Optical receiver characterizations and corrections for ground-based and airborne measurements of spectral actinic flux densities
- 1Institut für Energie- und Klimaforschung, IEK-8: Troposphäre, Forschungszentrum Jülich GmbH, 52428 Jülich, Germany
- 2Deutscher Wetterdienst, Bildungszentrum Langen, 63225 Langen, Germany
Correspondence: Birger Bohn (email@example.com)
Solar actinic radiation in the ultraviolet and visible range (UV/VIS) perpetuates atmospheric photochemistry by inducing photolysis processes which form reactive radical species. Photolysis frequencies are rate constants that quantify the rates of photolysis reactions and therefore constitute important parameters for quantitative analyses. Photolysis frequencies are usually calculated from modelled or measured solar spectral actinic flux densities. Suitable measurement techniques are available, but measurement accuracy can suffer from non-ideal 2π or 4π solid-angle reception characteristics of the usually employed 2π optical receivers or receiver combinations. These imperfections, i.e. deviations from an angle-independent response, should be compensated for by corrections of the measured data. In this work, the relative angular sensitivities of four commonly used 2π quartz receivers were determined in the laboratory in a range 280–660 nm. Based on this information, the influence of the non-ideal responses on measured spectral actinic flux densities for ground-based and airborne applications was investigated for a wide range of atmospheric conditions. Spectral radiance distributions and contributions of direct, diffuse downward and diffuse upward spectral actinic flux densities were calculated with a radiative transfer model to derive the corrections. The intention was to determine the ranges of possible corrections under realistic measurement conditions and to derive simple parametrizations with reasonable uncertainties. For ground-based 2π measurements of downward spectral actinic flux densities, corrections typically range <10 % dependent on wavelength and solar zenith angle, with 2 %–8 % uncertainties covering all atmospheric conditions. Corrections for 4π airborne measurements were determined for the platforms Zeppelin NT (New Technology) and HALO (High Altitude and Long Range Research Aircraft) in altitude ranges 0.05–2 and 0.2–15 km, respectively. Total, downward and upward spectral actinic flux densities were treated separately. In addition to various atmospheric conditions, different ground albedos and small (<5∘) aircraft attitude variations were considered in the uncertainties, as well as aircraft headings with respect to the sun in the case of HALO. Corrections for total and downward spectral actinic flux densities again typically range <10 % dependent on wavelength, solar zenith angle and altitude, with 2 %–10 % uncertainties covering all atmospheric conditions for solar zenith angles below 80∘. For upward spectral actinic flux densities, corrections were more variable and significantly greater, up to about −50 % at low altitudes and low ground albedos. A parametrization for corrections and uncertainties was derived using uncorrected ratios of upward / downward spectral actinic flux densities as input, applicable independent of atmospheric conditions for a given wavelength, solar zenith angle and altitude. The use was limited to conditions with solar zenith angles <80∘ when direct sun radiation cannot strike upward- and downward-looking receivers simultaneously. Examples of research flights with the Zeppelin and HALO are discussed, as well as other approaches described in the literature.
Photodissociation of atmospheric gas-phase constituents by solar ultraviolet and visible radiation (UV/VIS) essentially influences atmospheric chemistry and composition through the formation of highly reactive photoproducts. These intermediates, or secondary products like OH, can initiate oxidizing chain reactions and lead to other reactive species like O3. The rates of photolysis processes are quantified by first-order rate constants denoted as photolysis frequencies which are important parameters because they directly or indirectly determine the lifetime of many atmospheric species. Accurate knowledge is therefore essential for a quantitative understanding of atmospheric photochemistry. Photolysis frequencies can be determined from solar spectral actinic flux densities Fλ. For example, j(NO2), the rate constant of the process , is calculated by integration over the relevant wavelength range:
where and are the absorption cross sections of NO2 and the quantum yields of the photoproduct O(3P), respectively. Fλ is inserted in molecular units (cm−2 s−1 nm−1). Photolysis frequencies of other photolysis processes can be calculated accordingly by inserting the respective parameters of the precursor molecules. Spectroradiometry, a technique to measure Fλ in the relevant UV/VIS spectral range, is therefore the most convenient experimental method to determine photolysis frequencies. Measurements of Fλ are important for many field studies, mainly because the strong and variable influence of clouds on actinic radiation is hard to predict by radiative transfer models unless detailed local cloud information is available. A general overview of techniques to derive photolysis frequencies in the atmosphere by radiometric and chemical methods, as well as by radiative transfer models, is given by Hofzumahaus (2006).
The radiometric determination of Fλ in the atmosphere is complicated by two experimental challenges related with (i) the specificity of measurements in the UV-B range and (ii) the quality of optical receivers for actinic radiation. For aircraft measurements, these issues are particularly relevant:
UV-B radiation is strongly diminished in the lower atmosphere by stratospheric ozone but highly important for tropospheric ozone photolysis and OH formation. Aircraft deployments require both high time resolution and high UV sensitivity, which can be achieved by CCD (charge-coupled device) array spectroradiometers. However, because these instruments are single-monochromator-based, the weak UV-B range is significantly affected by stray light, i.e. by radiation that is non-regularly reflected inside monochromators. Instrument calibrations and field data analyses therefore require special procedures to minimize the stray light influence. In previous studies, suitable approaches were described for a widely used type of spectroradiometers (Jäkel et al., 2007; Bohn and Lohse, 2017).
Spectral actinic flux density Fλ is obtained upon integrating the directional quantity spectral radiance Lλ over all solid angles ω:
In contrast to spectral irradiance, no polar-angle-dependent weighting of Lλ is applied, and there is no sign distinction between upward and downward flux densities because from the perspective of gas-phase molecules, radiation is received with the same efficiency regardless of the direction of incidence. Therefore, the ideal optical receiver for actinic radiation has an angle-independent reception sensitivity and a 4π solid-angle field of view. A corresponding 4π optical receiver (Teflon sphere) with adequate properties was described in the literature (Eckstein et al., 2003). However, technically 2π receivers covering a hemisphere are more practicable and often sufficient, for example, for many ground-based applications under conditions with low ground albedo. On the other hand, owing to the greater importance of upward radiation, reflected by underlying air columns and clouds, airborne measurements require 4π reception characteristics, which is accomplished by two 2π receivers on the top and bottom fuselage of the aircraft. Because the quartz-dome receivers that are usually employed have vertical extensions, and adequate horizontal shielding can be difficult for technical reasons (Sect. 2), some cross-talk to the opposite hemisphere is typical. Receiver-specific corrections are therefore necessary to compensate for cross-talk as well as for other imperfections. Corresponding corrections were derived in the literature for ground-based and airborne applications (Volz-Thomas et al., 1996; Shetter and Müller, 1999; Hofzumahaus et al., 1999, 2002; Eckstein et al., 2003; Jäkel et al., 2005; Stark et al., 2007; Bohn et al., 2008). These corrections were based on laboratory measurements of angular sensitivities of the receiver optics and radiative transfer calculations of spectral actinic flux density contributions from direct, diffuse downward and diffuse upward radiation. However, except for the studies by Volz-Thomas et al. (1996) and Jäkel et al. (2005), estimated mean corrections and uncertainties were applied, independent of actual measurement conditions.
In this work, an extended approach was developed by consulting spectral radiance distributions from radiative transfer calculations for a wide range of atmospheric conditions. Corrections were derived as a function of wavelength, altitude and solar zenith angle for two pairs of receiver optics that were deployed during several missions on the airborne platforms Zeppelin NT (New Technology) and HALO (High Altitude and Long Range Research Aircraft, Gulfstream G550), as well as for ground-based pre- and post-flight comparisons of downward spectral actinic flux densities. The objective was to determine corrections as accurate as possible with realistic uncertainty estimates and to derive parametrizations that are easily applicable under all measurement conditions. The uncertainties of the corrections add to those from the radiometric calibrations, which are typically small and range around 5 %–6 % based on traceable spectral irradiance standards (Bohn and Lohse, 2017). Consequently, even small corrections and small improvements of uncertainties are significant.
