CN102121661B - Reflecting face cover for navigation lamp and navigation lamp using same - Google Patents

Abstract

The invention discloses a navigation lamp. The navigation lamp comprises a light source, a transparent lamp shade, a reflecting face cover and a bottom plate, wherein the reflecting face cover and the transparent lamp shade are connected into a whole and are fixed on the bottom plate together; the light source is arranged on the bottom plate and is close to the reflecting face cover; light rays emitted by the light source are reflected by the reflecting face cover and then emitted from the transparent lamp shade. The navigation lamp has a compact structure, and reduces pneumatic influence on the premise of ensuring light distribution.

Description

A kind of for the reflection face shield of navigation lights and the navigation lights that uses this reflection face shield

Technical field

The present invention relates to a kind of aviation lighting field, more particularly, relate to a kind of structural design of navigation lights.

Background technology

In the aircraft field, navigation lights is used for the heading of sign aircraft, and aircraft provides sail information around giving.In general, the navigation lights system must comprise forward position light, after steaming light, and wherein forward position light is comprised of left red light and right green light, between spacing as far as possible large, after steaming light then is white lamp.

Present navigation lights product comprises two large classes take Halogen lamp LED or LED as light source, wherein led light source have efficiently, the characteristics such as long-life, high reliability, so the LED navigation lights is just becoming the trend of navigation lights development.

For satisfying airworthiness requirement, use the after steaming light of white light LEDs usually to be installed in aircraft tail bone end, and the exhaust outlet of close APU (Auxiliary Power Units, accessory power system).When adopting traditional APU muffler, the temperature of this position is usually about 100 ℃.For traditional Halogen lamp LED, remain acceptable at such temperature conditions.Along with the development of technology, the client is more and more stricter to the requirement of Aircraft noise index, and this forces aircraft to gradually adopt integrated muffler.This muffler is the cavity of tail bone back segment integral body as muffler, however at this moment near the temperature the exhaust outlet will be up to 200 ℃ about, this temperature has surpassed the common operating temperature of Halogen lamp LED.And led light source is a kind of to the highstrung light source of temperature, its in when normal operation environment temperature generally can not be higher than 90 ℃, so for led light source, more can't bear so high temperature.Even by certain provision for thermal insulation the temperature of light source installation site is dropped to suitable scope, the corresponding electric wiring in lamp source also is very difficult.Therefore need to consider at APU both sides installation after steaming light.

Yet if existing after steaming light is installed in the afterbody both sides, the light distribution of navigation lights can't reach the requirement of airworthiness regulation.

Summary of the invention

The present invention relates to a kind of reflection face shield for navigation lights, after this face shield and navigation lights are fitted together, can so that described navigation lights is of compact construction, and guarantee to reduce aerodynamic effects under the photodistributed prerequisite.

For achieving the above object, the invention provides a kind of reflection face shield for navigation lights, this reflection face shield receives the light that described navigation lights light source sends and this light reflection is gone out, wherein, the reflecting surface of described reflection face shield forms around the axis three-dimensional rotation by curve R, in cylindrical coordinates system (R, φ), described curve R is denoted as R (φ), wherein:

R=constexp (∫ tan α d φ)=R (φ) and P _i(φ) d φ=P ₀(θ) d θ; Wherein,

Const is constant,

P _i(φ) for the light distribution of light source outgoing is,

P ₀(θ) be the light distribution through obtaining behind the described reflecting surface,

φ is light source emergent ray and axis angle;

θ is the angle through light and axis after the reflecting surface reflection.

Especially, when the light distribution of described light source is constant, i.e. P _i(φ)=P _i, the light distribution of simultaneously outgoing is at 0＜θ＜θ ₁Also be constant, i.e. P in the scope ₀(θ)=P ₀The time, there is following linear relationship between cos θ and the cos φ:

Cos θ=acos φ+b, wherein

$a=\frac{1-\cos {\mathrm{\θ}}_1}{1-{\cos \mathrm{\φ}}_1},$ $b=\frac{\cos {\mathrm{\θ}}_1-\cos {\mathrm{\φ}}_0}{1-\cos {\mathrm{\φ}}_0}$

In addition, the present invention also provides a kind of navigation lights, comprise: light source, Transparent lamp shade, reflection face shield and base plate, described reflection face shield and described Transparent lamp shade are connected to an integral body and together are fixed on the described base plate, described light source is arranged on the described base plate and near described reflection face shield, the light of described light source emission penetrates from described Transparent lamp shade after described reflection face shield reflection.Described reflection face shield reflecting surface forms around the axis three-dimensional rotation by curve R, and in cylindrical coordinates system (R, φ), described curve R is denoted as R (φ), wherein:

R=constexp (∫ tan α d φ)=R (φ) and P _i(φ) d φ=P ₀(θ) d θ; Wherein,

P _i(φ) for the light distribution of light source outgoing is,

P ₀(θ) be the light distribution through obtaining behind the described reflecting surface,

φ is light source emergent ray and axis angle;

θ is the angle through light and axis after the reflecting surface reflection.

