WO2015035893A1 - 用来调节飞机着陆灯安装角度的装置和方法 - Google Patents

用来调节飞机着陆灯安装角度的装置和方法 Download PDF

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Publication number
WO2015035893A1
WO2015035893A1 PCT/CN2014/086111 CN2014086111W WO2015035893A1 WO 2015035893 A1 WO2015035893 A1 WO 2015035893A1 CN 2014086111 W CN2014086111 W CN 2014086111W WO 2015035893 A1 WO2015035893 A1 WO 2015035893A1
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Prior art keywords
laser emitter
bracket
laser
base
angle
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PCT/CN2014/086111
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English (en)
French (fr)
Inventor
王佳
刘洪涛
朱志胜
杨文�
钟军
窦连财
赵健
Original Assignee
中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
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Publication of WO2015035893A1 publication Critical patent/WO2015035893A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
    • G01B11/27—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes
    • G01B11/272—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes using photoelectric detection means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B64D47/04—Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead

Definitions

  • the present invention relates to a device for adjusting the installation angle of an aircraft landing light. Further, the present invention relates to a method for adjusting the installation angle of an aircraft landing light. Background technique
  • the aircraft landing lights are important external lighting equipment for the aircraft. When the aircraft is landing in the night flight state, the landing lights need to provide enough light to illuminate the landing site, so that the pilot can clearly visually compare the relative position of the aircraft and the runway and the flight altitude. , and can safely maneuver the aircraft landing and ground taxiing. Therefore, landing lights are one of the factors that affect the safe operation of aircraft.
  • the landing lights of aircraft mainly use high-intensity spotlights, which have high requirements for installation accuracy. If there is a slight deviation in the installation angle of the landing light, it will result in poor lighting in the main lighting area of the landing light, which will bring hidden danger to the safety of the aircraft.
  • the main lighting area requiring a landing light is in the 300 to 1200 foot area in front of the pilot.
  • a goniometer to measure the installation angle of the landing lights. As shown in Fig. 1, generally, an angle ⁇ is formed between the normal N of the landing lamp 2 and the horizontal axis H, and the angle ⁇ is measured by a goniometer (not shown), and according to The measured angle is used to adjust the installation angle of the landing light.
  • the beam is measured with a light meter device.
  • a light measuring device 3 is placed at a target position in front of the landing light 2.
  • the photometer device includes a plurality of photometers, and the photometers are arranged in a cruciform structure to form a target.
  • adjust the installation angle of the landing light fixture so that the beam or beam centerline ⁇ is displayed on the bull's-eye. Thereby, the landing light is mounted at the desired angle.
  • the measuring principle of the goniometer is based on gravity to determine the angle between the normal ⁇ of the luminaire and the horizontal axis ⁇ . Since the direction of gravity always points in the vertical direction, the goniometer can only measure the pitch angle of the landing light, and it is impossible to measure the roll angle of the lamp. Therefore, adjust the landing angle of the landing light with a goniometer In the case of the landing light, the pitch angle of the landing light can only be adjusted, and the roll angle of the landing light is not guaranteed.
  • the photometer device must be composed of a plurality of photometers, so that it is expensive to manufacture and inconvenient to operate in the field.
  • the present invention has been made to solve the above problems in the prior art, and an object thereof is to provide an apparatus and method for adjusting an installation angle of an aircraft landing light so that the adjustment of the installation angle of the landing lamp is conspicuous and easy to measure.
  • an apparatus for adjusting an installation angle of an aircraft landing light includes: a base including a rotating member and a fixed member, the rotating member being rotatable relative to the fixed member; the bracket, the bracket being a hollow cylinder, and being fixed On the rotating component; the laser emitter, the laser emitter is provided with a laser exit hole at a first end thereof, and the second end of the laser emitter passes through the bracket and is fixedly connected to the rotating component; wherein an adjustment mechanism is disposed on the bracket Used to adjust the angle of the laser emitter relative to the base.
  • the adjusting mechanism is specifically configured to include a screw inserted into the wall of the bracket, the screw extending into the interior of the bracket and abutting against the laser emitter, and adjusting the distance of the screw into the interior of the bracket to adjust the laser emitter relative to the base Angle.
  • the central portion of the rotating member is provided with a circular groove, and the second end of the laser emitter is inserted into the circular groove.
  • a bushing is provided between the second end of the laser emitter and the circular groove and/or between the laser emitter and the adjustment mechanism.
