CN203601576U - Aircraft approach guidance system - Google Patents
Aircraft approach guidance system Download PDFInfo
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- CN203601576U CN203601576U CN201320396624.0U CN201320396624U CN203601576U CN 203601576 U CN203601576 U CN 203601576U CN 201320396624 U CN201320396624 U CN 201320396624U CN 203601576 U CN203601576 U CN 203601576U
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- movable framework
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Abstract
An aircraft approach guidance system comprises a pedestal, a fixing framework fixed on the pedestal, a movable framework, a reflector group a light source module, a first rotating module and a second rotating module. The movable framework is rotatably erected on the fixing framework along a vertical shaft which is vertical to the pedestal; the reflector group is rotatably erected on the movable framework along a horizontal shaft which is parallel to the pedestal; the light source module is fixedly erected on the movable framework and provides a light ray impinged toward the reflector group; the first rotating module is used for driving the movable framework along the vertical shaft; and the second rotating module is used for driving the reflector group along the horizontal shaft. According to the aircraft approach guidance system, the configuration of the integral structure is compact, the occupied area is small, the movable framework is arranged in the fixed framework, and is very easy to move and assemble.
Description
Technical field
The utility model is to provide a kind of aerocraft guidance system of marching into the arena, refer to especially one use for location, the object of identifying and follow the trail of the objective, for example be applied to airport after aerocraft landing, measure the distance of aerocraft preset distance point (SPOT), move to correct position for guiding aerocraft, or be applied to other ground traffic tools.
Background technology
For location, identification and follow the trail of aerocraft, particularly follow the trail of and aircraft that indication is advanced along indicatrix after landing can correctly stop at the halt point (being for example the empty bridge on airport) of an appointment.Prior art has TaiWan, China 278141 " aircraft identification and the guidance system of marching into the arena ", can be used for by using the effect of laser pulse detecting, identify and docking one airplane, but its overall structure is compared with dispersion and wordy, be unfavorable for installing, need in addition two dressing tables, increase and measure the complexity of integrating.
Utility model content
The utility model is to provide a kind of aerocraft guidance system of marching into the arena, and all elements is incorporated on the pedestal of a board and is beneficial to install, and utilize a catadioptre group to reduce number of elements.
Described above for reaching, the utility model provides a kind of aerocraft guidance system of marching into the arena, and this aerocraft guidance system of marching into the arena comprises that a pedestal, is fixed on fixed frame, a movable framework, a catadioptre group, a light source module, one first rotary module and one second rotary module on this pedestal.Movable framework is set up on this fixed frame revolvably along a vertical axis perpendicular to pedestal; Catadioptre group is set up on this movable framework revolvably along a horizontal shaft that is parallel to pedestal; Light source module is set up in regularly on this movable framework and the light of this catadioptre group of a directive is provided; The first rotary module along above-mentioned vertical axis to drive above-mentioned movable framework; The second rotary module along above-mentioned horizontal shaft to drive above-mentioned catadioptre group.
Further, fixed frame comprises that one is fixed on the top board that the high assembly of frame, on pedestal is fixed on base plate on the high assembly of frame, is fixed on pair of side plates and on base plate and is fixed on the top of this pair of side plates, wherein, movable framework is set up on described base plate revolvably.
Further, the first rotary module has first follower and that is fixed on the first axle body and is positioned at the below of base plate through base plate and the first axle body, that is connected in movable framework and is located at the first power pack on pedestal, and the first power pack drives the first follower.
Further, the first power pack comprises that one is fixed on motor base, on pedestal and is located at the first driving wheel and one first Transmission that the first motor, on motor base is positioned at the below of motor base and is driven by the first motor, and the first Transmission is by transmission of power to the first follower of the first driving wheel.
Further, the first Transmission is a drive belt.
Further, movable framework is U font, and movable framework comprises a transverse slat and be located at a pair of riser at the two ends of transverse slat, and transverse slat is parallel to base plate, and the two ends of catadioptre group can be set up on this pair of riser rotationally.
Further, the second rotary module comprises the second follower and one second power pack that is connected in the second axle body and is positioned at the outside of movable framework through one of them of this pair of riser and the second axle body, that is connected with catadioptre group, and the second power pack drives the second follower.