The employed 2π actinic receiver optics were developed by Meteorologie Consult GmbH based on an original design by Junkermann et al. (1989) with modifications implemented by Volz-Thomas et al. (1996) and have been widely used in atmospheric research for more than 25 years (Volz-Thomas et al., 1996; Shetter and Müller, 1999; Hofzumahaus et al., 1999). The receivers are composed of a stack of sandblasted, elongate quartz domes covering a quartz rod in aluminium housing. The plain outer dome surface is sealed against a black-anodized aluminium base flange (Fig. 1). Radiation that enters the receiver is multiply scattered and partly transmitted by the quartz domes until it reaches a sandblasted surface at the bottom of the quartz rod. This surface forms a virtual light source that can be captured by an optical fibre, eventually guiding the radiation to a spectroradiometer or other detectors. The distances of the domes from each other can be adjusted for optimum angular response of the receiver, i.e. an ideally angle-independent sensitivity within a hemisphere. However, despite adjustments, some receiver-specific imperfections typically remain. In particular, the vertical extension that is necessary for sufficient sensitivity at near-horizontal incidence can cause cross-talk to the other hemisphere, which is significant for aircraft measurements because of commonly high spectral radiances in both hemispheres. The cross-talk can be reduced by fitting the receiver base flanges into larger, black-anodized or varnished flanges or by using horizontal shadow rings that act as artificial horizons.
Ground-based installations in this work were occasionally set up on a roof platform at Forschungszentrum Jülich for the purpose of comparisons with a reference instrument before and after airborne deployments (Bohn and Lohse, 2017). Ground-based measurements were confined to downward actinic flux densities, with aircraft top and bottom receivers facing the upper hemisphere using the original aircraft flanges or matching substitutes. Because the local surroundings had a low ground albedo (roofing felt), cross-talk effects were insignificant for this setup as during previous intercomparisons (Bohn et al., 2008).
Aircraft installations of the receivers were adapted to the specific requirements of the Zeppelin and HALO. For the Zeppelin, the top receiver covering the upper hemisphere was installed on the roof cover of a rectangular instrument box that was sitting on top of the airship envelope. A roof area about 1 m2 wide surrounding the receiver flange was covered with black matted foil, resulting in effective horizontal shielding. The reflective properties of the plastic foil were investigated in the laboratory (Sect. 3.2). The bottom receiver covering the lower hemisphere was mounted under the cabin in an extension flange to avoid shading by other inlets. In this case, the field of view was limited by the 200 mm receiver flange alone, unaffected by any airship structure. A scheme of the setup is shown in Fig. S1 in the Supplement.
For the HALO aircraft, aerodynamic requirements were more demanding, and receivers were built into robust instrument plates compatible with the aircraft notches (≈200 mm ×300 mm). The same construction was used for top and bottom receivers, but to compensate for the typical pitch angle of HALO under normal flight conditions, instrument plates were slightly tilted by 3.3∘ in opposite directions on the top and bottom fuselage in the middle–front section of the aircraft. This setup is shown schematically in Fig. 2 and was repeatedly employed for two specific inlet configurations named FLT and FLV in the following. In a third configuration denoted FLN, the bottom receiver was placed in the rear section of the aircraft. The ascending slope of the bottom fuselage in the rear section was compensated for by turning the instrument plate by 180∘, again resulting in horizontal orientations under normal flight conditions. The receiver positions of the three configurations are indicated by arrows in Fig. 3.
Another factor was the glossy white paint of HALO that caused specular reflections striking the receivers in a narrow range of incident angles. Laboratory measurements were made to estimate the influence of these reflections which affected the configurations FLT and FLN (Sect. 3.2). In the FLV configuration the instrument plates were built into larger (≈60 cm) black-anodized flanges that effectively prevented the influence of aircraft reflections but had no effect on the field of view because they were shaped as the aircraft fuselage. The horizontal shielding by the aircraft fuselage on average was around 6∘ below the horizon but different in lateral and parallel directions (Sect. 3.2). The use of larger, flat flanges to improve the horizontal shielding of the receivers was not feasible for this comparatively small aircraft without expensive flight tests. Moreover, an attempt by the manufacturer to downsize the receivers to minimize cross-talk effects without degrading the 2π reception characteristics was not successful in the run-up of the HALO integration.
For field and laboratory measurements, receiver optics were connected with CCD array spectroradiometers (CCD-SRs) with optical quartz fibres of suitable lengths (2–12 m). The CCD-SRs were developed by Meteorologie Consult GmbH for atmospheric measurements of spectral actinic flux densities. The instruments are composed of a single monochromator (Carl Zeiss, MCS-CCD) with spherical refraction grating and a temperature-stabilized CCD array detector (Hamamatsu, S7031-0906S). These components were built into compact aluminium housing that was placed in 19 in. flight-rack mounts. Actinic flux density spectra were measured with a spectral resolution of about 2 nm in a wavelength range 280–650 nm with a time resolution of 1–3 s dependent on the aircraft. More details on the employed CCD-SRs, the calibration procedure and the data analysis can be found in a previous paper (Bohn and Lohse, 2017). The CCD-SRs were also used for the laboratory characterizations of the optical receivers, utilizing extended integration times of up to 1 s and repeated measurements (10–100) to improve signal-to-noise ratios in the UV range (Bohn and Lohse, 2017). However, it should be noted that the targeted receiver-specific properties and the resultant corrections are independent of the radiometric detection method.
3.1 2π receivers
Knowledge of the relative angular sensitivities of the optical receivers is the basis of assessing the uncertainties and correcting atmospheric measurements of spectral actinic flux densities. Angle-dependent sensitivity measurements were carried out in the laboratory with a goniometric setup on an optical bench, where the receivers including their aircraft flanges were positioned at different incident angles relative to a stabilized point light source (1000 W tungsten halogen lamp). Polar angles of incidence ϑ were defined here as usual in geometric optics and are indicated in Fig. 1 for a 2π receiver. Azimuth angles φ=0∘ refer to fixed positions on the receiver base flanges which correspond to the flight directions of the aircraft-installed receivers. Pictures of the goniometric setup are shown in Fig. S2.
Angle-dependent measurements of lamp spectra were made in a range for . By extending the range beyond 90∘, the cross-talk for each receiver was investigated, including the shading effects of the aircraft-specific flanges. Azimuth angles were changed in 45∘ steps in a range .
Following the notation introduced by Hofzumahaus et al. (1999), relative angular sensitivities Zp were determined by normalizing background-corrected signal spectra S with those obtained at normal incidence ():
For an ideal receiver, Zp=1 for all wavelengths at and Zp=0 for .
The index of Zp indicates the use of a point light source in front of which the receiver was rotated. For a point light source, the problem is that the flux density strongly depends on distance following an inverse square law. As a consequence, for actinic radiation receivers with vertical extensions, the concept of an equivalent plane receiver is used for calibrations with irradiance standard lamps: the lamp position is adjusted for a receiver-specific distance Δz with respect to the quartz dome tip. Typical Δz values range around 20 mm for an incident angle ϑ=0∘, as indicated in Fig. 1. They have to be determined experimentally for each receiver to ensure accurate calibrations (Hofzumahaus et al., 1999; Bohn and Lohse, 2017). In this work, Δz values were also determined for , which turned out to be smaller by 8–15 mm. The polar-angle-dependent differences correspond to small but significant signal changes that can affect the angle-dependent Zp measurements at the lamp distances used. Enhanced distances z between the lamp and receiver would be favourable to avoid this problem, but greater distances also result in smaller signals, dependent on lamp power, wavelength and the detector used.
To avoid uncertainties caused by the potentially ϑ-dependent Δz, the laboratory procedure was revised. Angle-dependent measurements were performed at two lamp distances of z=400 mm and z=800 mm with respect to the equivalent plane at ϑ=0. The final Zp values were then determined by a two-point extrapolation towards an inverse distance of zero; i.e. they correspond to a hypothetical infinite distance z. The influence of distance on the measured Zp was generally small but not negligible, at least for two of the employed receivers. More details on the experimental approach and a formal derivation of the two-point method are given in Sect. S2.1 in the Supplement.