  • the bushing is a rubber ring.
  • the bracket is fixed to the rotating member by screws and nuts.
  • the rotating member is a rotating disk
  • the fixing member is a rotating groove
  • the rotating plate is rotatably fitted in the rotating groove
  • the laser emitter is arranged such that the laser emitted by the laser emitter can clearly show the central trajectory of the landing light beam, whereby the landing can be clearly seen from the indication of the laser emitted by the laser emitter
  • the current installation state of the lamp and the angle of installation of the landing lights can be easily adjusted.
  • the apparatus of the present invention is provided with an adjustment mechanism and a base composed of a rotating member and a fixed member. By rotating the rotating member relative to the fixed member, the angle of the laser emitter relative to the base can be judged The degree of relationship, and thus the apparatus of the present invention, can be calibrated using an adjustment mechanism.
  • a method of adjusting an installation angle of an aircraft landing light is carried out by the apparatus of the invention described above, the method comprising the steps of: a. fixing the apparatus to a light exiting plane of the landing light; b. Before or after step a, the angle of the laser emitter relative to the base is adjusted by the adjustment mechanism until the laser emitter is perpendicular to the base; c. adjusting the installation angle of the landing light until the projection of the laser emitted by the laser emitter on the ground Located at the desired location.
  • step b comprises: d. rotating the component with the laser emitter and the bracket together with respect to the stationary component while observing the projection point of the laser emitted by the laser emitter on a distant object; e. if the laser emitter The projection point of the emitted laser on the distant object changes with the rotation of the rotating member, and the angle of the laser emitter relative to the base is adjusted by the adjustment mechanism; f. Repeat steps d and e until the laser emitted by the laser emitter The projection point on the distant object no longer changes with the rotation of the rotating member.
  • Fig. 1 schematically shows a method for adjusting the installation angle of a landing light in the prior art.
  • Fig. 2 schematically shows another method for adjusting the installation angle of a landing light in the prior art.
  • 3 is an exploded perspective view of the apparatus for adjusting the installation angle of an aircraft landing light of the present invention.
  • Figure 4 is a partial enlarged view of the apparatus for adjusting the installation angle of an aircraft landing light of the present invention after assembly.
  • Figure 5 is a schematic illustration of a method of adjusting the installation angle of an aircraft landing light of the present invention.
  • Fig. 6 is a diagram showing the principle of adjusting the laser emitter, showing a case where the laser emitter is at an acute angle with the base.
  • Fig. 7 is a diagram showing the principle of adjusting the laser emitter, showing the case where the laser emitter is at an obtuse angle with the base.
  • Fig. 8 is a diagram showing the principle of adjusting the laser emitter, in which the case where the laser emitter is perpendicular to the base is shown. detailed description
  • Fig. 3 shows an exploded perspective view of the apparatus 1 for adjusting the installation angle of an aircraft landing light of the present invention.
  • the apparatus 1 mainly includes a laser emitter 20, a bracket 30, and a base 50.
  • the bracket 30 shown in Fig. 3 is a hollow cylinder in the shape of a quadrangular prism.
  • a fin 310 is disposed on each of the four side walls of the bracket, and a tab 311 is fixed on each side of each fin by means of splicing or the like, and a through hole is formed in the tab.
  • through holes are also provided in the base 50 (eight shown in Fig. 3).
  • the screw 120 is passed through the through hole of the base 50 and the tab 311 and cooperates with the nut 110 to fix the bracket 30 to the base 50.
  • the laser emitter 20 is provided with a laser exit aperture 21 at its first end, and the second end of the laser emitter 20 opposite the first end passes through the hollow bracket 30 and is inserted into a circular slot 51 at the center of the base 50.
  • a bushing 40 is provided between the circular groove 51 and the second end of the laser emitter 20 to assist in securing the laser emitter 20 within the circular groove 51.
  • the bushing 40 can also be in the form of a rubber ring or the like.
  • a through hole is provided in each of the four side walls of the bracket 30, and the screw 70 is from the outer side of the side wall The through hole is inserted and reaches the inner side of the side wall. Also, on the inner side of the side wall, a number of nuts 100 corresponding to the number of screws 70 are provided for receiving the screws 70.
  • a bushing 10 is provided between the nut 100 and the first end of the laser emitter 20 to enable the nut 100 to better secure the laser emitter 20.
  • the bushing 10 can also be in the form of a rubber ring or the like.
