CN105352609A - Optical remote-sensing satellite absolute radiation scaling method based on spatial Lambert globe - Google Patents
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Abstract
Description
技术领域technical field
本发明属于遥感卫星辐射定标领域，涉及一种对空间光学遥感卫星的在轨辐射性能进行常态化绝对定标的方法。The invention belongs to the field of remote sensing satellite radiation calibration and relates to a method for normalized absolute calibration of the on-orbit radiation performance of space optical remote sensing satellites.
背景技术Background technique
随着遥感应用的深入，定量遥感已成为遥感应用的重点，而定量遥感的基础和前提是遥感器的辐射定标。空间遥感器的辐射定标可以分为发射前的实验室定标和发射后的在轨定标。由于卫星发射之后，随着工作环境和长期工作状态等各种因素的影响，都可能使发射前的定标系数发射改变，因此发射后的在轨定标是确保遥感数据可靠度和准确度的关键。With the deepening of remote sensing applications, quantitative remote sensing has become the focus of remote sensing applications, and the basis and premise of quantitative remote sensing is the radiometric calibration of remote sensors. The radiometric calibration of space remote sensors can be divided into laboratory calibration before launch and on-orbit calibration after launch. After the satellite is launched, with the influence of various factors such as the working environment and long-term working status, the calibration coefficient before launch may be changed. Therefore, the on-orbit calibration after launch is the key to ensure the reliability and accuracy of remote sensing data. The essential.
发射后的在轨定标方法主要有场地定标、星上定标等方法。场地定标是依赖地球表面大面积均匀稳定的地物作为定标源，实现在轨卫星的辐射定标，该类方法受到地物目标特性和大气状况影响，其定标精度偏低且成本较高。星上定标是通过星上定标装置实现定标，根据所用定标光源的不同，主要有内置灯、月球、恒星、太阳定标等方式。内置灯是早期的定标方案中常用的一种方式，但是内置灯是一种加入到光路中的人工光源，存在非全光路、与太阳光谱分布差异大等缺陷。月球通过依靠太阳而发光，其光谱特性与太阳光谱以及月球本身的吸收、反射特性相关，由于目前尚未获得准确的月球光谱分布，其辐照模型尚未达到实际应用的精度，因此通过月球定标的方式还不能直接用于绝对定标中，只可以用于相对辐射校正。恒星作为一种天体目标，也具有一定亮度，但是除太阳外目前研究中的恒星亮度均无法达到要求，无法用于星上辐射定标。目前常用的一个定标光源是太阳，它是一个均匀且高度稳定的朗伯光源，通过反射或者透射的方式将太阳能量衰减到合适的范围后，能够为空间遥感器提供稳定且精确的定标途径。通过星载太阳漫射板，覆盖有漫射材料的太阳漫反射板均具有很好的均匀性和朗伯特性，太阳漫射板打开后可以实现对遥感器的太阳定标，这种方法一般具有全口径、全光路、光谱匹配性好等优点，是目前星上定标的主要手段之一。但是受到技术条件限制，这种方式需要在卫星本身安装单独的太阳漫反射板，其结构设计复杂，容易受到卫星排出物的污染，而且增加了整星系统的运行负担，此外这种方式中零部件的失效将对后续的定标工作带来巨大的影响。The on-orbit calibration methods after launch mainly include field calibration and on-board calibration. Site calibration relies on a large area of uniform and stable ground objects on the earth's surface as a calibration source to realize radiation calibration of satellites in orbit. This type of method is affected by the characteristics of ground objects and atmospheric conditions, and its calibration accuracy is low and the cost is relatively high. high. On-board calibration is achieved through an on-board calibration device. According to the different calibration light sources used, there are mainly methods such as built-in light, moon, star, and sun calibration. The built-in light is a commonly used method in the early calibration schemes, but the built-in light is an artificial light source added to the optical path, which has defects such as a non-full optical path and a large difference in spectral distribution from the sun. The moon emits light by relying on the sun, and its spectral characteristics are related to the solar spectrum and the absorption and reflection characteristics of the moon itself. Since the accurate lunar spectral distribution has not yet been obtained, its irradiance model has not yet reached the accuracy of practical application. Therefore, through the lunar calibration The method cannot be directly used for absolute calibration, but only for relative radiometric correction. As a kind of celestial object, stars also have a certain brightness, but except for the sun, the brightness of the stars in the current research cannot meet the requirements, and cannot be used for on-star radiation calibration. A commonly used calibration light source is the sun, which is a uniform and highly stable Lambertian light source. After attenuating the solar energy to an appropriate range through reflection or transmission, it can provide stable and accurate calibration for space remote sensors. way. Through the space-borne solar diffuser, the solar diffuse reflector covered with diffuse material has good uniformity and Lambertian properties. After the solar diffuser is opened, the solar calibration of the remote sensor can be realized. This method generally has The advantages of full aperture, full optical path, and good spectral matching are currently one of the main means of on-board calibration. However, limited by technical conditions, this method needs to install a separate solar diffuse reflector on the satellite itself. Its structural design is complex, it is easily polluted by satellite exhaust, and it increases the operating burden of the entire star system. In addition, this method has zero The failure of components will have a huge impact on the subsequent calibration work.