Contour plots of the final Zp values are shown in Fig. 4 for the HALO top and bottom receivers for a wavelength of 400 nm as an example. Corresponding plots for the Zeppelin receivers are shown in Fig. S4. An azimuthal equal-area projection was chosen to correctly reproduce the solid-angle contributions for different polar angles relevant for actinic flux density measurements; i.e. the areas increase with the sine of the polar angle, consistent with Eq. (2) (dω=sin (ϑ)dϑdφ). Because of the rotational symmetry of the receivers, dependencies on azimuth angles are typically minor (<5 %). Cross-talk effects are not visible in Fig. 4. Similar plots for the opposite hemispheres are not shown because the values are mostly zero, except for narrow ≤15∘ bands close to the horizon. Instead, Fig. 5 shows azimuthal mean Zp values for the HALO top and bottom receivers for selected wavelengths where the cross-talk to the other hemisphere becomes visible. This cross-talk quickly diminishes above 90∘ and vanishes at around 105∘. The Zp dependencies on polar angle and the wavelength dependence are slightly different for the different receivers but can differ by up to 15 % at greater polar angles. The properties of the 2π receivers investigated here are similar to those shown in previous work using the same type of receivers (Shetter and Müller, 1999; Hofzumahaus et al., 1999; Jäkel et al., 2005; Bohn et al., 2008). Corresponding plots for the Zeppelin receivers are shown in Fig. S5.
3.2 4π aircraft assemblies
For ground-based measurements, the Zp data of Figs. 4 and 5 are directly applicable for the calculation of correction functions (Sect. 5). On the other hand, for airborne measurements, the combined total sensitivities of the receivers installed on the top and bottom fuselage have to be considered. As an example, Fig. 6 shows contour plots of total relative angular sensitivities of the FLT configuration on HALO in the upper and the lower hemisphere for a wavelength of 400 nm. The values comprise the combined effects of the Zp of top and bottom receivers, geometrical restrictions of the fields of view by the aircraft and fuselage reflections. More details on field-of-view effects and fuselage reflections are given in Sect. S2.2 and S2.3. The range of incidence angles in Fig. 6 was extended to 0–180∘ with ϑ=0∘ and 180∘, corresponding to zenith and nadir directions, respectively. The cross-talk effects on are most pronounced towards the aircraft sides where the field-of-view restrictions were smallest because of the curved fuselage. Towards the flight direction, the cross-talk is correspondingly smaller and also influenced by the 3.3∘ tilt angle of the aircraft (Fig. 2). In the rear direction, the field of view in the lower hemisphere was for this configuration restricted by a containment on the bottom fuselage. This restriction prevented cross-talk to the upper hemisphere in a rearward section visible in panel (a) of Fig. 6 and causes the dark area close to the horizon in panel (b) where radiation was blocked. For ϑ<80∘ and ϑ>100∘, the values correspond to those shown in Fig. 4. Similar plots for the two other HALO configurations FLN and FLV as well as for the Zeppelin are shown in Figs. S8, S10 and S12.
Azimuthal averages of the data in Fig. 6 are plotted in Fig. 7a. In this representation, the contributions of the top receiver (zenith-oriented) and bottom receiver (nadir-oriented) become visible. At ϑ>80∘, total sensitivities are enhanced (on average) by up to a factor of about 1.6 at ϑ=90∘ because radiation can strike both receivers simultaneously, caused by the non-ideal field-of-view limitations. As a consequence, radiance contributions from polar angles around 90∘ have to be corrected substantially, which also applies to direct sun actinic flux densities at low sun.
In Fig. 7b, relative sensitivities were multiplied by sin (ϑ) to account for the solid-angle contributions, consistent with the ϑ-dependent areas in the projections of Figs. 4 and 6. In the simplest case of an isotropic radiance distribution, the data shown in Fig. 7b would lead to an overestimation of measured actinic flux densities that correspond to the integral of the curve divided by the integral of the ideal sin (ϑ) curve. In this example, the ratio is 1.045, which is suitable to correct measurements at 400 nm, albeit under the special conditions of constant radiances. In order to obtain more realistic corrections, sensitivity distributions as shown in Fig. 6, as well as wavelength-dependent direct sun contributions and diffuse spectral radiance distributions, are required. The latter information is usually not available under measurement conditions. Correction functions were therefore calculated based on results from a radiative transfer model.
4.1 Model settings
Distributions of diffuse spectral radiances were calculated with the radiative transfer model uvspec from the libRadtran package (version 2.0.4) (Mayer and Kylling, 2005; Emde et al., 2016). The purpose was not to obtain radiance distributions for actual measurement conditions. Rather, a range of atmospheric scenarios was created that should ideally cover all realistic measurement conditions. The main model input parameters are listed in Table 1. The radiative transfer equation solver DISORT in pseudo-spherical geometry was utilized (Buras et al., 2011) with 16 streams to obtain accurate spectral radiance output suitable to calculate spectral actinic flux densities by numerical integrations (Kylling et al., 1995; Hofzumahaus et al., 2002). Calculations were made for 12 different solar zenith angles and an arbitrary solar azimuth angle of 180∘. The radiance output was generated with a step size of 2∘ in 0–180∘ ranges for polar and azimuth angles of incidence, resulting in 8280 spectral radiance values for each wavelength. In subsequent calculations, radiances in the azimuth range 180–360∘ were produced by inversion of the 0–180∘ results. In addition, spectral actinic flux densities for total downward, diffuse downward and diffuse upward radiation were calculated for consistency checks and as an additional input for the evaluation of correction functions (Sect. 5).
a Additional calculations with 200 and 400 DU for selected altitudes of 1 and 10 km. b libRadtran default aerosol properties (Shettle, 1989). c Additional clear-sky calculations for 1 km ground elevation. d Mean ground albedo for vegetation (Feister and Grewe, 1995). e Cloud cases according to Table 2. f In-cloud altitude for a specific cloud case. g Cloud top altitude for a specific cloud case. h Spectral albedo scaled to produce ground albedos A470 of 0.02, 0.04 or 0.07. i Default aerosol (AOD550=0.23) scaled to produce aerosol optical depths AOD550 of 0.03, 0.20 or 1.5. j 89.9∘; the solar zenith angle range for calculations of spectral radiances with the solver DISORT is limited to <90∘.
All model calculations were made in the wavelength range 290–660 nm using 5 nm steps below 310 and 20 nm steps above 320 nm; i.e. the total number of wavelengths was confined to 23. This is justified because, except for the UV-B range, which is affected by stratospheric ozone, a smooth change of radiance distributions with wavelength was expected. Despite this coarse-wavelength sampling, a triangular response function with a full width at half maximum (FWHM) of 1.7 nm was adopted in the model to allow for an optional comparison of the model output with measurements (Bohn and Lohse, 2017).
4.2 Atmospheric scenarios and variables
A number of atmospheric scenarios were devised to simulate realistic measurement conditions. An atmospheric scenario was defined by a cloud case, a ground albedo case and an aerosol case. For each scenario, calculations were made for up to 11 altitudes (Table 1). The total ozone column was fixed at a typical value of 300 DU for the majority of the model calculations. For selected altitudes of 1 and 10 km, additional calculations were made for 200 and 400 DU to examine the influence of ozone columns. The ground elevation was set to mean sea level except for additional clear-sky calculations at a ground elevation of 1 km and heights above ground of 0 and 1 km. Atmospheric pressure and temperature profiles were not varied. Their influence is presumed to be insignificant compared to that related to the different atmospheric scenarios.
Four cloud cases were distinguished: (i) clear-sky, no clouds (Cl); (ii) an optically thin, high-level cirrostratus layer (Cs); (iii) an optically thick medium-level altostratus layer (As); and (iv) an optically thick low-level stratus layer (St). In the model, clouds were idealized as homogeneous layers. The idea was to reproduce conditions with HALO flying below, within or above clouds at different altitudes and the Zeppelin always flying below any clouds. Cloud micro- and macrophysical properties, as well as cloud optical depth (COD), are listed in Table 2. These data represent typical values adopted from the literature (Miles et al., 2000; Sassen and Comstock, 2001; Krämer et al., 2009). More details on the implementation of clouds in the model are given in Sect. S3.1.
Five ground albedo cases were considered: (i–iii) a wavelength-dependent ground albedo A typical for vegetated ground, scaled to match values of 0.02, 0.04 and 0.07 at 470 nm; (iv) a high, wavelength-independent, ground albedo of 0.8 representing snow cover; and (v) a spectral ground albedo of open water. The applied ground albedos are based on literature data (Bowker et al., 1985; Feister and Grewe, 1995; Wendisch et al., 2004). A470=0.04 is considered a standard ground albedo. The theoretical case A=0 was included for test purposes but will not be used for the calculation of correction functions. More details on the ground albedos are given in Sect. S3.2.