  • a washer 80 can be provided for each of the screws 70, and the gap between the screws 70 and the bracket 30 can be filled with the washer 80 for better fixing.
  • FIG. 4 there is shown a partial enlarged view of the apparatus 1 of the present invention after assembly.
  • the portion shown in FIG. 4 is the first end of the laser emitter 20 provided with the laser exit hole 21 and the portion of the bracket 30 corresponding to the first end.
  • the portion of the screw 70 that passes through the through hole in the bracket 30 and into the interior of the bracket 30 abuts against the bushing 10, thereby holding the laser emitter 20 in place.
  • the distance by which the respective screws 70 protrude from the inside of the side walls can be adjusted, thereby achieving adjustment of the laser emitter 20, specifically, adjusting the angle of the laser emitter 20 with respect to the base 50.
  • the base 50 of the apparatus 1 includes a rotary disk 52 and a rotary groove 53.
  • a circular groove 51 for fixing the second end of the laser emitter 20 is disposed on the center of the rotary disk 52, and the bracket 30 is also fixed to the rotary disk 52.
  • the rotary disk 52 is rotatably fitted in the rotary groove 53.
  • the rotary disk 52 can be rotated relative to the rotary slot 53 with the laser transmitter 20 and the bracket 30.
  • the overall structure of the apparatus 1 for adjusting the installation angle of an aircraft landing light of the present invention has been specifically described above.
  • the structures disclosed above are exemplary, and some of the specific details of the above-described structures may be modified to achieve the objects of the present invention.
  • the bracket 30 is shown in the form of a hollow cylinder in the shape of a quadrangular prism.
  • the bracket 30 may have other shapes such as a cylindrical shape, a triangular prism shape, and the like.
  • the number of the screws 70 for fixing and adjusting the laser emitter 20 may not necessarily be four as shown in Fig. 3, but may be any number as needed.
  • the number of washers and nuts corresponding to the screws 70 can also vary accordingly.
  • the means for adjusting the angle of the laser emitter 20 relative to the base 50 includes four screws 70 and a corresponding number of nuts 100 and washers 80 and the like.
  • other types of adjustment mechanisms can be employed to adjust the laser emitter 20.
  • a spacer may be inserted between the laser emitter 20 and the inner wall of the bracket 30 to fix the laser emitter 20, and at the same time, by increasing or decreasing the number of spacers at different directions of the laser emitter 20, the laser emitter 20 can be realized. Adjustment.
  • the adjustment and adjustment of the laser emitter 20 can be accomplished using other adjustment mechanisms known to those skilled in the art.
  • the mechanism for adjusting the laser emitter 20 does not have to be provided corresponding to the first end of the laser emitter 20 in which the laser exit hole 21 is provided, but may be provided corresponding to any one of the laser emitters 20.
  • a structure such as the flap 310, the tab 311, and the screw 120 is provided.
  • a flange may be provided at one end of the cylindrical bracket 30, and then the bracket 30 may be secured to the base 50 by flanges by various means known in the art, such as screws, splicing, snapping, and the like.
  • the number of screws used and their corresponding nuts may not necessarily be eight as shown in Fig. 3, but may be any number as needed.
  • bushings 10, 40 are provided at both ends of the laser emitter 20, respectively, to facilitate fixing the laser emitter 20.
  • the bushings 10, 40 herein are optional.
  • an interference fit can be employed between the second end of the laser emitter 20 and the circular groove 51 on the base 50 so that no bushing is required between them.
  • a connecting portion may be provided on the second end of the laser emitter 20, and the second end may be directly fixed to the base 50 by screws, splicing or the like, so that the circular groove 51 need not be provided on the base 50.
  • a screw 70 or other form of adjustment mechanism can be in direct contact with the laser emitter 20 without the need to provide a bushing therebetween .
  • the base 50 includes a rotary groove 53 and a rotary disk 52 to which the laser emitter 20 and the holder 30 are fixed, and the rotary disk 52 can be rotated with respect to the rotary groove 53 with the laser emitter 20 and the holder 30.
  • a circular groove may be formed in the bottom surface of the rotary disk 52, and correspondingly, a disk-shaped fixing member is provided, on which a circular protrusion corresponding to the circular groove is formed, through the circular groove and the circular protrusion The cooperation between the rotating discs allows the rotating disc to rotate relative to the fixed member.