发明内容Contents of the invention
本发明解决的技术问题是：克服现有技术的不足，提供了一种基于空间朗伯球体的光学遥感卫星绝对辐射定标方法，可以在不增加额外星载定标设备的基础上，摆脱地面目标特性的影响和大气条件的影响，以太阳为定标源实现全光路、全孔径、光谱匹配的高精度绝对辐射定标。The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, and to provide an absolute radiometric calibration method for optical remote sensing satellites based on a space Lambertian sphere, which can get rid of ground Influenced by target characteristics and atmospheric conditions, the sun is used as the calibration source to achieve high-precision absolute radiation calibration with full optical path, full aperture, and spectral matching.
本发明的技术解决方案是：一种基于空间朗伯球体的光学遥感卫星绝对辐射定标方法，包括如下步骤：The technical solution of the present invention is: a kind of optical remote sensing satellite absolute radiometric calibration method based on space Lambertian sphere, comprises the following steps:
(1)通过运载火箭发射方式或者卫星释放发射方式向空间中发射一颗人造朗伯球体，球体的直径与轨道位置满足卫星定标对信号能量的要求；所述的人造朗伯球体为表面具有接近朗伯特性的均匀球体；(1) launch an artificial Lambertian sphere into space by means of carrier rocket launch or satellite release launch, the diameter and orbital position of the sphere meet the requirements of satellite calibration for signal energy; the artificial Lambertian sphere has a A homogeneous sphere close to Lambertian;
(2)设置待标定卫星遥感器的参数，使积分时间、增益和级数在整个标定过程中保持不变；(2) Set the parameters of the satellite remote sensor to be calibrated so that the integration time, gain and series remain unchanged throughout the calibration process;
(3)对卫星进行姿态机动，使待标定卫星遥感器指向深空背景，获取待标定卫星遥感器成像像元的灰度值，共进行n次测量，得到每次测量的像元k的灰度值DNk0i，其中n≥1，k为遥感器像元的位置，k的取值范围是从1到遥感器像元的总数，i为测量的次数，i＝1,2,3......,n；n次测量完成之后，计算出待标定卫星遥感器像元k的背景信号平均值DNk0，(3) Maneuver the attitude of the satellite, make the remote sensor of the satellite to be calibrated point to the deep space background, obtain the gray value of the imaging pixel of the remote sensor of the satellite to be calibrated, and perform a total of n measurements to obtain the gray value of the pixel k of each measurement Degree value DN k0i , where n≥1, k is the position of the remote sensor pixel, the value range of k is from 1 to the total number of remote sensor pixels, i is the number of measurements, i=1,2,3.. ...., n; after n measurements are completed, calculate the average background signal DN k0 of pixel k of the satellite remote sensor to be calibrated,
(4)建立包含卫星、人造朗伯球体和太阳的场景，仿真太阳辐射能量的传递，得到卫星、人造朗伯球体和太阳三者之间的位置关系满足定标条件的时间段；所述的定标条件包括几何可见条件和传感器可见条件，几何可见条件为卫星与人造朗伯球体二者之间的连线不受地球遮挡，传感器可见条件为人造朗伯球体处于地影之外，人造朗伯球体能够反射太阳辐射能从而实现观测成像；(4) set up the scene that comprises satellite, artificial Lambertian sphere and the sun, simulate the transmission of solar radiation energy, obtain the time period when the positional relationship between the satellite, artificial Lambertian sphere and the sun satisfies the calibration condition; Calibration conditions include geometric visible conditions and sensor visible conditions. The geometrically visible condition is that the line between the satellite and the artificial Lambertian sphere is not blocked by the earth. The sensor visible condition is that the artificial Lambertian sphere is outside the shadow of the earth. The Bo sphere can reflect solar radiation energy to achieve observation and imaging;