Further, the second power pack comprises that second motor, that is fixed on one of them of this pair of riser and is positioned at movable framework is positioned at the outside of movable framework and is connected in the second driving wheel and one second Transmission of the second motor, and the second Transmission is by transmission of power to the second follower of the second driving wheel.
Further, the second Transmission is a drive belt.
Further, the second rotary module further comprises an angle limit assembly, angle limit assembly and the second follower are located opposite from the opposite side of movable framework, and angle limit assembly is positioned at wherein another the lateral surface of this pair of riser, angle limit assembly comprises that one is fixed on wherein another the stop part of this pair of riser with the position-limited wheel and of catadioptre group synchronous rotary, wherein, position-limited wheel has a sector notch, and stop part is positioned at sector notch.
The configuration of the utility model integral structure is simplified and is taken less space, and wherein movable frame is set up and is placed in fixed frame, and mobile and assembling is very easy to.
Be in order to give an example and to explain principle of the present utility model about the explanation of the utility model content and the explanation of following embodiment above, and provide patent claim of the present utility model further to explain.
Accompanying drawing explanation
Fig. 1 is the march into the arena three-dimensional combination figure of guidance system of aerocraft of the present utility model.
Fig. 2 is march into the arena another three-dimensional combination figure of guidance system of aerocraft of the present utility model.
Fig. 3 is the march into the arena front elevation of guidance system of aerocraft of the present utility model.
Fig. 4 A is the march into the arena lateral plan of guidance system of aerocraft of the present utility model.
Fig. 4 B is the aerocraft of the present utility model postrotational lateral plan of guidance system signal catadioptre group of marching into the arena.
Fig. 5 A is the march into the arena birds-eye view of guidance system of aerocraft of the present utility model.
Fig. 5 B is that the aerocraft of the present utility model guidance system of marching into the arena is illustrated the postrotational birds-eye view of movable framework.
[nomenclature]
Fixed frame 20
The high assembly 21 of frame
Elevated plate body 21a, 21b
Perforate 240
Transverse slat 31
Riser 33a, 33b
Catadioptre group 40
Catadioptre 42
Crimp 44
Supporting plate 46
The first rotary module 50
The first power pack 52
The first motor 522
The first driving wheel 526
The first Transmission 528
The first axle body 54
The first follower 56
The first limit assembly 58
The first position-limited wheel 581
The first stop part 582
The second rotary module 60
The second power pack 62
The second motor 622
The second driving wheel 624
The second Transmission 626
The second axle body 64
The second follower 66
The second limit assembly 68
The second position-limited wheel 681
The second stop part 682
Optical transmitting set 72
Fixing part 74
Angle Θ x, Θ y
Light R
Horizontal shaft X
Vertical axis Y
The specific embodiment
Please refer to Fig. 1 and Fig. 2, is the march into the arena three-dimensional combination figure of guidance system of aerocraft of the present utility model.The utility model provides a kind of aerocraft guidance system of marching into the arena, it comprise a pedestal 10, be fixed on fixed frame on this pedestal 10 20, be set up in movable framework in fixed frame 20 30, be set up in the catadioptre group 40 of movable framework 30, in order to driving the first rotary module 50 of movable framework 30, in order to drive the second rotary module 60 and a light source module 70 of catadioptre group 40.Wherein movable framework 30 is rotatably set up on fixed frame 20 perpendicular to the vertical axis Y of pedestal 10 along one.Catadioptre group 40 is rotatably set up on movable framework 30 along a horizontal shaft X who is parallel to pedestal 10.The first rotary module 50 along above-mentioned vertical axis Y to drive above-mentioned movable framework 30; The second rotary module 60 along above-mentioned horizontal shaft X to drive above-mentioned catadioptre group.Light source module 70 is set up in regularly movable framework 30 and the light of a toward mirror group 40 is provided.
The fixed frame 20 of the present embodiment is a square framework substantially, is fixed on pedestal 10 in the high mode of frame, and the lower side space after 20 of fixed frames are high is for the subelement of accommodating the first rotary module 50.In particular, fixed frame 20 comprises that one is fixed on that the high assembly of the frame of said base 10 21, is fixed on the base plate 22 of the high assembly 21 of frame, a pair of side plate 23 and that is fixed on base plate 22 is fixed on this top board 24 to side plate 23 tops, and wherein this movable framework 30 is rotatably set up on this base plate 22.The high assembly 21 of frame of the present embodiment is a pair of elevated plate body 21a, 21b, but is not restricted to this, as long as can all applying in order to the structure of the high above-mentioned base plate 22 of frame, for example, can be the plate body etc. of many cylinders or square frame-shaped.