  • the device 1 is fixed to the light exiting surface of the landing lamp 2, for example by bonding, mechanical connection or the like.
  • the laser emitter 20 will emit a laser that indicates the trajectory of the center of the beam. Therefore, the adjustment of the installation angle of the landing lamp can be achieved by simply projecting the laser light emitted from the laser emitter 20 onto a desired position on the ground. The projected position of the desired laser on the ground can be determined in the following manner.
  • the landing lamp is expected to have an installation angle of ⁇ .
  • the height h of the landing lamp is measured.
  • the distance AP between the desired projection position A and the projection point P of the landing lamp 2 on the ground can be obtained by the following formula.
  • Out: AP h/tanp.
  • the position of the point A can be determined.
  • the laser emitter 20 In order to ensure that the landing light installation angle is adjusted, in order to ensure that the laser light emitted by the laser emitter 20 represents the light beam of the land light, the laser emitter 20 is required to be at a specific angle with respect to the base 50. Typically, the laser emitter 20 needs to be adjusted perpendicular to the base 50.
  • the adjustment principle of the laser emitter 20 is as follows.
  • the rotating member of the base 50 e.g., the rotating disk 52
  • the stationary member e.g., the rotating groove 53
  • the trajectory of the projection point of the laser light emitted from the laser emitter 20 on the distant object is observed. If the angle ⁇ of the laser emitter 20 with respect to the base 50 is an acute angle, as shown in FIG. 6, the projection of the laser light emitted by the laser emitter 20 on a distant object during the rotation of the rotating member of the base 50 The point will move from point to point A'.
  • angle ⁇ of the laser emitter 20 with respect to the base 50 is an obtuse angle, as shown in FIG. 7, the projection of the laser light emitted by the laser emitter 20 on a distant object during the rotation of the rotating member of the base 50 The point will move from point A' to point.