(5)从满足定标条件的时间段中选取某一成像时刻点，对卫星进行姿态机动，使待标定卫星遥感器的入瞳法线指向朗伯球体，将遥感器观测人造朗伯球体的方位角记为φ，获取人造朗伯球体与太阳的相对距离L1(j)、人造朗伯球体与待定标卫星遥感器入瞳处的相对距离L2(j)、太阳与人造朗伯球体之间的连线以及待定标卫星遥感器与人造朗伯球体之间的连线的夹角θj，由此得到人造朗伯球体反射太阳辐射能到达卫星遥感器入瞳处的辐照度Ekj，人造朗伯球体像点对应的像元位置k及灰度值DNkj；(5) Select an imaging time point from the time period that satisfies the calibration conditions, and perform attitude maneuver on the satellite, so that the entrance pupil normal of the remote sensor of the satellite to be calibrated points to the Lambertian sphere, and the remote sensor observes the artificial Lambertian sphere. The azimuth angle is denoted as φ, and the relative distance L 1(j) between the artificial Lambertian sphere and the sun, the relative distance L 2 (j) between the artificial Lambertian sphere and the entrance pupil of the remote sensor of the satellite to be calibrated, and the relative distance between the sun and the artificial Lambertian sphere and the included angle θ j of the line between the satellite remote sensor to be calibrated and the artificial Lambertian sphere, thus obtaining the irradiance E at which the artificial Lambertian sphere reflects solar radiation and reaches the entrance pupil of the satellite remote sensor kj , the pixel position k corresponding to the artificial Lambertian sphere image point and the gray value DN kj ;
(6)在保持φ不变的条件下，重复步骤(5)，得到像元k的n次测量对应的灰度值DNkj和入瞳辐照度Ekj，结合像元的背景信号值DNk0，通过最小二乘法建立线性响应关系，得到像元k的绝对辐射定标系数Gk，(6) Under the condition of keeping φ constant, repeat step (5) to obtain the gray value DN kj and entrance pupil irradiance E kj corresponding to the n measurements of pixel k, combined with the background signal value DN of the pixel k k0 , the linear response relationship is established by the least square method, and the absolute radiation calibration coefficient G k of pixel k is obtained,
所述步骤(1)中卫星定标对信号能量的要求为：卫星遥感器能够接收到人造朗伯球体反射的太阳光能量，且卫星遥感器中的探测器产生的信号电压位于探测器饱和信号电压值的20％～80％之间。In the step (1), the satellite calibration requires that the signal energy is: the satellite remote sensor can receive the sunlight energy reflected by the artificial Lambertian sphere, and the signal voltage generated by the detector in the satellite remote sensor is at the saturation signal of the detector. Between 20% and 80% of the voltage value.
所述的人造朗伯球体为铝制球体，表面通过粘合剂涂覆有硫酸钡粉。The artificial Lambertian sphere is an aluminum sphere, and the surface is coated with barium sulfate powder through an adhesive.