Above-mentioned the first rotary module 50 has first follower 56 and that is fixed on this first axle body 54 and is positioned at base plate 22 belows through base plate 22 and the first axle body 54, that is connected in movable framework 30 and is located at the first power pack 52 on pedestal 10 to drive the first follower 56.
In the present embodiment, the first power pack 52 is positioned at the outside of fixed frame 20, it comprise one be fixed on that motor base on pedestal 10 524, is located at that the first motor 522, on motor base 524 is positioned at motor base 524 belows and the first driving wheel 526 of being driven by the first motor 522 and one first Transmission 528 with by transmission of power to the first follower 56 of the first driving wheel 526.First Transmission 528 of the present embodiment is a drive belt, but is not restricted to this, for example, can be gear.As long as above-mentioned the first power pack 52 can drive the first follower 56, can be applicable to the utility model, can be for example that motor coordinates worm gear or accurate screw rod to drive the first follower 56.
After landing, slides to predetermined stop position according to indication by aircraft; for example empty bridge; be to advance along the guide wire of landing ground, the utility model is installed on airport and in the face of guide wire is to scan aircraft and to show the distance of aircraft from predetermined point (SPOT), the scope of its scanning only need to be in predetermined angle.As shown in Figure 3, for the first rotary module 50 of the present utility model is also provided with one first limit assembly 58 to limit the anglec of rotation of movable framework 30 teeters, be also the horizontal surface scanning range of catadioptre group 40.The first limit assembly 58 comprises that the first position-limited wheel 581 and of being located at the first follower 56 bottom surfaces is fixed on the first stop part 582 of pedestal 10, wherein the first position-limited wheel 581, and this first stop part 582 is in order to limit the rotational angle of the first position-limited wheel 581.Can limit by this anglec of rotation of catadioptre group 40 along vertical axis Y.
Above-mentioned the second rotary module 60 comprise one through this second follower 66, one second power pack 62 that one of them of riser 33a, 33b and the second axle body 64, that is connected in this catadioptre group 40 is connected in to this second axle body 64 and is positioned at movable framework 30 outsides to drive this second follower 66.As shown in Figure 1, the second axle body 64 of the present embodiment is through the riser 33a on Fig. 1 right side.Wherein above-mentioned the second power pack 62 comprise one be fixed on this one of them of riser 33a, 33b and the second motor 622, of being positioned at this movable framework 30 are positioned to these movable framework 30 outsides and be connected in the second driving wheel 624 of this second motor 622 and one second Transmission 626 with by the transmission of power of this second driving wheel 624 to this second follower 66.As shown in Figure 1, second motor 622 of the present embodiment is positioned at the riser 33a on Fig. 1 right side.Wherein the second Transmission 626 is a drive belt, but is not restricted to this, for example, can be gear.As long as above-mentioned the second power pack 62 can drive the second follower 66, can be applicable to the utility model, can be for example that motor coordinates worm gear or accurate screw rod to drive the second follower 66.
Refer to Fig. 1 and Fig. 3, second rotary module 60 of the present embodiment further comprises the anglec of rotation of the second limit assembly 68 with restriction catadioptre group 40, is also vertical surface scanning range.The second limit assembly 68 and the second follower 66 are located opposite from the opposite side of movable framework 30, and are positioned at another riser 33b(as shown in Figure 1) lateral surface.Above-mentioned the second limit assembly 68 comprises that one is fixed on the second stop part 682 of another riser 33b with second position-limited wheel 681 and of catadioptre group 40 synchronous rotaries, wherein the second position-limited wheel 681 has sector notch 6810, the second stop parts 682 and is positioned at this sector notch 6810.Can limit by this anglec of rotation of catadioptre group 40 along horizontal shaft X.