  • the adjusting mechanism is constituted by the screw 70
  • the angle of the laser emitter 20 with respect to the base 50 is adjusted by screwing in and out the respective screws 70.
  • the laser emitter 20 When the laser emitter 20 is adjusted to be perpendicular to the base 50, as shown in Fig. 8, as the rotating member of the base 50 rotates, the projection point of the laser light emitted from the laser emitter 20 on the distant object will remain unchanged. .
  • the adjustment of the laser emitter 20 may be performed before the device 1 is mounted on the landing lamp 2, or may be performed after the device 1 is mounted on the landing lamp 2.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Lighting Device Outwards From Vehicle And Optical Signal (AREA)

Abstract

一种用于调节飞机着陆灯安装角度的装置和方法，其中，该装置（1）包括：底座（50），底座（50）包括旋转部件（52）和固定部件（53），旋转部件（52）可相对于固定部件（53）转动；支架（30），为中空筒体，且固定于旋转部件（52）上；激光发射器（20），其第一端上设置有激光出射孔（21），该激光发射器（20）的第二端穿过支架（30）并固定连接于旋转部件（52）；在支架（30）上设置有调节机构（70），以用于调节激光发射器（20）相对于底座（50）的角度。通过该装置和方法，可以容易和明显地调节飞机着陆灯的安装角度。

Description

用来调节飞机着陆灯安装角度的装置和方法 技术领域
本发明涉及一种用来调节飞机着陆灯安装角度的装置， 进一步地， 本发明还 涉及一种用来调节飞机着陆灯安装角度的方法。 背景技术
飞机着陆灯是飞机的重要外部照明设备， 飞机在夜航状态下着陆时， 需要由 着陆灯来提供足够的光线来照明着陆场地， 从而使飞行员能够清晰地目测飞机与 跑道的相对位置以及飞行高度， 并能够安全地操纵飞机着陆以及地面滑行。 因此， 着陆灯是影响飞机安全运行的因素之一。
目前，飞机的着陆灯主要采用高光强度的聚光灯，对安装精度有较高的要求。 如果着陆灯的安装角度有微小偏差， 则将导致在着陆灯的主要照明区域内的照明 效果不佳， 从而给飞机的安全性带来隐患。 通常来说， 需要着陆灯的主要照明区 域在飞行员前方 300至 1200英尺的区域。
目前， 用来调节着陆灯安装角度的方法主要有以下两种。
1) 用测角仪来测量着陆灯的安装角度。 如图 1 所示， 通常来说， 着陆灯 2 的灯具法线 N与水平轴线 H之间会形成一个夹角 α， 用一个测角仪 （未示出） 来 测量该夹角 α， 并根据所测量出的角度来调整着陆灯的安装角度。
2) 用光测定仪装置来测量光束。如图 2所示， 在着陆灯 2前方的一个目标位 置放置一个光测定仪装置 3。 该光测定仪装置包括多个光测定仪， 将这些光测定 仪布置成十字形的结构， 从而形成靶子。 在安装过程中， 调整着陆灯的灯具安装 角度， 使光束或者说光束中心线 Μ显示在靶心上。 由此， 将着陆灯安装在所需要 的角度上。
现有技术的上述两种方法有其固有的缺点。
对于第一种方法，测角仪的测量原理是基于重力来确定灯具法线 Ν与水平轴 线 Η之间的夹角。 由于重力方向始终指向铅直的方向， 用测角仪只能测量着陆灯 的俯仰角度， 无法测量灯具的横滚角度。 因此， 在用测角仪调整着陆灯安装角度 的情形中， 只能调整着陆灯的俯仰角度， 而着陆灯的横滚角度得不到保障。
对于第二种方法， 如以上所提到的， 光测定仪装置须由多个光测定仪组合而 成， 因此其制造成本高， 且不便于在外场进行操作。