本发明与现有技术相比的优点在于：The advantage of the present invention compared with prior art is:
(1)本发明方法采用朗伯球体将太阳辐射作为定标源间接引入遥感器，定标源位于整个系统外部，能对整个光路中的光学元件进行定标，还可充满遥感器孔径，满足全光路、全孔径、与太阳光谱分布匹配的辐射定标要求；(1) The inventive method adopts the Lambertian sphere to indirectly introduce the solar radiation into the remote sensor as a calibration source. The calibration source is located outside the entire system, can calibrate the optical elements in the entire optical path, and can also fill the remote sensor aperture to meet Radiation calibration requirements for full optical path, full aperture, and solar spectral distribution matching;
(2)本发明方法采用在轨的朗伯球体直接反射太阳辐射，摆脱了大气条件和地面目标特性的限制，避免了太阳辐射传递链路中大气、地面目标等环境因素引入的不确定性，提高了在轨绝对辐射定标精度；(2) the inventive method adopts the Lambertian sphere on orbit to directly reflect solar radiation, gets rid of the limitation of atmospheric conditions and ground target characteristics, and avoids the uncertainty introduced by environmental factors such as atmosphere and ground targets in the solar radiation transfer link, Improved on-orbit absolute radiometric calibration accuracy;
(3)本发明方法通过在空间中部署朗伯球体，建立了统一的空间光学辐射基准，可以对卫星遥感器实现常态化监测，及时修正卫星遥感器的辐射响应变化，提高卫星遥感器的在轨辐射定标响应效率；(3) The method of the present invention establishes a unified space optical radiation reference by deploying Lambertian spheres in space, which can realize normalized monitoring of satellite remote sensors, correct the radiation response changes of satellite remote sensors in time, and improve the satellite remote sensors. Orbit radiation calibration response efficiency;
(4)本发明方法通过使用在轨的朗伯球体就可开展定标，易于实现，无需在卫星本身安装额外的定标仪器设备，有利于减轻现有光学遥感卫星星上系统的负担。(4) The method of the present invention can carry out the calibration by using the Lambertian sphere in orbit, which is easy to implement, and does not need to install additional calibration equipment on the satellite itself, which is conducive to reducing the burden on the existing optical remote sensing satellite on-board system.
附图说明Description of drawings
图1为本发明方法的流程框图；Fig. 1 is a block flow diagram of the inventive method;
图2为本发明的太阳辐射能传递模型示意图；Fig. 2 is the schematic diagram of solar radiation energy transfer model of the present invention;
图3为本发明的特征参量示意图；Fig. 3 is the characteristic parameter schematic diagram of the present invention;
图4为本发明的朗伯球体反射信号DN值与深空背景信号DN值的关系。Fig. 4 is the relationship between the Lambertian sphere reflection signal DN value and the deep space background signal DN value according to the present invention.
具体实施方式detailed description
如图1所示，为本发明方法的流程框图，主要步骤如下：As shown in Figure 1, it is a flow chart of the inventive method, and the main steps are as follows:
(1)通过运载火箭发射方式或者卫星释放发射方式向空间中发射一颗人造朗伯球体，球体的直径与轨道位置满足卫星定标对信号能量的要求；(1) launch an artificial Lambertian sphere into space by means of carrier rocket launch or satellite release launch, the diameter and orbital position of the sphere meet the requirements of satellite calibration for signal energy;
卫星定标对信号能量的要求为卫星遥感器接收到球体反射太阳光能量，遥感器中的探测器产生的信号电压位于探测器饱和信号电压值的20％～80％之间。The signal energy requirement of satellite calibration is that the satellite remote sensor receives the solar energy reflected by the sphere, and the signal voltage generated by the detector in the remote sensor is between 20% and 80% of the saturation signal voltage value of the detector.
所述的人造朗伯球体为表面具有接近朗伯特性的均匀球体，其中的一种实施例是硫酸钡朗伯球体，硫酸钡朗伯球体采用喷涂的方法制成。首先将均匀的铝制球体表面用砂纸磨光，将硫酸钡粉与乳白胶混合制成半糊状均匀地喷涂在磨光的铝制球体表面，干燥后即可获得人造朗伯球体。The artificial Lambertian sphere is a uniform sphere with a surface close to Lambertian, and one example thereof is a barium sulfate Lambertian sphere, which is made by spraying. First, polish the surface of the uniform aluminum sphere with sandpaper, mix barium sulfate powder with milky white glue to make a semi-paste and evenly spray it on the surface of the polished aluminum sphere, and obtain the artificial Lambertian sphere after drying.