Three aerosol cases were implemented based on the default aerosol defined in libRadtran. The properties were varied using the option to scale aerosol optical depth (AOD) to user-defined values at selected wavelengths, in this case at 550 nm. AODs for other wavelengths were scaled accordingly, resulting in the following aerosol cases: (i) AOD550=0.03, (ii) AOD550=0.2 and (iii) AOD550=1.5. These cases cover typical atmospheric properties from very clean oceanic to strongly polluted urban continental conditions. AOD550=0.2 is regarded as the standard aerosol optical depth. The theoretical case AOD =0 was included but will also not be used to calculate correction functions. More details on the aerosol optical depth are given in Sect. S3.3.
An overview of scenarios used for the platforms HALO and Zeppelin, as well as for the ground station, is given in Table S1 in the Supplement. Not all possible combinations of cloud, albedo and aerosol cases were implemented as atmospheric scenarios. For HALO, cruise flight altitudes below 200 m are unrealistic. The 200 m cloud top height of the St layer was therefore chosen so that HALO is always above this cloud type for which the influence of different ground albedos was not evaluated. For the Zeppelin, the St cloud case was neglected because visual flight rules do not permit in-cloud flights. Rare cases where the Zeppelin could be flying above low-lying clouds or ground fog are reasonably represented by scenarios with a high, wavelength-independent ground albedo of 0.8. Altitudes below 50 m were also not considered for the Zeppelin because of the ground-shading effect of the airship itself. For ground-based measurements, all scenarios for an altitude of 0 km were taken into account, except the St cloud case because radiance distributions turned out to be sufficiently similar for St and As cloud cases at ground level. Multiple cloud layers were also not considered. Such conditions are supposed to be covered by in-cloud scenarios and combinations of Cs or As cloud cases with a high ground albedo of 0.8.
Examples of modelled diffuse radiance distributions Lλ(ϑ,φ) for the upper and lower hemisphere under clear-sky conditions are shown in Fig. 8 for an altitude of 5 km, a solar zenith angle of 40∘ and a wavelength of 400 nm. In this example, the relative contributions of direct, diffuse downward and diffuse upward radiation to the total spectral actinic flux density are 0.52, 0.26 and 0.22, respectively. For the same scenario, Fig. 9 shows azimuthal averaged spectral radiances for different wavelengths, normalized to their maximum values for better comparability. In both hemispheres, these radiances are strongly enhanced at polar angles close to the horizon, except for 300 nm where the downward radiances are almost independent of polar angles.
With regard to Figs. 8 and 9, it should be noted that for the modelled spectral radiances polar angles ϑ were redefined as angles of incidence with respect to the 4π aircraft assemblies, in accordance with the notation in the last sections. For the physical directions of propagation different polar angles (θ) apply: . The same holds for solar zenith angles; for example, when the sun is located in the zenith (), the radiation is directed towards the nadir (). The use of angles of incidences has no consequences, except that polar angle integration limits interchange for the upper and the lower hemisphere in some of the equations given in the following section, Sect. 5.1.
Plots like those in Figs. 8 and 9 were produced for each atmospheric scenario, altitude, solar zenith angle and selected wavelength. They provide a quick overview of the variation of radiance distributions and actinic flux densities as a function of atmospheric conditions. In Figs. S17 and S18, a second example is shown for the As cloud case under conditions otherwise the same as in Fig. 8. Expectedly, the spectral actinic flux densities above the cloud layer are strongly enhanced by a factor of around 1.7, and the distributions are different for both upward and (to a minor extend) downward spectral radiances. Two further examples of radiance distributions at a lower altitude under clear-sky conditions and below the As cloud layer are shown in Figs. S19–S22. All model results are available for download for other users (Bohn, 2022). More details are given in Sect. S3.5. The large number of model results naturally contains a lot of interesting information and phenomena. However, a more detailed analysis is beyond the scope of this work. Potential uncertainties of the model results were also not considered. Rather, the variability of naturally occurring radiance distributions is assumed to be represented realistically by the different atmospheric scenarios.
For solar zenith angles approaching 90∘, modelled spectral radiances will become unrealistic because diffuse radiation was calculated in plane-parallel geometry, while for direct radiation, a pseudo-spherical correction was applied in the model. On the other hand, radiance distributions were found to change smoothly on a relative scale, even at large solar zenith angles. Modelled radiance distributions for solar zenith angles of up to 85∘ are therefore considered useful, but, except for ground-based measurements, the correction procedure will be limited to solar zenith angles smaller than 80∘ anyway (Sect. 5.3.2).
For brevity the indication of the wavelength dependency of Fλ and Lλ variables was omitted here. Measurements can be simulated by calculating uncorrected spectral actinic flux densities Fλ,m using the receiver assemblies' relative angular sensitivities :
Angles are defined as angles of incidence, and ϑ∘ and φ∘ are corresponding solar zenith and azimuth angles, respectively (Sect. 4.2). Accordingly, the values have to be rotated horizontally to match the actual situation, dependent on the receiver heading and the solar azimuth angle. By analogy with the hemispherical correction function ZH introduced by Hofzumahaus et al. (1999), the right-hand side of Eq. (5) defines a spherical correction function for measured total spectral actinic flux densities. Because upward and downward Fλ values are determined separately, and information on their contributions is relevant, hemispherical corrections functions ZH are defined as well:
Downward and upward Fλ values are indexed by downward- and upward-pointing arrows, respectively. The hemispherical correction functions and refer to the zenith-oriented (Z) and nadir-oriented (N) top and bottom receivers on the upper and lower fuselage, respectively. Equations (6)–(9) apply to conditions ∘; i.e. no cases with upward direct radiation are considered, but direct radiation unintentionally captured by the bottom receiver is included in Eq. (9).
An important constraint for the three correction functions is that total and hemispherical corrections are related to each other, dependent on the contributions of downward and upward actinic flux densities:
Any final correction should comply with this equation to satisfy the general budget equation:
For the special case of ground-based measurements of downward spectral actinic flux densities, the integration limits can be confined to the upper hemisphere if local upward radiation is negligible (low local ground albedo) or effectively shielded (extended artificial horizons):
The corresponding correction functions were named and apply to the ground-station setup of the four receivers (Sect. 2); i.e. the Zp values in Eq. (12) correspond to those of the individual receivers (Figs. 5 and S4). Other ground-based applications will be discussed in Sect. 7.1.
5.2 Numerical calculations, uncertainties and exemplary results
The ground-station of the four receivers and the three correction functions , and for the airborne platforms were calculated for the atmospheric model scenarios and altitudes summarized in Table S1. To avoid inaccuracies, numerical integrations were done after interpolating the variables to sufficiently high angular resolutions (≤1∘). The procedures were verified by comparing the numerically calculated and with the first-hand model output for these integrated quantities. The influence of different azimuthal positions of the sun was investigated by repeating the calculations after the spectral radiance distributions were rotated in φ=2∘ steps until a full circle was accomplished; i.e. all possible receiver headings with respect to the sun were tested (180 calculations). Uncertainties for each calculation were obtained based on the uncertainty estimates of the Zp variables (Sect. S2.1) and of fuselage reflectivity, if applicable (Sect. S2.3).
5.2.1 Ground station
For the corrections on the ground, the results of the 180 calculations at different solar azimuth angles were averaged to obtain azimuthal mean for downward spectral actinic flux densities. Averaging is justified because the azimuthal variations of the Zp variables are small (Figs. 4 and 5 and Figs. S4 and S5). Total uncertainties for the averages were derived so that they cover the uncertainties of the 180 calculations as well as the variations induced by the rotations of the radiance distributions.
As an example, Fig. 10 shows the resulting for one of the HALO receivers on the ground for different cloud cases at standard aerosol optical depths and ground albedos. The solar zenith angle dependence and uncertainties are greatest under clear-sky conditions and smallest for the As cloud case, where no direct radiation is present, and the spectral radiance distributions exhibit no azimuthal dependencies. Overall, the corrections are small in the UV range (≤2 %) but can reach around 10 % at 600 nm at clear sky and low sun. The values for the other receivers under the same conditions are shown in Figs. S23–S25. Expectedly, they are specific for each receiver, dependent on the individual angular sensitivities.