Especially, when the light distribution of described light source was constant, there was following relation in the function of the curve R of described reflecting surface, i.e. cos θ=acos φ+b, wherein:

$a=\frac{1-\cos {\mathrm{\θ}}_1}{1-\cos {\mathrm{\φ}}_0},$ $b=\frac{\cos {\mathrm{\θ}}_1-\cos {\mathrm{\φ}}_0}{1-\cos {\mathrm{\φ}}_0}$

More preferably, a kind of navigation lights of more compact structure also is provided in one embodiment of the present of invention, it also is equipped with the reflecting layer on described base plate, the light of described light source emission arrives on the described reflecting layer after described emission face shield reflection, and penetrates from described Transparent lamp shade behind the secondary reflection through described reflecting layer again.

Especially, described light source is halogen light source or led light source.

Especially, described base plate also can be the substrate with metal heat sink.

Especially, described light source is fixed on the described base plate by the mode of mechanical connection or welding.

Especially, described reflection face shield and described transparent face mask tie point place to the angle of the line at described reflection face shield and described base plate tie point place and described base plate at 60 °-80 °.More preferably, the described angle number of degrees are 70 °.

Navigation lights of the present invention is because compact conformation, so the mode that can adopt the side to install is installed in fuselage rear both sides, effectively avoids the afterbody high-temperature area, have because lampshade of the present invention has special reflecting curved surface, distribute so that this navigation lights in compact conformation, can guarantee again light

Description of drawings

Fig. 1 is the schematic diagram of one embodiment of the invention;

Fig. 2 is the schematic diagram of another embodiment of the present invention;

Fig. 3 is the scheme of installation of navigation lights of the present invention.

The specific embodiment

As shown in Figure 1, the invention provides a kind of navigation lights 7, comprise: light source 1, Transparent lamp shade 2, reflection face shield 3 and base plate 4, described reflection face shield 3 is connected to an integral body with described Transparent lamp shade 2 and together is fixed on the described base plate 4, described light source 1 is arranged on the described base plate 4 and near described reflection face shield 3, the light of described light source 1 emission penetrates from described Transparent lamp shade 2 after described reflection face shield 3 reflections.

For so that navigation lights of the present invention 7 has compact navigation lights structure, and guaranteeing to reduce aerodynamic effects under the photodistributed prerequisite, so will carry out particular design to face shield of the present invention.

The light distribution of white light navigation lights system must reach following minimum requirements, considers the optical attenuation in the use procedure, and the actual light intensity situation must increase certain nargin in minimum requirements.

Wherein, the minimum intensity of light in the white light navigation lights horizontal plane is as shown in table 1.

Minimum intensity of light requirement in table 1 horizontal plane

In addition, the minimum intensity of light in the white light navigation lights vertical plane is as shown in table 2.

Minimum intensity of light requirement in table 2 vertical plane

It is as shown in table 3 that the white light navigation lights mixes light intensity to the maximum in dihedral angle zone, the left and right sides.

Table 3 maximum is mixed light intensity requirement

In an embodiment of the present invention, according to the light distribution requirement of above-mentioned table 1 to the white light navigation lights shown in the table 3, and the light distribution characteristic of white light LEDs, adopt the nonimaging optics method for designing to obtain satisfactory secondary reflection curved surface.

In the scope of LED irradiation, the A district is the white light LEDs navigation lights light intensity area of coverage, and the B district is the exclusion area, can not have light intensity to exist, and therefore, the light that we adopt 3 couples of LED of reflection face shield to send is changed, and makes this light can be converted into the light in A district.

According to the two-dimensional non-imaging optical design method, and the track by the equation solution curve, just can obtain section curve.

This curve around axis (x direction) three-dimensional rotation (90 °-+90 °), is formed surface of revolution.In the XZ plane, form line of cut afterwards, and unlimited extension of this line of cut edge ± z direction of principal axis obtained a cutting planes, then remove to cut surface of revolution with this cutting planes, obtain surface of revolution, and with the Partial Resection of surface of revolution radian less than 70 °, just become the reflecting surface of reflection face shield 3 through remaining part after above-mentioned cutting and the excision.