Refer to Fig. 1, catadioptre group 40 comprises a catadioptre 42 and is positioned at a pair of crimp 44 of these catadioptre 42 both sides.Catadioptre group 40 is rotatably set up in movable framework 30 along a horizontal shaft X who is parallel to pedestal 10.Referring again to Fig. 3, the catadioptre group 40 of the present embodiment preferably has a supporting plate 46 to hold catadioptre 42, and above-mentioned two the second axle bodies 64 can be to be preferably connected with supporting plate 46 one, are namely stretched out integratedly by the both sides of supporting plate 46.Above-mentioned crimp 44 is pushed down the dual-side of catadioptre 42 and is fixed on supporting plate 46.
Refer to Fig. 1, light source module 70 is fixed on the top board 24 of fixed frame 20, and top board 24 is provided with a perforate 240, and light source module 70 comprises that an optical transmitting set 72 through this perforate 240 and the fixing above-mentioned optical transmitting set 72 of a fixing part 74 are in top board 24.Optical transmitting set 72 preferably provides laser beam, but is not restricted to this.
Referring to Fig. 4 A and Fig. 4 B, is the march into the arena lateral plan of guidance system of aerocraft of the present utility model.By the second rotary module 60, catadioptre group 40 can be rotated along horizontal shaft X, as shown in Figure 4 A, along clockwise rotating an angle Θ x, form as shown in Figure 4 B, the light being sent by light source module 70 by this reflects via catadioptre group 40, and light R can be positioned at along vertical surface scanning the object in front.When object is herein applied to aviation airport, look like for aerocraft.
Referring to Fig. 5 A and Fig. 5 B, is the march into the arena lateral plan of guidance system of aerocraft of the present utility model.By the first rotary module 50, movable framework 30 can rotate along vertical axis Y, as shown in Figure 5A, along rotating counterclockwise an angle Θ y, form as shown in Figure 5 B, the light R that catadioptre group 40 reflects by this can be along the plane that is parallel to pedestal 10, and left and right scanning is positioned at the object in front.
The light reflecting by reception, coordinates the time difference between transmitting and reflection, can calculate the distance of scanned object, applicable to the distance that detects plane distance predetermined point (SPOT).The wherein detection position of light emission and reflection, can be set the distance between each scanning spot, or each angle of scanning.In addition also can set, the covering scope of scanning.When being applied to airport to detect and to guide aerocraft and march into the arena, the scanning range of its setting can be slightly larger than the width and height of maximum aerocraft.Money after receiving and calculating, according to data, also recorded to the distance of different reflection positions, save as a matrix ordered series of numbers.The wherein the most close aerocraft of the present utility model of the aircraft front-end processor nose guidance system of marching into the arena, therefore can learn by data (nearest point) minimum in recognition matrix ordered series of numbers the distance of aerocraft machine nose, by these data values are provided, can revise in real time the direction of aircraft and stop aircraft in correct position for chaufeur again.In addition, by the position of machine nose and with respect to the height on ground, even further comprise the length of both sides wing or the height of empennage, the database data that comparison stores in advance, can identify the type of aircraft.
By the aerocraft of the present utility model guidance system of marching into the arena, only need to pass through a catadioptre group 40, compare prior art, element minimizing.Moreover the configuration of the utility model integral structure is more simplified and taken less space, wherein movable framework 30 is arranged in fixed frame 20, and the second motor 622 major parts are contained in movable framework 30, and the width of entirety is only slightly larger than the width of catadioptre group 40; Mobile and assembling is also very easy to.The utility model is also provided with the limit assembly of limited angular.
In sum, the real important document that has met utility model patent of the utility model is filed an application in accordance with the law.But above disclosed person is only the utility model preferred embodiment, from not limiting claim scope of the present utility model with this, the equalization of therefore doing according to the utility model application range changes or modifies, and still belongs to the scope that the utility model is contained.
Claims (10)
1. the aerocraft guidance system of marching into the arena, is characterized in that, the described aerocraft guidance system of marching into the arena comprises:
One pedestal;
One fixed frame, described fixed frame is fixed on described pedestal;
One movable framework, described movable framework is set up on described fixed frame revolvably along a vertical axis perpendicular to described pedestal;
One catadioptre group, described catadioptre group is set up on described movable framework revolvably along a horizontal shaft that is parallel to described pedestal;
One light source module, described light source module is set up in regularly on described movable framework and the light of catadioptre group described in a directive is provided;
One first rotary module, described the first rotary module along described vertical axis to drive described movable framework; And
One second rotary module, described the second rotary module along described horizontal shaft to drive described catadioptre group.