Considering other atmospheric scenarios, the influence of different ground albedos on the was found to be minor (≤1 %), even for the greatest albedo of 0.8. On the other hand, the effects of aerosol load were more significant. The greatest AOD in the model led to clear-sky corrections, i.e. corrections in the absence of clouds, like for the Cs cloud case. Calculations for a ground elevation of 1 km instead of sea level produced minor deviations well below 1 %, even under clear-sky conditions.
The dashed lines in Fig. 10 show corrections based on the assumption of isotropic diffuse radiance distributions in the upper hemisphere; i.e. only the contributions of direct and diffuse downward actinic flux densities were accounted for. The differences between dashed and full lines are small (≤2 %), which implies that for the determination of the , the use of modelled radiance distributions is expendable, at least for this receiver. The limited influence of the radiance distributions also means that the correction functions remain applicable at solar zenith angles >85∘, even though the radiative transfer model calculations are not reliable under these conditions (Sect. 4.2).
For the Zeppelin, the , and were again averaged to obtain azimuthal mean values of the three correction functions. Azimuthal means are suitable because the azimuthal variabilities of the , and variable distributions are small (Fig. S12). However, for the Zeppelin, deviations from the normal flight attitude with zero pitch and roll angles can lead to additional variations in the corrections, which increases the uncertainties. Attitude changes were specified by a tilt angle α with respect to the surface normal of the top receiver plane. A limit α=5∘ was defined, after consulting tilt angle frequency distributions from the research flights, where the α values were calculated from airship pitch and roll angles. The limit α=5∘ led to a typical loss in data coverage below 20 %, which is accepted to contain the uncertainties of the corrections and to ensure a proper distinction of upward and downward actinic flux densities. To determine the influence of attitude changes, the azimuth-dependent calculations (0–360∘) were repeated eight times (with a resolution of 10∘) after the Zp variable distributions were tilted by 5∘ in eight directions with respect to the aircraft heading in 45∘ steps. Azimuthal variations expectedly increased upon a change in aircraft attitude though strongly dependent on solar zenith angles and atmospheric conditions. The uncertainty estimates for the corrections were increased to cover the additional variations obtained for the eight tilted configurations.
As an example, Fig. 11 shows the altitude dependence of the , and for the Zeppelin at standard aerosol optical depths and ground albedos for a solar zenith angle of 40∘. The three lines of panels correspond to clear-sky conditions as well as overlying Cs and As cloud layers. The altitude dependencies of the and are minor and insignificant for a given cloud case for all wavelengths within the estimated uncertainties which cover the effects of ±5∘ attitude variations as explained above. Because of insufficient field-of-view limitations of the bottom receiver, significant cross-talk to the upper hemisphere occurs, and the values are generally greater than unity. Moreover, they increase strongly towards the ground when upward actinic flux densities typically decrease, which requires an increasing compensation for the cross-talk to the upper hemisphere. However, the values are hardly affected by the greater because the contributions of upward radiation are small under such conditions. Accordingly, the increase towards the ground depends on ground albedos and virtually vanishes for the scenario with a high ground albedo of 0.8 (not shown). Generally, towards greater solar zenith angles, uncertainty ranges increase with wavelength and decreasing aerosol optical depth for the clear-sky case but show little dependence on solar zenith angles for the cloud cases.
Dashed lines in Fig. 11 correspond to corrections based on isotropic diffuse radiance distributions in each hemisphere using the modelled contributions of diffuse upward, diffuse downward and direct actinic flux densities. The differences are small for the clear-sky case, more pronounced for the of the cloud cases and most significant for the of the cloud cases, where the isotropic corrections are greater. This can be explained by the modelled downward spectral radiance distributions below the cloud layers, which show a decrease with increasing polar angle, leading to a reduced cross-talk compared to the isotropic case (Figs. S21 and S22).
For the three HALO configurations, simple azimuthal averages were not used because the , and vary significantly with azimuth angle at polar angles between around 80 and 100∘ (Figs. 6 and Figs. S8 and S10). Consequently, the approach described for the Zeppelin was refined for HALO. A solar heading angle (γ∘) was defined describing the relative azimuth angle of the aircraft heading with respect to the sun: ∘ when the aircraft was heading towards the sun and ∘ for the opposite direction. Because the Zp values are similar on the left- and right-hand sides, the solar heading angle range was limited to 0–180∘. Correction functions were derived for solar heading angles of 0, 45, 90, 135 and 180∘ by averaging the correction functions obtained at α=0 within ±22∘ ranges of the five γ∘ values, including results from left- and right-hand sides of the aircraft. Heading-specific uncertainties were determined from maximum deviations within the ±22∘ ranges, including those obtained for the eight tilted configurations. For HALO, a more strict maximum tilt angle of α=2.5∘ was defined because tilt angle distributions were narrower compared to the Zeppelin. Nevertheless, corrections for α=5∘ were also derived for HALO as a backup to optionally increase data coverage at the expense of greater uncertainties.
Figure 12 shows the altitude dependence of , and of the FLT configuration on HALO for different cloud cases at a solar zenith angle of 40∘. The results apply to a solar heading angle of 90∘, i.e. with the sun on the left- or right-hand side of the aircraft. The altitude range now expands up to 15 km, and the fourth cloud case with the low-lying stratus layer is included. In contrast to the Zeppelin, HALO can fly below and within clouds (Cs, As) as well as above all cloud types, which increases the ranges of modelled corrections. Towards the ground, a similar albeit less strong increase of the was obtained. This increase is smaller compared to the Zeppelin because the cross-talk to the upper hemisphere is, on average, smaller for the HALO bottom receiver. For the St cloud case, the increase of the towards the ground is missing because upward actinic flux densities are strongly enhanced. A comparable result was obtained for the maximum ground albedo of 0.8 (not shown), which has a similar effect as the St cloud layer. Except below a cloud layer, uncertainty ranges of the corrections, as well as the dependence on solar heading angles and the HALO configuration, generally increase with increasing solar zenith angles and increasing wavelengths. The distinction of different solar heading angles helps to confine the uncertainties of the corrections compared to an approach using simple 360∘ azimuthal averages that were also derived.
Dashed lines again show the results assuming isotropic radiance distributions. The differences are less pronounced compared to the Zeppelin but still significant for the below a cloud layer. On the other hand, under clear-sky and above-cloud conditions, the assumption of isotropic radiance distributions in the lower hemisphere is apparently sufficient to obtain useful results.
A feature that stands out in Fig. 12 is the more pronounced altitude dependence of the for 300 nm. Modelled radiance distributions vary significantly already within the narrow UV-B range (280–320 nm), dependent on total ozone columns. Nevertheless, the influence of ozone columns on the corrections was found to be minor. At 1 km altitude, corrections obtained for ozone columns of 200 and 400 DU are within 1 % of the results for 300 DU for all solar zenith angles and wavelengths. At 10 km altitude, deviations exceeding 1 % were confined to solar zenith angles >80∘. Consequently, the influence of ozone columns was not considered in more detail. The validity of the final correction functions in the UV-B range for ozone columns of 200 and 400 DU will be shown in Sect. 5.3.2.
5.3 Interpolations and parametrizations
5.3.1 Ground station
The dependence of the modelled on atmospheric conditions is weak. Consequently, corrections for ground-based measurements of downward spectral actinic flux densities can be calculated for each wavelength and solar zenith angle, with uncertainties covering all atmospheric scenarios, including cloud cases and arbitrary azimuthal receiver orientations with respect to the sun. The resulting uncertainties range around 2 %–3 % in the UV range, dependent on receiver properties and solar zenith angles. Final results for the four receivers examined in this work are shown in Fig. S26 for selected wavelengths. Through interpolations, these corrections become applicable to measurements under all conditions by interpolating corrections and uncertainties as functions of solar zenith angles and wavelengths. Because of smooth changes with both variables, these interpolations introduce no additional uncertainties. In the UV range, even constant values that are independent of solar zenith angle and measurement conditions are sufficient. Further aspects and possible refinements related to ground-based measurements are discussed in Sect. 7.1.