因此， 需要提供一种用来调节飞机着陆灯安装角度的装置和方法， 其能够减 少对着陆灯安装角度调整的工作量， 同时又能够保证安装角度调整的精度。 发明内容
本发明是为了解决现有技术中的上述问题而作出的， 其目的在于提供一种用 于调节飞机着陆灯安装角度的装置和方法， 以使对着陆灯的安装角度的调节明显 且便于度量。
根据本发明的一个方面， 一种用于调节飞机着陆灯安装角度的装置包括： 底 座， 底座包括旋转部件和固定部件， 旋转部件可相对于固定部件转动； 支架， 支 架为中空筒体， 且固定于旋转部件上； 激光发射器， 激光发射器的第一端上设置 有激光出射孔， 激光发射器的第二端穿过支架并固定连接于旋转部件； 其中， 在 支架上设置有调节机构， 以用于调节激光发射器相对于底座的角度。
较佳地， 调节机构的具体结构为， 包括插入支架的壁的螺钉， 螺钉伸入支架 的内部并抵靠激光发射器， 通过调节螺钉伸入支架的内部的距离， 调节激光发射 器相对于底座的角度。
较佳地，旋转部件的中心部位设置有圆槽，激光发射器的第二端插入圆槽中。 较佳地，在激光发射器的第二端与圆槽之间和 /或在激光发射器与调节机构之 间设置衬套。 其中， 衬套为橡胶圈。
较佳地， 支架由螺钉和螺母固定于旋转部件上。
较佳地， 旋转部件为旋转盘， 固定部件为旋转槽， 旋转盘可转动地嵌装于旋 转槽中。
通过本发明的装置， 设置激光发射器， 从而激光发射器发出的激光可以明确 地示出着陆灯光束的中心轨迹， 由此， 根据激光发射器所发出的激光的指示， 可 以明显地看出着陆灯的当前的安装状态， 并可容易地调节着陆灯的安装角度。
而且， 本发明的装置设置有调节机构以及由旋转部件和固定部件构成的底 座。 通过旋转部件相对于固定部件的转动， 可以判断激光发射器相对于底座的角 度关系， 并由此可利用调节机构对本发明的装置进行校准。
根据本发明的另一方面， 一种调节飞机着陆灯安装角度的方法由以上所述本 发明的装置来实施，该方法包括如下步骤： a. 将装置固定到着陆灯的出光平面上； b. 在步骤 a之前或之后， 通过调节机构来调节激光发射器相对于底座的角度， 直 到激光发射器垂直于底座； c. 调节着陆灯的安装角度， 直到激光发射器发出的激 光在地面上的投影位于所期望的位置上。
较佳地， 步骤 b包括： d. 是旋转部件带着激光发射器和支架一起相对于固定 部件旋转， 同时观察激光发射器发出的激光在远处物体上的投影点； e. 若激光发 射器发出的激光在远处物体上的投影点随着旋转部件的旋转而变化， 则通过调节 机构来调节激光发射器相对于底座的角度； f. 重复步骤 d和 e， 直到激光发射器 发出的激光在远处物体上的投影点不再随旋转部件的旋转而变化。
可以看到， 本发明的方法易于实施， 且能够精确地调节着陆灯的安装角度。 附图说明
图 1示意性地示出了现有技术中用来调节着陆灯安装角度的一种方法。
图 2示意性地示出了现有技术中用来调节着陆灯安装角度的另一种方法。 图 3是本发明的用于调节飞机着陆灯安装角度的装置的立体分解图。
图 4是本发明的用于调节飞机着陆灯安装角度的装置在组装好之后的局部放 大图。
图 5是本发明的用于调节飞机着陆灯安装角度的方法的示意图。
图 6是示出了调节激光发射器的原理的简图， 其中显示的是激光发射器与底 座呈锐角的情形。
图 7是示出了调节激光发射器的原理的简图， 其中显示的是激光发射器与底 座呈钝角的情形。
图 8是示出了调节激光发射器的原理的简图， 其中显示的是激光发射器垂直 于底座的情形。 具体实施方式
下面， 为便于理解本发明， 将结合附图对本发明的具体实施例进行说明。 需 要说明的是， 附图中所示的只是本发明的优选实施方式， 相关领域中的技术人 员可以对其中的细节作各种等效变换，而这些等效变换同样在本发明所要求的 保护范围之内。
下面，先对本发明的用于调节飞机着陆灯安装角度的装置的具体结构进行描 述。
<总体结构>
图 3示出了本发明的用于调节飞机着陆灯安装角度的装置 1的立体分解图。 如图 3所示， 装置 1主要包括激光发射器 20、 支架 30和底座 50。 图 3中所示的 支架 30 为四棱柱形状的中空筒体。 在支架的四个侧壁中的每一个上设置有翼片 310， 通过悍接等方式， 在每个翼片的两侧分别固定有突片 311， 在该突片上设置 有通孔。对应于突片 311上的通孔， 在底座 50上也设置有通孔（图 3中所示的是 八个） 。 用螺钉 120穿过底座 50和突片 311上的通孔， 并与螺帽 110相配合， 从 而将支架 30固定于底座 50上。
激光发射器 20的第一端上设置有激光出射孔 21，激光发射器 20与第一端相 对的第二端则穿过中空的支架 30， 并插入底座 50中心处的圆槽 51中。 较佳地， 在圆槽 51和激光发射器 20的第二端之间可设置衬套 40， 从而有助于将激光发射 器 20固定于圆槽 51之中。 衬套 40的形式也可以是橡胶圈或类似部件。 在支架 30与激光发射器 20的第一端、即设置有激光出射孔 21的那一端相对应的位置处， 在支架 30的四个侧壁上分别设置通孔， 螺钉 70从侧壁的外侧插入该通孔， 并到 达侧壁的内侧。 并且， 在侧壁的内侧， 设置与螺钉 70的数量相对应的数量的螺母 100， 用以接纳螺钉 70。