2. the aerocraft according to claim 1 guidance system of marching into the arena, it is characterized in that, described fixed frame comprises that one is fixed on the top board that the high assembly of frame, on described pedestal is fixed on described base plate on high assembly, is fixed on pair of side plates and on described base plate and is fixed on the top of described pair of side plates, wherein, described movable framework is set up on described base plate revolvably.
3. the aerocraft according to claim 2 guidance system of marching into the arena, it is characterized in that, described the first rotary module has first follower and that is fixed on described the first axle body and is positioned at the below of described base plate through described base plate and the first axle body, that is connected in described movable framework and is located at the first power pack on described pedestal, and described the first power pack drives described the first follower.
4. the aerocraft according to claim 3 guidance system of marching into the arena, it is characterized in that, described the first power pack comprises that one is fixed on motor base, on described pedestal and is located at the first driving wheel and one first Transmission that the first motor, on described motor base is positioned at the below of described motor base and is driven by described the first motor, described the first Transmission by the transmission of power of described the first driving wheel to described the first follower.
5. the aerocraft according to claim 4 guidance system of marching into the arena, is characterized in that, described the first Transmission is a drive belt.
6. the aerocraft according to claim 2 guidance system of marching into the arena, it is characterized in that, described movable framework is U font, described movable framework comprises a transverse slat and is located at a pair of riser at the two ends of described transverse slat, described transverse slat is parallel to described base plate, and the two ends of described catadioptre group can be set up on described a pair of riser rotationally.
7. the aerocraft according to claim 6 guidance system of marching into the arena, it is characterized in that, described the second rotary module comprises the second follower and one second power pack that is connected in described the second axle body and is positioned at the outside of described movable framework through one of them of described a pair of riser and the second axle body, that is connected with described catadioptre group, and described the second power pack drives described the second follower.
8. the aerocraft according to claim 7 guidance system of marching into the arena, it is characterized in that, described the second power pack comprises that second motor, that is fixed on one of them of described a pair of riser and is positioned at described movable framework is positioned at the outside of described movable framework and is connected in the second driving wheel and one second Transmission of described the second motor, described the second Transmission by the transmission of power of described the second driving wheel to described the second follower.
9. the aerocraft according to claim 8 guidance system of marching into the arena, is characterized in that, described the second Transmission is a drive belt.
10. the aerocraft according to claim 7 guidance system of marching into the arena, it is characterized in that, described the second rotary module further comprises an angle limit assembly, described angle limit assembly and described the second follower are located opposite from the opposite side of described movable framework, and described angle limit assembly is positioned at wherein another the lateral surface of described a pair of riser, described angle limit assembly comprise one with the position-limited wheel of described catadioptre group synchronous rotary, and wherein another a stop part that is fixed on a described a pair of riser, wherein, described position-limited wheel has a sector notch, described stop part is positioned at described sector notch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320396624.0U CN203601576U (en) | 2013-07-04 | 2013-07-04 | Aircraft approach guidance system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320396624.0U CN203601576U (en) | 2013-07-04 | 2013-07-04 | Aircraft approach guidance system |
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| Publication Number | Publication Date |
|---|---|
| CN203601576U true CN203601576U (en) | 2014-05-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320396624.0U Expired - Lifetime CN203601576U (en) | 2013-07-04 | 2013-07-04 | Aircraft approach guidance system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016015545A1 (en) * | 2014-08-01 | 2016-02-04 | 深圳中集天达空港设备有限公司 | System and method for aircraft docking guidance and aircraft type identification |
-
2013
- 2013-07-04 CN CN201320396624.0U patent/CN203601576U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016015545A1 (en) * | 2014-08-01 | 2016-02-04 | 深圳中集天达空港设备有限公司 | System and method for aircraft docking guidance and aircraft type identification |
| US10562644B2 (en) | 2014-08-01 | 2020-02-18 | Shenzhen Cimc-Tianda Airport Support Ltd. | System and method for aircraft docking guidance and aircraft type identification |
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Granted publication date: 20140521 |
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| CX01 | Expiry of patent term |