The below will discuss the two-dimensional non-imaging optical design method in detail.This method for designing is based on the given light of two dimension and distributes.It is exactly that the light with rotational symmetry or translational symmetry distributes that the given light of described two dimension distributes.

There is a main cross section in the two-dimensional non-imaging optical design, in any case rotation or translation, radiation direction in the main cross section and distribution can not change, therefore can utilize the curve of a two dimension of this main cross section design, then curve rotation or the translation with two dimension obtains forming given photodistributed optical system.

At first, will be used to form point coordinates on the curve R of curved surface with cylindrical coordinates (R, φ) expression, the differential expressions of reflection law is so:

$\frac{d\left(\ln R\right)}{\mathrm{d\φ}}=\tan \mathrm{\α}---\left(1\right)$

$\mathrm{\α}=\frac{\mathrm{\φ}-\mathrm{\θ}}{2}---\left(2\right)$

And then obtain:

R＝const·exp(∫tanαdφ)＝R(φ) (3)

In theory, distribute for arbitrarily emergent light distribution and incident light, all answer Existence dependency relationship θ (φ) between them, as long as therefore find the solution formula (2), just can access reflectivity curve contour shape R (φ).

For two-dimentional system, whole optical system is along the extension of z axle congruence.At this moment, suppose that the light distribution by the light source outgoing is P _i(φ), be P through the light distribution that obtains behind the two-dimentional reflecting surface ₀(θ), so according to the conservation of energy, both must have following relation:

P _i(φ)·dφ＝P ₀(θ)·dθ (4)

The simplest a kind of situation is discussed now, i.e. the light distribution of light source is constant, i.e. P _i(φ)=P _i, with the light distribution of seasonal outgoing at 0＜θ＜θ ₁Also be constant, i.e. P in the scope ₀(θ)=P ₀Substitution formula (4), and consider boundary condition θ (φ) | _φ=0=0, obtain:

$\mathrm{\θ}=\frac{P_i}{P_0}\mathrm{\φ}---\left(5\right)$

Bring (5) formula into (3) formula, just can obtain the in this case shape of cross section of reflecting curved surface:

$R=\frac{R_0}{{\cos }^k\left(\frac{\mathrm{\φ}}{k}\right)}---\left(6\right)$

R wherein ₀Be the value of the R at φ=0 place,

For rotationally symmetric system, whole system is take the y axle as rotation axes of symmetry.Similar with two-dimentional system, can access equally differential relationship between incident field and the outgoing light field according to the conservation of energy:

P _i(φ)·d(cosφ)＝P ₀(θ)·d(cosθ) (7)

The simplest situation P of same consideration _i(φ)=P _i, P ₀(θ)=P ₀(0＜θ＜θ ₁), then should there be following linear relationship between cos θ and the cos φ:

cosθ＝acosφ+b (8)

Consider such boundary condition θ (φ) | _φ=0=0 He

, then can obtain a and b:

$a=\frac{1-\cos {\mathrm{\θ}}_1}{{1-\cos \mathrm{\φ}}_0}---\left(9\right)$

$b=\frac{\cos {\mathrm{\θ}}_1-\cos {\mathrm{\φ}}_0}{1-\cos {\mathrm{\φ}}_0}---\left(10\right)$

With the equation substitution (3) of formula (8) to formula (10), just can obtain a meridian surface profile equation R=R (φ) of rotational symmetric reflecting surface.Find the solution this equation and need to adopt numerical solution.

According to said method, in one embodiment of the invention, the reflecting surface of described reflection face shield 3 forms around the axis three-dimensional rotation by curve R, and in cylindrical coordinates system (R, φ), described curve R is denoted as R (φ), wherein:

R=constexp (∫ tan α d φ)=R (φ) and P _i(φ) d φ=P ₀(θ) d θ; Wherein,

Const is constant,

P _i(φ) for the light distribution of light source 1 outgoing is,

P ₀(θ) be the light distribution through obtaining behind the described reflecting surface,

φ is light source 1 emergent ray and axis angle;

θ is the angle through light and axis after 3 reflections of reflection face shield.