较佳地， 在螺母 100与激光发射器 20的第一端之间可设置衬套 10， 以使螺 母 100能够更好地固定激光发射器 20。 同样地， 该衬套 10的形式也可以是橡胶 圈或类似部件。 而且， 可以对每个螺钉 70设置垫圈 80， 利用垫圈 80来填充螺钉 70和支架 30之间的间隙， 以更好地进行固定。
参见图 4， 其中示出了本发明的装置 1在组装好之后的局部放大图。 具体来 说， 图 4所示出的部分是激光发射器 20的设置有激光出射孔 21的第一端以及支 架 30与该第一端相对应的部分。从图 4中可以看到， 螺钉 70穿过支架 30上的通 孔而进入支架 30内部的部分抵靠在衬套 10上， 从而将激光发射器 20固定在位。 此外， 通过旋转各个螺钉 70， 可以调节各个螺钉 70突出于侧壁内侧的距离， 从 而实现对激光发射器 20 的调节， 具体来说是调节激光发射器 20相对于底座 50 的角度。
回到图 3， 可以看到， 装置 1的底座 50包括旋转盘 52和旋转槽 53。 用来固 定激光发射器 20的第二端的圆槽 51设置在旋转盘 52的中心上， 并且支架 30也 固定在旋转盘 52上。 旋转盘 52则可旋转地嵌装在旋转槽 53 中。 从而， 旋转盘 52可带着激光发射器 20和支架 30—起相对于旋转槽 53转动。
<变形例 >
以上对本发明的用于调节飞机着陆灯安装角度的装置 1的总体结构进行了具 体说明。 以上所公开的结构是示例性的， 可以对上述结构中的一些具体细节进行 改变， 同样能够实现本发明的目的。
图 3中显示支架 30的形式为呈四棱柱形状的中空筒体。 除此之外， 支架 30 还可呈其它的形状， 例如圆筒形、 三棱柱形等等。 相对应地， 用来固定和调节激 光发射器 20的螺钉 70的数量也可不必是图 3中所示的四个， 而是可以按照实际 需要而为任意数量。从而，与螺钉 70相对应的垫圈和螺母的数量也可相应地变化。
在上述公开的结构中， 用来调节激光发射器 20相对于底座 50的角度的装置 包括四个螺钉 70以及相应数量的螺母 100和垫圈 80等。 当然， 也可采用其它形 式的调节机构来调节激光发射器 20。 例如， 可以在激光发射器 20和支架 30的内 壁之间插入垫片， 以固定激光发射器 20， 同时， 通过增减激光发射器 20不同方 向处的垫片数量， 可以实现对激光发射器 20的调节。 或者， 也可采用本领域技术 人员已知的其它调节机构来实现对激光发射器 20的固定和调节。而且， 用来调节 激光发射器 20的机构也不必对应于激光发射器 20中设置了激光出射孔 21的第一 端来设置， 而是可以对应于激光发射器 20的任意一个部分设置。
在上述公开的结构中， 为了将支架 30固定到底座 50， 设置了翼片 310、 突 片 311和螺钉 120等结构。 当然， 也可采用其它方式来固定支架 30。 例如， 可以 在呈筒状的支架 30的一端设置凸缘， 然后通过螺钉、悍接， 卡接等各种本领域已 知的方式通过凸缘将支架 30固定到底座 50上。 而且， 在使用螺钉的情形中， 所 使用的螺钉及其对应的螺母的数量也可不必是图 3中所示的八个， 而是按照实际 需要可以为任意数量。 在上述公开的结构中， 在激光发射器 20的两端分别设置有衬套 10、 40， 以 利于固定激光发射器 20。 应当知道， 此处的衬套 10、 40是可选的。 例如， 激光 发射器 20的第二端与底座 50上的圆槽 51之间可以采用过盈配合，从而无需在它 们之间插入衬套。 甚至， 可以在激光发射器 20的第二端上设置连接部， 并且通过 螺钉、 悍接等方法将该第二端直接固定到底座 50上， 从而无需在底座 50上设置 圆槽 51。 此外， 对于激光发射器 20的第一端， 通过适当地选择激光发射器 20外 壳的材料， 螺钉 70或其它形式的调节机构可以与激光发射器 20直接接触， 而无 需在它们之间设置衬套。
在上述公开的结构中， 底座 50包括旋转槽 53和固定有激光发射器 20和支 架 30的旋转盘 52， 旋转盘 52可带着激光发射器 20和支架 30—起相对于旋转槽 53转动。 但是， 也可采用其它结构来使激光发射器 20和支架 30可转动。 例如， 可在旋转盘 52的底面形成圆形槽， 相对应地， 提供一个盘形的固定部件， 其上形 成有对应于该圆形槽的圆形突起， 通过圆形槽和圆形突起之间的配合， 使旋转盘 可相对于固定部件旋转。
<着陆灯安装角度的调节方法 >
下面， 将结合图 5— 8对着陆灯安装角度的调节方法进行说明。