5.3.2 Airborne platforms
For the modelled , and of the airborne platforms, corrections as a function of wavelength, solar zenith angle and altitude alone are not useful because uncertainties become too large when all atmospheric scenarios are included, in particular for the . Refinements by accessing measured aerosol loads or cloud presence are difficult because the required small-scale, local information is usually not available along flight tracks. Moreover, the assignment to modelled scenarios is difficult, in particular for the cloud cases. Therefore parametrizations were developed which depend on the measured data alone and cover all modelled atmospheric scenarios.
A closer look at the correction functions reveals that the most variable values increase strongly when the ratios of upward to downward actinic flux densities go down, for example, towards low altitudes at low ground albedos, as explained in the previous section. Therefore the ratio Φm of upward to downward uncorrected spectral actinic flux densities was used as a parametrization variable. Φm has the advantage that it can be calculated directly from measured data in subsequent applications. For the modelled corrections, it is obtained from the following equation:
Plots of , and as a function of Φm covering all atmospheric scenarios indeed show compact relationships for a given altitude, solar zenith angle and wavelength. Examples for the Zeppelin at 1 km altitude are shown in Fig. 13. The and are weakly dependent on Φm and can be described by linear dependencies in good approximations. Full black and red lines show corresponding linear regressions. On the other hand, for the , linear approximations are inadequate, in particular at lower altitudes and small Φm. However, because the three correction functions are related to each other through Eq. (10), the values that correspond to the linearly approximated and can be calculated:
Equation (14) ensures the consistency of the three corrections according to Eq. (10) and leads to an adequate description of the observed non-linear dependence of on Φm, as shown by the full blue lines in Fig. 13. Ultimately, two linear parametrizations with four coefficients that depend on altitude, solar zenith angle and wavelength are required to describe the corrections within this approach for the Zeppelin.
Total uncertainties and of the parametrized corrections were obtained by adding the deviations from the regression lines to the uncertainties of each scenario, followed by linear regressions of the uncertainties as a function of Φm. Corresponding upper and lower limits are indicated by the dashed black and red lines in Fig. 13. As the corrections themselves, the and are weakly dependent on Φm. On the other hand, the uncertainties of are more variable and typically increase non-linearly with decreasing Φm. An adequate description was obtained by differentiating Eq. (14) with respect to and to derive theoretical upper limits of that were scaled by empirical factors :
The values were again obtained from linear regressions as a function of Φm, resulting in the upper and lower limits indicated by the dashed blue lines in Fig. 13. Typical values of range around 0.4, which is reasonable because the and are not independent and partly compensate for each other in the calculation of (Eq. 14).
For the three different HALO configurations, the same parametrization approach was used as for the Zeppelin but separately for each of the five solar heading angles. An example for an altitude of 5 km is shown in Fig. 14. At higher altitudes, the range of Φm generally becomes smaller, and the non-linearity of the is less pronounced. The distinction of different solar heading angles again confines the uncertainties, especially at large solar zenith angles and wavelengths.
Corrections from in-cloud model calculations at the intermediate altitudes of 3.5 km (As) and 11 km (Cs) as well as from above-cloud at 12 km (Cs) were not considered in the parametrizations. Nevertheless, the in-cloud results are reasonably covered within the uncertainty limits of the parametrizations using altitude-interpolated coefficients. Examples are shown in Fig. S27. However, for the greatest model altitude of 15 km, no below-cloud scenario was included. This leads to decreasing uncertainties which do not fully cover in-cloud or below-cloud conditions at greater altitudes in the interpolation range between 10 and 15 km. On the other hand, the presence of clouds at flight altitudes >12 km was rare during previous research flights, which justifies the current approach, resulting in smaller uncertainties at very high altitudes.
Ozone columns other than 300 DU were also not included in the parametrizations. As was explained in the last section, the influence of ozone columns on the corrections was minor. A comparison of correction functions obtained at total ozone columns of 200 and 400 DU with the parametrizations derived for 300 DU is shown in Fig. S28.
For both airborne platforms, the overall performance of the parametrizations gradually degrades with increasing solar zenith angles and wavelengths, resulting in correspondingly increasing uncertainties. At solar zenith angles >80∘, direct sun radiation can strike both receivers simultaneously, which can result in strongly enhanced corrections dependent on wavelength and atmospheric conditions. Consequently, no corrections with acceptable uncertainty limits that cover all measurement conditions can be derived for solar zenith angles >80∘. Exceptions are wavelengths below about 320 nm at all altitudes, as well as wavelengths below about 450 nm at low altitudes, where the contributions of direct sun are sufficiently small. Anyway, for the present, the application of the parametrizations is confined to solar zenith angles ≤80∘, which covers the predominant fractions of all research flights. Possible refinements for airborne measurements at solar zenith angles >80∘ will be discussed in Sect. 7. A detailed description of the correction procedure is given in Sect. S7.
6.1 Zeppelin flight example
An example of corrections derived for a Zeppelin flight under clear-sky conditions is shown in Fig. 15. On this day, the airship followed a quasi-stationary circular flight pattern for about 4 h during which six height profiles were flown between about 100 and 800 m above agricultural land in the Po valley, Italy, during the PEGASOS campaign (Li et al., 2014; Kaiser et al., 2015). The values show a wavelength-dependent periodic pattern induced by the altitude changes. On the other hand, the and and their uncertainties remain almost constant for a given wavelength within this flight's range of solar zenith angles.
The altitude dependence and the magnitude of the decrease with wavelength, which is explainable by increasing ground albedos over vegetated ground (Fig. S14) and decreasing diffuse sky radiance in the upper hemisphere captured by the bottom receiver. However, despite values of around 2 for the in the UV range, the are merely increased by about 5 % compared to the , which is reasonable if only small fractions of the total actinic flux densities are directed upward.
The final total, downward and upward spectral actinic flux densities are shown in Fig. 16, together with their total uncertainties and those resulting from the corrections. The latter are dominant for the upward component but less significant for the total and downward components. The different dependencies of the Fλ, and on altitude and solar zenith angle as a function of wavelength are qualitatively explainable. The increase of the from 300 to 600 nm at the lowest altitudes is caused by the increasing ground albedos. On the other hand, the increase of the with altitude is stronger for shorter wavelengths because of increased backscattering in the air column between the ground and the airship (Rayleigh and aerosol scattering). Increased scattering at shorter wavelengths also explains the different dependencies of the Fλ on solar zenith angles. In addition, the influence of stratospheric ozone enhances the solar zenith angle dependence for 300 nm. Expectedly, photolysis frequencies show similar patterns dependent on the wavelength range of the photolysis reactions. However, a more detailed analysis of photolysis frequencies is beyond the scope of this study.
6.2 HALO flight example
For HALO flights, the spatial and atmospheric condition ranges were typically much greater than for the Zeppelin. An example is shown in Fig. 17 where HALO performed a 9 h non-stop return flight from Taiwan to Japan over the East China Sea during the EMeRGe-Asia campaign. Several flight levels between 0.5 and 12 km were operated on this day under changing, partly cloudy atmospheric conditions. Again, the turned out to be most variable and uncertain, dependent on altitude and wavelength, but generally smaller compared to the Zeppelin. Minor, short-term variations at constant altitudes indicate sporadic cloud influence. Gaps in the data record mark periods where flight manoeuvres led to attitude deviations that exceeded the HALO-specific limit of 2.5∘. Towards the end of the flight, solar zenith angles approached 80∘, resulting in increased uncertainties of the at longer wavelengths.
The final spectral actinic flux densities and their uncertainties are shown in Fig. 18. The uncertainties from the corrections are again more significant for the , especially at low altitudes. Flux densities and uncertainties reveal a complex dependence on altitude, solar zenith angle and cloud presence for the selected wavelengths. The variability of the is strongly enhanced, and values can become as high as the through cloud influence. Accordingly, the total Fλ values increase during such periods. Cloud influence on is hardly visible in this specific flight but is clear in others, in particular at low altitudes. Because of wider ranges, the influence of altitude and solar zenith angles is greater than in the Zeppelin example. The minor differences between 500 and 600 nm are explainable by similar scattering properties of air, aerosols and clouds, as well as similar ocean albedos. An analysis of these data with the help of radiative transfer model calculations is currently under preparation but beyond the scope of this work. The corresponding photolysis frequencies again exhibit very similar, wavelength-dependent patterns. However, because of the greater altitude range, for some photolysis frequencies, the additional influence of temperature and pressure variations, affecting absorption cross sections and quantum yields, can become significant (Eq. 1).
