme drawing at unmanned plane;
Fig. 2 pushes away ice bar collapsed state scheme drawing for deicer when unmanned plane during flying;
Fig. 3 carries out deicing action scheme drawing for deicer when unmanned plane during flying;
Fig. 4 is the deicer structural representation;
Fig. 5 is Fig. 4 A-A view;
Fig. 6 ices bar scheme drawing when collapsed state for deicer pushes away;
Fig. 7 ices bar scheme drawing when the jack-up state for deicer pushes away;
Fig. 8 is a deicer partly cut-away scheme drawing.
Description of reference numerals:
1, unmanned plane wing; 2, servo steering wheel; 3, steering wheel connecting rod; 4, push away ice bar fixed plate;
5, push away the ice bar; 6, steering wheel rocking arm;
51, push away ice bar guide groove; 52, spacing collar; 53, holding screw;
54, lock nut; 55 pads;
The specific embodiment
Below in conjunction with accompanying drawing the present invention is specifically described.
Figure 1 shows that the exhibition of deicer on unmanned plane is to arranging scheme drawing.As seen from the figure, this deicer is arranged in the leading edge of unmanned plane wing 1, along opening up to layout.
Fig. 4-8 shows the concrete structure of deicer.Deicer comprises servo steering wheel 2, and steering wheel rocking arm 6 is provided with a steering wheel rocking arm 6, and steering wheel rocking arm 6 is fixed on steering wheel 2 output shafts, and it can be that the center of circle moves in a circle with the output shaft.Steering wheel rocking arm 6 connects a steering wheel connecting rod 3, the other end of steering wheel connecting rod 3 with push away ice bar 5 and be connected, like this, steering wheel rocking arm 6, steering wheel connecting rod 3 push away and ice bar 5 and promptly constituted a quadric linkage.Steering wheel 2 outputting powers, steering wheel rocking arm 6 rotatablely moves, and shown in Fig. 6,7, drives the motion that pushes away ice bar 5 realization jack-up and pack up by connecting rod 3.
Deicer also comprises pushing away ices bar fixed plate 4.As shown in Figure 8, push away ice bar fixed plate 4 and be the L type, two ends all are provided with through hole, and wherein an end is fixed on the upper surface of unmanned plane wing 1 covering by screw.Two push away ice bar fixed plate 4 symmetric arrangement, pass pad 55, push away ice bar fixed plate 4, push away ice bar 5 and spacing collar 52 by screw 53, will push away ice bar spacing collar 52 with lock nut 55 and clamp.Spacing collar 52 length are greater than the thickness that pushes away ice bar 5, and spacing collar 52 and push away and be free-running fit on the ice bar 5 between the corresponding guide groove 51, so after holding screw 53 lockings two symmetries push away ice bar fixed plate 4, pushing away ice bar 5 can freely rotate pushing away between the ice bar fixed plate 4, realizes pushing away the jack-up of icing bar 5 and packs up action.
Figure 2 shows that pushing away ice bar 5 is in collapsed state, its edge is embedded in unmanned plane wing 1 covering.Fig. 3 carries out deicing action scheme drawing for deicer when unmanned plane during flying, servo steering wheel 2 both can also can pass through unmanned aerial vehicle onboard autopilot programming control by ground-surface emitter manual control by the control of unmanned aerial vehicle onboard receiver.By manual remote control or the control of unmanned aerial vehicle onboard autopilot, servo steering wheel 2 actions, steering wheel rocking arm 6 rotates thereupon, drive 3 motions of steering wheel connecting rod, and then push away ice bar 5 jack-up, and protrude unmanned plane wing 1 skin-surface after pushing away ice bar 5 jack-up, can push up freezing of broken unmanned plane wing 1 leading edge.
Above-mentioned embodiment of the present invention can not be thought restriction that claim of the present invention is done; if those skilled in the art does not need performing creative labour to make corresponding variation by inspiration of the present invention, all should fall into the protection domain of claim of the present invention.
Claims (9)
1. aerofoil leading edge deicing device that is used for unmanned plane, it is characterized in that: comprise servo steering wheel (2), pushing mechanism and push away ice bar (5), pushing mechanism pushes away ice bar (5) under the driving of servo steering wheel (2), protrude unmanned plane wing (1) skin-surface after pushing away ice bar (5) jack-up, carry out de-icing work.