如图 5所示， 将装置 1固定在着陆灯 2的出光平面上， 例如通过粘接、 机械 连接等方式。 激光发射器 20将发出激光， 该激光指示出光束中心的轨迹。 因此， 通过简单地将激光发射器 20发出的激光投射到地面上的期望位置上，就能实现对 着陆灯安装角的调节。 所期望的激光在地面上的投射位置可由以下方式来确定。
如图 5所示， 着陆灯预期安装角度为 β， 首先测量着陆灯的高度 h， 这样， 所期望的投射位置 A到着陆灯 2在地面上的投影点 P之间的距离 AP可由以下公 式得出： AP=h/tanp。 由此， 根据所得到的 AP的值， 可以确定点 A的位置。
在调节着陆灯安装角度时， 为了保证激光发射器 20所发射出的激光代表着 陆灯的光束， 需使激光发射器 20相对于底座 50处于特定的角度。 通常， 需要将 激光发射器 20调节成垂直于底座 50。 激光发射器 20的调节原理如下所述。
在将装置 1组装好之后， 使底座 50的旋转部件 （如旋转盘 52) 带着激光发 射器 20和支架 30—起相对于固定部件 （如旋转槽 53 ) 旋转。 此时， 观察激光发 射器 20发出的激光在远处物体上的投影点的轨迹。 如果激光发射器 20相对于底座 50所呈的角度 γ为锐角时， 如图 6所示， 则 在底座 50的旋转部件的转动过程中， 激光发射器 20发出的激光在远处物体上的 投影点将从点 Α运动到点 A'的位置。
如果激光发射器 20相对于底座 50所呈的角度 γ为钝角时， 如图 7所示， 则 在底座 50的旋转部件的转动过程中， 激光发射器 20发出的激光在远处物体上的 投影点将从点 A'运动到点 Α的位置。
当激光发射器 20发出的激光在远处物体上的投影点如图 6或图 7所示地移 动时， 则说明需要对激光发射器 20进行调节。 例如， 在由螺钉 70构成调节机构 的情况下， 通过旋进和旋出各个螺钉 70， 来调节激光发射器 20相对于底座 50的 角度。
当将激光发射器 20调节成垂直于底座 50时， 则如图 8所示， 随着底座 50 的旋转部件的转动， 激光发射器 20 发出的激光在远处物体上的投影点将保持不 变。
需要说明的是， 对激光发射器 20的调节可以是在将装置 1安装到着陆灯 2 上之前进行， 也可以是在将装置 1安装到着陆灯 2上之后进行。

Claims

权利要求
1.一种用于调节飞机着陆灯安装角度的装置， 其特征在于， 所述装置包括： 底座， 所述底座包括旋转部件和固定部件， 所述旋转部件可相对于所述固定 部件转动；
支架， 所述支架为中空筒体， 且固定于所述旋转部件上；
激光发射器， 所述激光发射器的第一端上设置有激光出射孔， 所述激光发射 器的第二端穿过所述支架并固定连接于所述旋转部件；
其中， 在所述支架上设置有调节机构， 以用于调节所述激光发射器相对于所 述底座的角度。
2. 如权利要求 1所述的装置， 其特征在于， 所述调节机构包括插入所述支架 的壁的螺钉， 所述螺钉伸入所述支架的内部并抵靠所述激光发射器， 通过调节所 述螺钉伸入所述支架的内部的距离，调节所述激光发射器相对于所述底座的角度。
3. 如权利要求 1所述的装置， 其特征在于， 所述旋转部件的中心部位设置有 圆槽， 所述激光发射器的所述第二端插入所述圆槽中。
4. 如权利要求 3所述的装置， 其特征在于， 在所述激光发射器的所述第二端 与所述圆槽之间和 /或在所述激光发射器与所述调节机构之间设置衬套。
5. 如权利要求 4所述的装置， 其特征在于， 所述衬套为橡胶圈。
6. 如权利要求 1所述的装置， 其特征在于， 所述支架由螺钉和螺母固定于所 述旋转部件上。
7. 如权利要求 1所述的装置， 其特征在于， 所述旋转部件为旋转盘， 所述固 定部件为旋转槽， 所述旋转盘可转动地嵌装于所述旋转槽中。
8. 一种调节飞机着陆灯安装角度的方法， 其特征在于， 所述方法由如权利要 求 1一 7中任一项所述的装置来实施， 包括如下步骤：
a. 将所述装置固定到所述着陆灯的出光平面上；
b. 在步骤 a之前或之后，通过所述调节机构来调节所述激光发射器相对于所 述底座的角度， 直到所述激光发射器垂直于所述底座；
c 调节所述着陆灯的安装角度，直到所述激光发射器发出的激光在地面上的 投影位于所期望的位置上。
9. 如权利要求 8所述的方法， 其特征在于， 步骤 b包括：
d. 是所述旋转部件带着所述激光发射器和所述支架一起相对于所述固定部 件旋转， 同时观察所述激光发射器发出的所述激光在远处物体上的投影点； e. 若所述激光发射器发出的所述激光在所述远处物体上的投影点随着所述 旋转部件的旋转而变化， 则通过所述调节机构来调节所述激光发射器相对于所述 底座的角度；
f. 重复步骤 d和 e， 直到所述激光发射器发出的所述激光在所述远处物体上 的投影点不再随所述旋转部件的旋转而变化。
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