(2)设置待标定卫星遥感器的参数，使积分时间、增益和级数在整个标定过程中保持不变。(2) Set the parameters of the satellite remote sensor to be calibrated so that the integration time, gain and series remain unchanged throughout the calibration process.
(3)对卫星进行姿态机动，使待标定卫星遥感器指向深空背景，获取待标定卫星遥感器成像像元的灰度值，进行n次(n≥1，次数越多，精度越高)测量，得到每次测量的像元的灰度值DNk0i，其中，k为遥感器像元的位置(k的取值范围是从1到遥感器像元的总数)，i为测量的次数，i＝1,2,3......,n，n次测量完成之后，计算出待标定卫星遥感器像元k的背景信号平均值DNk0 (3) Maneuver the attitude of the satellite, point the remote sensor of the satellite to be calibrated to the deep space background, obtain the gray value of the imaging pixel of the remote sensor of the satellite to be calibrated, and perform n times (n≥1, the more times, the higher the accuracy) Measurement, to obtain the gray value DN k0i of each measured pixel, where k is the position of the remote sensor pixel (the value range of k is from 1 to the total number of remote sensor pixels), i is the number of measurements, i=1,2,3...,n, after n measurements are completed, calculate the average value of the background signal DN k0 of the pixel k of the satellite remote sensor to be calibrated
(4)利用卫星工具软件STK仿真太阳辐射能的传递，建立包含卫星、朗伯球体和太阳的场景，得出当卫星、朗伯球体和太阳三者之间的位置关系满足定标条件下的时间段，太阳辐射能的传递模型如图2所示，图2中，朗伯球体将接收到的太阳辐射能后向外部反射，遥感器接收由朗伯球体反射的辐射能。(4) Use the satellite tool software STK to simulate the transfer of solar radiation energy, establish a scene including satellites, Lambertian spheres and the sun, and obtain that when the positional relationship among the satellites, Lambertian spheres and the sun satisfies the calibration conditions The transfer model of solar radiant energy during the time period is shown in Figure 2. In Figure 2, the Lambertian sphere reflects the received solar radiant energy to the outside, and the remote sensor receives the radiant energy reflected by the Lambertian sphere.
定标条件包括几何可见条件和传感器可见条件，两个条件必须同时满足。几何可见条件为卫星与朗伯球体二者之间的连线不受地球遮挡。传感器可见条件为朗伯球体处于地影之外，朗伯球体能够反射太阳辐射能从而实现观测成像。Calibration conditions include geometric visible conditions and sensor visible conditions, and the two conditions must be satisfied at the same time. The geometrically visible condition is that the connection line between the satellite and the Lambertian sphere is not blocked by the earth. The visible condition of the sensor is that the Lambertian sphere is outside the earth's shadow, and the Lambertian sphere can reflect solar radiation energy to achieve observation and imaging.
(5)从满足定标条件的时间段中任意选取某一成像时刻点，对卫星进行姿态机动，使待标定卫星遥感器的指向朗伯球体，卫星遥感器中的探测器可以获取朗伯球体反射太阳辐射能得到的信号。将遥感器观测朗伯球体的方位角，即遥感器与朗伯球体之间的连线与遥感器入瞳方向的夹角记为φ。(5) Randomly select an imaging time point from the time period that satisfies the calibration conditions, and perform attitude maneuver on the satellite so that the remote sensor of the satellite to be calibrated points to the Lambertian sphere, and the detector in the satellite remote sensor can obtain the Lambertian sphere The signal obtained by reflecting solar radiation. The azimuth angle of the Lambertian sphere observed by the remote sensor, that is, the angle between the line between the remote sensor and the Lambertian sphere and the direction of the entrance pupil of the remote sensor is recorded as φ.