2. aerofoil leading edge deicing device according to claim 1, it is characterized in that: described pushing mechanism comprises steering wheel rocking arm (6) and steering wheel connecting rod (3), steering wheel rocking arm (6) is fixed on the output shaft of servo steering wheel (2), can be that the center of circle moves in a circle with the output shaft, steering wheel connecting rod (3) one ends are connected to steering wheel rocking arm (6), the other end with push away ice bar (5) be connected, steering wheel rocking arm (6), steering wheel connecting rod (3), push away ice bar (5) and constitute a quadric linkage, drive by steering wheel connecting rod (3) and push away ice bar (5) realization jack-up and the motion of packing up.
3. aerofoil leading edge deicing device according to claim 2, it is characterized in that: also comprise pushing away ice bar fixed plate (4), push away ice bar fixed plate (4) and be the L type, two push away ice bar fixed plate (4) symmetric arrangement, push away ice bar (5) and are arranged on two and push away between the ice bar fixed plate (4).
4. aerofoil leading edge deicing device according to claim 3 is characterized in that: push away ice and have a plurality of guide grooves (51) on the bar, a plurality of spacing collars (52) are inserted in the guide groove, and the length of spacing collar (52) is greater than the thickness that pushes away ice bar (5).
5. aerofoil leading edge deicing device according to claim 4 is characterized in that: spacing collar (52) and push away between the guide groove (51) on ice bar (5) and be free-running fit.
6. according to claim 4 or 5 described aerofoil leading edge deicing devices, it is characterized in that: a holding screw (53) passes and pushes away ice bar fixed plate (4) and spacing collar (52), with lock nut (55) spacing collar (52) is clamped.
7. according to each described aerofoil leading edge deicing device of claim 3-6, it is characterized in that: push away ice bar fixed plate (4) and be fixed on the covering on unmanned plane wing (1) surface by screw.
8. according to each described aerofoil leading edge deicing device of claim 1-7, it is characterized in that: all parts of this aerofoil leading edge deicing device all are arranged on unmanned plane wing (1) inside.
9. according to each described aerofoil leading edge deicing device of claim 1-8, it is characterized in that: the ice that pushes away that pushes away ice bar (5) by manual remote control or the control of unmanned plane autopilot moves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010183910 CN101830285B (en) | 2010-05-26 | 2010-05-26 | Aerofoil leading edge deicing device for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010183910 CN101830285B (en) | 2010-05-26 | 2010-05-26 | Aerofoil leading edge deicing device for unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101830285A true CN101830285A (en) | 2010-09-15 |
| CN101830285B CN101830285B (en) | 2013-03-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010183910 Expired - Fee Related CN101830285B (en) | 2010-05-26 | 2010-05-26 | Aerofoil leading edge deicing device for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494832A (en) * | 2014-12-04 | 2015-04-08 | 湖北易瓦特科技有限公司 | High-altitude flight antifreezing system of unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1949787A (en) * | 1932-01-30 | 1934-03-06 | Robt Benj Davis | Airplane |
| GB523108A (en) * | 1938-12-23 | 1940-07-05 | George Burns Salmond | Improvements in or relating to means for de-icing surfaces of aircraft |
| US2271466A (en) * | 1940-06-22 | 1942-01-27 | Benjamin G Wendt | Wing deicer |
| GB564747A (en) * | 1943-02-19 | 1944-10-11 | Flight Refueling Ltd | Improvements in and relating to means for combating ice-formation on surfaces |
| GB654190A (en) * | 1947-06-26 | 1951-06-06 | Autogiro Co Of America | Deicing system for aircraft sustaining rotor blades |
-
2010
- 2010-05-26 CN CN 201010183910 patent/CN101830285B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1949787A (en) * | 1932-01-30 | 1934-03-06 | Robt Benj Davis | Airplane |
| GB523108A (en) * | 1938-12-23 | 1940-07-05 | George Burns Salmond | Improvements in or relating to means for de-icing surfaces of aircraft |
| US2271466A (en) * | 1940-06-22 | 1942-01-27 | Benjamin G Wendt | Wing deicer |
| GB564747A (en) * | 1943-02-19 | 1944-10-11 | Flight Refueling Ltd | Improvements in and relating to means for combating ice-formation on surfaces |
| GB654190A (en) * | 1947-06-26 | 1951-06-06 | Autogiro Co Of America | Deicing system for aircraft sustaining rotor blades |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494832A (en) * | 2014-12-04 | 2015-04-08 | 湖北易瓦特科技有限公司 | High-altitude flight antifreezing system of unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN101830285B (en) | 2013-03-06 |
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