7.1 Ground-based measurements
The correction functions for measurements of downward spectral actinic flux densities are comparable with previous results for other receivers from the same manufacturer (Hofzumahaus et al., 1999; Bohn et al., 2008). Except for one receiver and wavelengths >500 nm, the corrections remained below 10 %, with maximum uncertainties below 3 %. Moreover, for the four receivers used in this work, similar corrections were obtained using radiative transfer modelled and isotropic diffuse radiance distributions in the upper hemisphere. This result probably also holds for other receivers with comparable properties, which simplifies the calculations. However, this does not mean that corrections for ground-based measurements are generally straightforward or secondary. Substantial corrections and large uncertainties can result for receivers with poorer reception characteristics (Bohn et al., 2008), and, as already mentioned in the Introduction, the basically high accuracy of radiometric calibrations can be significantly degraded by uncertainties of receiver-related corrections. This issue may even remain unnoticed unless the quality of receivers is thoroughly tested. On the other hand, as shown in Fig. S28, a constant correction factor covering all conditions can be sufficient in the UV range. This is of relevance for measurements of j(O1D) and j(NO2) with filter radiometers. If a calibration of these instruments is done by comparison with a corrected reference instrument, receiver related mean corrections are already included (Bohn et al., 2004, 2008). In contrast, in the VIS range where significant contributions of direct radiation are possible at large solar zenith angles, further refinements can be helpful. The potential presence or absence of direct radiation increased the uncertainties of the when all atmospheric scenarios were included (Fig. S26). Therefore, uncertainties can be reduced if conditions with and without direct radiation are distinguished, either based on the measurements themselves, by the use of auxiliary instruments (sky cameras, pyrheliometers or sunshine recorders), or on a separate determination of the contribution of diffuse sky radiation. The latter is feasible using a classical shadow ring, a sun tracker or a rotating shadow band (only one receiver required). Such approaches would, for example, be useful for a more accurate determination of j(NO3) (λ≤640 nm) at low sun.
Generally, for measurements of downward spectral actinic flux densities, the cross-talk to the lower hemisphere should be minimized by sufficiently large artificial horizons, dependent on the local ground albedo, as already noted by Hofzumahaus et al. (1999), who estimated corrections of up to 15 % for a ground albedo of 0.9 (fresh snow) with a 150 mm diameter artificial horizon. As a consequence, the size of the artificial horizon (shadow ring) was doubled in subsequent applications of the same instrument (e.g. Bais et al., 2003; Bohn et al., 2008).
Ground-based measurements of upward spectral actinic flux densities may be desirable as well, for example, at sites with regular snow cover. However, useful measurements of upward spectral actinic flux densities are challenging. First, downward-facing receivers capture the reflective properties of the natural or artificial ground at close range which may be different from the ground in the surrounding area. A careful selection of the location is therefore important. If no suitable location is available, an estimation of upward from measured downward flux densities is possible based on typical ground albedos in the area (Madronich, 1987). Second, also a downward-facing receiver should be equipped with a large artificial horizon to prevent (i) cross-talk to the usually brighter, upper hemisphere and (ii) reception of direct solar radiation at low sun, although this is a minor problem in the UV range as mentioned in Sect. 5.3. The situation on the ground is comparable with the Zeppelin at very low altitudes, where the limited size of the extension flange produced overestimations by a factor of 2–3 in the UV range (Sect. 6.1). Similar overestimations are expected on the ground (at low ground albedos) unless the upper hemisphere is effectively shielded. Of course, if required, a 4π correction approach like for the Zeppelin can be implemented for a single, zero height above ground.
7.2 Airborne measurements
The correction functions , and for the Zeppelin and HALO typically produce changes no greater than 5 %–10 %. An exception are the values at low altitudes and low ground albedos, which can become significantly greater. The results are comparable with corrections applied in the literature for other airborne platforms. A direct comparison with previous work is difficult because the corrections are specific for each experimental setup and the individual receivers employed.
Volz-Thomas et al. (1996) used a prototype of the quartz dome receivers employed since then to measure j(NO2) with filter radiometers (370±40 nm) on board a Lockheed C-130. The diameter of the base flanges was limited to 200 mm, and the authors optimized the total angular sensitivity with circular rims at the flange edges acting as artificial horizons. The performance of the 4π reception characteristics was tested in-flight by dedicated circular flight patterns with roll angles of 30∘ at different solar zenith angles, which merely resulted in small variations of the total radiometer signals. From these test flights, uncertainties of the total j(NO2) caused by the 4π receiver imperfections of 1.5 % and 6 % were estimated for solar zenith angles below and above 75∘, respectively. For downward and upward contributions under horizontal flight conditions, altitude-dependent correction factors in a range 1.00–1.04 and 0.69–1.01 were derived, respectively, with uncertainties of 2 % and 5 %–12 % at solar zenith angles ≤75∘. These factors, which correspond to reciprocal values of the and defined in this work, were derived based on radiative transfer calculations, including the polar angle dependence of diffuse radiances, though confined to clear-sky conditions. In qualitative agreement with the results presented here, the corrections for the upward component increased with decreasing altitude, leading to a minimum factor of 0.69 () close to the ground.
Shetter and Müller (1999) employed a similar setup as Volz-Thomas et al. (1996) on a Douglas DC-8 for spectral actinic flux density measurements in a range 280–420 nm. No wavelength dependencies of angular sensitivities were detected and the effects of receiver imperfections were calculated assuming isotropic radiance distributions of diffuse sky radiation in both hemispheres. Average corrections of 1.036 and 1.027 which correspond to the were derived for the UV-B and UV-A range, respectively, independent of measurement conditions, with an estimated uncertainty of 4 %. Because the work focused on photolysis frequencies from total spectral actinic flux densities, no separation of upward and downward components was done. In a follow-up study by Shetter et al. (2003), the DC-8 inlet configuration was modified and equipped with larger 300 mm artificial horizons (including rims), which resulted in close to ideal angular responses in both hemispheres. Consequently, no corrections were applied for total, downward and upward spectral actinic flux densities, and the remaining uncertainty was estimated to be 1.5 %. The distinction of upward and downward contributions was confined to conditions where aircraft pitch or roll angles did not exceed ±5∘. A second, similar setup as on the DC-8 was installed on a Lockheed P-3B aircraft (Shetter et al., 2003; Lefer et al., 2003), and in-flight intercomparisons of the two instruments confirmed good agreements of j(O1D) and j(NO2) from total spectral actinic flux densities within 2 % (Eisele et al., 2003).
Hofzumahaus et al. (2002) made clear-sky spectroradiometer measurements on a Falcon-20E aircraft in a range 280–420 nm. Similar to HALO, the smaller size of the aircraft did not allow for extended artificial horizons, and the upward- and downward-looking receivers were tilted in the flight direction by ±5∘ to compensate for the typical pitch angle. The overall angular sensitivity of the receiver assembly was comparable with that described in this work. The consequences of the non-ideal 4π behaviour were investigated by radiative transfer calculations, including spectral radiance distributions under the measurement conditions. The deviations for total spectral actinic flux densities ranged from +1.4 % (0.1 km) to +3.6 % (12 km) at solar zenith angles <23∘ under clear-sky conditions. From these calculations, a maximum 4 % overestimation () was derived, but no corrections were applied. Upward and downward components were not distinguished.
Jäkel et al. (2005) performed spectral actinic flux density measurements in a range 305–700 nm on a Partenavia P68-B in an altitude range below about 3 km. These authors used a stabilization system that kept the receivers horizontal within ±0.2∘ as long as pitch or roll angles did not exceed ±6∘. This system was originally designed for an accurate distinction of upward and downward spectral irradiances (Wendisch et al., 2001). The size of the artificial horizons was limited by the stabilization system to a diameter of about 130 mm. Consequently, the mutual cross-talk was significant and corrected for separately for the upward- and downward-looking receivers by adopting the concept of hemispherical correction functions using isotropic diffuse radiance distributions (Hofzumahaus et al., 1999). The wavelength and altitude dependence was investigated for clear-sky and cloudy conditions. For the downward component, a maximum correction of around 1.08 (i.e. ) was obtained in the VIS range for an altitude of 2 km, above a highly reflective cloud. For the upward component, a maximum correction of around 1.35 (i.e. ) was reported in the UV range for an altitude of 1 km under clear-sky conditions using a surface albedo of 0.08. The final corrections were made along the flight tracks by attributing measurement conditions to the modelled scenarios. The uncertainty of these corrections was estimated to be 2 %.