In a preferred embodiment of the invention, when the light distribution of described light source 1 is constant, i.e. P _i(φ)=P _i, the light distribution of simultaneously outgoing is at 0＜θ＜θ ₁Also be constant, i.e. P in the scope ₀(θ)=P ₀The time, there is following linear relationship between cos θ and the cos φ:

Cos θ=acos φ+b, wherein

$a=\frac{1-\cos {\mathrm{\θ}}_1}{1-\cos {\mathrm{\φ}}_0},$ $b=\frac{\cos {\mathrm{\θ}}_1-\cos {\mathrm{\φ}}_0}{1-\cos {\mathrm{\φ}}_0}$

In addition, as shown in Figure 2, in a preferred embodiment of navigation lights 7 of the present invention, on described base plate, also be provided with reflecting layer 5, the light 6 of described light source 1 emission arrives on the described reflecting layer 5 after described emission face shield 3 reflections, and penetrates from described Transparent lamp shade 2 behind the secondary reflection through described reflecting layer 5 again.

Show a kind of concrete occupation mode of navigation lights of the present invention such as Fig. 3, in this mode, navigation lights 7 of the present invention is installed in the both sides of airplane tail group 9 as after steaming light, as shown in Figure 3, the light distribution zone 8 of described navigation lights has covered whole aircraft rear substantially, has satisfied the requirement of airworthiness regulation.

Technology contents of the present invention and technical characterstic disclose as above, yet are appreciated that under creative ideas of the present invention, and those skilled in the art can make various changes and improve said structure, but all belongs to protection scope of the present invention.The description of above-described embodiment is exemplary rather than restrictive, and protection scope of the present invention is determined by claim.

Claims (9)

1. reflection face shield that is used for navigation lights, this reflection face shield receives the light that described navigation lights light source sends and this light reflection is gone out, it is characterized in that, the reflecting surface of described reflection face shield forms around the axis three-dimensional rotation by curve R, at (the R of cylindrical coordinates system, φ), described curve R is denoted as R (φ), wherein:

R=constexp (∫ tan α d φ)=R (φ) and P _i(φ) d φ=P ₀(θ) d θ; Wherein,

Const is constant,

$\mathrm{\α}=\frac{\mathrm{\φ}-\mathrm{\θ}}{2}$

P _i(φ) be the light distribution of light source outgoing,

P ₀(θ) be the light distribution through obtaining behind the described reflecting surface,

φ is light source emergent ray and axis angle;

θ is the angle through light and axis after the reflection of reflection face shield;

Wherein, when the light distribution of described light source is constant, i.e. P _i(φ)=P _i, the light distribution of simultaneously outgoing is at 0＜θ＜θ ₁Also be constant, i.e. P in the scope ₀(θ)=P ₀The time, there is following linear relationship between cos θ and the cos φ:

Cos θ=acos φ+b, wherein, boundary condition is θ (φ) | _φ=0=0 He

The time:

$a=\frac{1-{\cos \mathrm{\θ}}_1}{1-{\cos \mathrm{\φ}}_0};$

$b=\frac{\cos {\mathrm{\θ}}_1-\cos {\mathrm{\φ}}_0}{1-\cos {\mathrm{\φ}}_0}.$

2. navigation lights, it is characterized in that, comprise: light source, Transparent lamp shade, reflection face shield as claimed in claim 1 and base plate, described reflection face shield and described Transparent lamp shade are connected to an integral body and together are fixed on the described base plate, described light source is arranged on the described base plate and near described reflection face shield, the light of described light source emission penetrates from described Transparent lamp shade after described reflection face shield reflection.

3. navigation lights as claimed in claim 2, it is characterized in that, also be equipped with the reflecting layer on described base plate, the light of described light source emission arrives on the described reflecting layer after described emission face shield reflection, and penetrates from described Transparent lamp shade behind the secondary reflection through described reflecting layer again.

4. navigation lights as claimed in claim 2 or claim 3 is characterized in that described light source is halogen light source or led light source.

5. navigation lights as claimed in claim 2 or claim 3 is characterized in that described base plate is the substrate with metal heat sink.

6. navigation lights as claimed in claim 2 or claim 3 is characterized in that described light source is fixed on the described base plate by the mode of mechanical connection or welding.

7. navigation lights as claimed in claim 2 or claim 3 is characterized in that, described reflection face shield and described Transparent lamp shade tie point place to the angle of the line at described reflection face shield and described base plate tie point place and described base plate at 60 °-80 °.

8. navigation lights as claimed in claim 7 is characterized in that, the described angle number of degrees are 70 °.

9. the mounting means such as each described navigation lights of claim 2-8 is characterized in that, described navigation lights is installed in the both sides of afterbody.

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