Stark et al. (2007) made spectroradiometer measurements on a modified Lockheed WP-3 aircraft covering a wavelength range 280–690 nm. The setup followed that of Shetter et al. (2003) using a 300 mm artificial horizon with an outer rim. A correction function corresponding to the was estimated for isotropic radiation, ranging between about 0.99 for 300 nm to 0.95 for 600 nm. These corrections were applied independent of measurement conditions which was accounted for by an additional 3 % error. Upward and downward components were not distinguished.
Generally, on bigger aircraft, the base flanges that form artificial horizons can be larger without imposing aerodynamic issues. Under these circumstances, negligible corrections within small uncertainties can be achieved, as demonstrated by Shetter et al. (2003). Moreover, a combination of two virtually ideal 2π receivers is expected to perform independent of aircraft attitude, as long as only total actinic flux densities are of interest (Shetter and Müller, 1999). On the other hand, even with two perfect hemispheric receivers, a distinction of upward and downward flux densities requires close to horizontal flight conditions or an active stabilization (Jäkel et al., 2005).
For HALO, the mutual cross-talk of the receivers and aircraft-specific field-of-view effects were more significant than in most previous studies, which motivated the extended correction approach of this work. The effort is justified because of the large number of HALO flights for which corrections are required, including further campaigns scheduled in the future. For the Zeppelin, mainly the cross-talk of the downward-facing receiver to the upper hemisphere was significant and produced enhanced under conditions with low ground albedo. The distinct dependence of the on the parameter Φm was instructive to derive the parametrization concept, which also proved to be useful for HALO. The main advantage of the parametrizations is that no potentially uncertain or unavailable information on the atmospheric state is required. Moreover, because different wavelengths are treated separately, it is irrelevant whether or not the wavelength dependencies of ground albedos and aerosol optical depths in the model scenarios are realistic for the measurement conditions.
The use of isotropic radiance distributions for the calculation of the corrections led to slightly different results and cannot be recommended in general because the extent of the differences depends on receiver properties and atmospheric conditions. The computational effort to derive the corrections is slightly lower, but a wide range of conditions with different contributions of direct sun should be covered anyway. Moreover, under below-cloud conditions, the assumption of isotropic radiances is clearly unrealistic for the upper hemisphere. Analytical expressions exist for the polar angle dependence of radiances under overcast conditions that can be easily implemented instead of constant radiances (e.g. Mayer and Kylling, 2005).
For the determination of total actinic flux densities and photolysis frequencies alone, the strict limitations with regard to aircraft attitudes of 2.5 or 5∘ can be relaxed in order to increase data coverage. Uncertainties for total actinic flux densities could be determined for greater maximum attitudes, or alternatively, corrections and uncertainties could be calculated as a function of attitude. However, as is evident from the example flights shown in Figs. 16 and 18, the current attitude limitations are not critical for Zeppelin and HALO measurements.
The application of the parametrizations was limited to conditions with solar zenith angles ≤80∘ because corrections for different atmospheric conditions become too variable when direct sunlight can strike both receivers simultaneously. This limitation affected a minor fraction of research flights on both HALO and the Zeppelin, but occasionally conditions with very low sun or day-to-night transitions were encountered. A reliable correction under such conditions would require an estimate of the contribution of direct sunlight (ideally based on the measurements themselves) and accurate radiative transfer model calculations at low sun, including solar zenith angles >90∘. As mentioned in Sect. 4.2, the currently applied radiative transfer model in plane-parallel geometry will not give reliable results at low sun. The libRadtran package offers solutions in spherical geometry with advanced Monte Carlo solvers, but these calculations are computationally more demanding. Moreover, a concept of how to practically combine the model results with the measurements to derive useful corrections has not been developed so far but may be worthwhile if twilight conditions become of greater interest, for example, for an accurate determination of j(NO3).
Accurate measurements of spectral actinic flux densities require specific corrections to compensate for typical angular reception imperfections of optical receivers. A refined method to determine relative sensitivities of commonly used 2π solid-angle optical receivers in the laboratory was presented in this work. The properties of four receivers were specified that were either employed separately on the ground to obtain downward spectral actinic flux densities or pairwise on airborne platforms to measure upward and downward spectral actinic flux densities. Correction functions were calculated based on the relative sensitivities, further platform characteristics (field-of-view effects and fuselage reflections) and spectral radiance distributions from a radiative transport model in a wavelength range 280–660 nm for a number of atmospheric scenarios, intended to cover all realistic measurement conditions. The results were generally found to depend on wavelength and measurement conditions (solar zenith angle, altitude and ground albedo), including atmospheric variables (cloud cover and aerosol load). For ground-based measurements, corrections for downward spectral actinic flux densities were determined, and mean values as a function of wavelength and solar zenith angle were derived, with uncertainties covering all atmospheric scenarios. For airborne measurements, corrections for upward, downward and total spectral actinic flux densities were calculated separately. Parametrizations of corrections as a function of wavelength, solar zenith angle and altitude were developed that use upward/downward ratios of measured, uncorrected actinic flux densities as input and provide uncertainties that cover all atmospheric scenarios. These parametrizations reproduce the mutual dependence of corrections and their uncertainties, resulting in consistent results for upward, downward and (photochemically relevant) total spectral actinic flux densities. The application was limited to conditions with solar zenith angles smaller than 80∘ and aircraft attitudes deviating less than 2.5∘ or 5.0∘ from normal flight conditions. The corrections derived in this work typically ranged well below 10 % for total and downward spectral actinic flux densities but became more significant for upward spectral actinic flux densities, dependent on the platform and atmospheric conditions. Although all results are receiver- and platform-specific, the method is generally applicable to other, comparable instruments and can improve the accuracy of spectral actinic flux density measurements and resultant photolysis frequencies for many applications.
The libRadtran input file examples compatible with version 2.0.4, as well as spectral radiance output and corrections for all atmospheric scenarios are available under https://doi.org/10.26165/JUELICH-DATA/8INBXK (Bohn, 2022). Note that the corrections, are specific for the receivers and measurement configurations used in this work.
The supplement related to this article is available online at: https://doi.org/10.5194/amt-16-209-2023-supplement.
Both authors designed the study and made field campaign and laboratory measurements, as well as radiative transfer calculations. BB did the final analysis and wrote the manuscript.
The contact author has declared that neither of the authors has any competing interests.
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This article is part of the special issue “Effect of Megacities on the Transport and Transformation of Pollutants at Regional and Global Scales (EMeRGe) (ACP/AMT inter-journal SI)”. It is not associated with a conference.
The authors thank a great number of people who helped to get instruments airborne on the platforms Zeppelin NT and HALO. We thank Enviscope GmbH for technical support with certifications and installations on HALO. We thank Zeppelin Luftschifftechnik and the Sensor and Data Group of DLR Flight Experiments department for providing aircraft avionic data. Regarding the campaign data examples in this work, we particularly thank Astrid Kiendler-Scharr and Thomas F. Mentel (Forschungszentrum Jülich) for organizing the PEGASOS Zeppelin campaign, as well as Maria Dolores Andrés Hernández and John P. Burrows (University of Bremen) for organizing the HALO EMeRGe campaign. We thank the Japan Aerospace Exploration Agency for the provision of high-resolution ground elevations from the ALOS Global Digital Surface Model (AW3D30). We thank Bernhard Mayer, Arve Kylling and the other developers of the libRadtran model for making this tool available for the scientific community. We thank Michael Decker (Forschungszentrum Jülich) for technical support with model calculations and the publication of the data. We thank DLR Flight Experiments for providing the drawing of HALO used in Fig. 3 and the Deutsche Forschungsgemeinschaft (DFG) for funding.
This research has been supported by the Deutsche Forschungsgemeinschaft (DFG; grant nos. BO 1580/4-1 and BO 1580/5-1) within the HALO SPP 1294 priority programme.
The article processing charges for this open-access publication were covered by the Forschungszentrum Jülich.
This paper was edited by Manfred Wendisch and reviewed by two anonymous referees.
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