(6)获取成像时刻点时刻，卫星、朗伯球体和太阳三者之间的位置关系。朗伯球体发射到空间特定轨道后，需要通过地面测量方式估算朗伯球体的在轨位置，得到卫星对朗伯球体成像时刻下的三个特征参量，包括朗伯球体与太阳的相对距离L1(j)、朗伯球体与待定标卫星遥感器入瞳处的相对距离L2(j)、太阳与朗伯球体之间的连线以及待定标卫星遥感器与朗伯球体之间的连线的夹角θj。特征参量的示意如图3所示。(6) Obtain the positional relationship between the satellite, the Lambertian sphere and the sun at the moment of imaging. After the Lambertian sphere is launched into a specific orbit in space, it is necessary to estimate the on-orbit position of the Lambertian sphere through ground measurement, and obtain three characteristic parameters at the time when the satellite images the Lambertian sphere, including the relative distance between the Lambertian sphere and the sun L 1 (j) , the relative distance L 2(j) between the Lambertian sphere and the entrance pupil of the satellite remote sensor to be calibrated, the connection line between the sun and the Lambertian sphere, and the connection line between the satellite remote sensor to be calibrated and the Lambertian sphere The included angle θ j . The schematic diagram of the characteristic parameters is shown in Figure 3.
(7)通过如下公式计算太阳辐射到达朗伯球体处的辐照度Ej。(7) Calculate the irradiance E j where the solar radiation reaches the Lambertian sphere by the following formula.
其中：in:
E(λ)为太阳辐射到达朗伯球体处的光谱辐射照度，单位为W·m-2·μm-1；E(λ) is the spectral irradiance at the place where the solar radiation reaches the Lambertian sphere, and the unit is W·m -2 ·μm -1 ;
λ1、λ2分别为待标定遥感器的谱段下限和上限；λ 1 and λ 2 are the lower limit and upper limit of the spectral band of the remote sensor to be calibrated respectively;
R为太阳半径，R＝6.9599×108m；R is the radius of the sun, R=6.9599×10 8 m;
j为测量次数。j is the number of measurements.
M(λ)为太阳的光谱辐射出射度(单位为W·m-2·μm-1)，太阳光源可以等效成温度为5900K的辐射黑体，根据普朗克黑体辐射公式，太阳的光谱辐射出射度可表示为式中，λ为波长，c1为第一黑体辐射常数(c1＝3.741844×104W·m-2·μm4)，c2为第二黑体辐射常数(c2＝14388μm·K)，T为热力学温度(T＝5900K)。M(λ) is the spectral radiance emission of the sun (in W·m -2 ·μm -1 ), the solar light source can be equivalent to a radiation black body with a temperature of 5900K, according to the Planck black body radiation formula, the spectral radiation of the sun The output degree can be expressed as In the formula, λ is the wavelength, c 1 is the first black body radiation constant (c 1 =3.741844×10 4 W·m -2 ·μm 4 ), c 2 is the second black body radiation constant (c 2 =14388μm·K), T is the thermodynamic temperature (T=5900K).
(8)通过如下公式计算卫星遥感器入瞳处的辐照度Ekj。(8) Calculate the irradiance E kj at the entrance pupil of the satellite remote sensor by the following formula.
其中：in:
ρ为朗伯球体的表面反射率；ρ is the surface reflectance of the Lambertian sphere;
f(θj)为反射能量与入射能量之间的夹角因子，通过对空间球体目标进行光学建模求出：f(θ j ) is the angle factor between the reflected energy and the incident energy, which is obtained by optical modeling of the space spherical target:
其中，d为朗伯球体直径；where d is the diameter of the Lambertian sphere;
(9)朗伯球体为点源目标，对朗伯球体成像后，获取其在探测器上所成的像点的位置和灰度值大小，分别记为k、DNkj。朗伯球体反射信号DN值与深空背景信号DN值的关系如图4所示，图中所示的情况中，像点位置k＝15，像点灰度值DNkj＝B。(9) The Lambertian sphere is a point source target. After imaging the Lambertian sphere, obtain the position and gray value of the image point on the detector, which are denoted as k and DN kj respectively. The relationship between the Lambertian sphere reflection signal DN value and the deep space background signal DN value is shown in Figure 4. In the situation shown in the figure, the image point position k=15, and the image point gray value DN kj =B.
(10)在保持φ不变的条件下，重复步骤(5)～(9)，得到像元k的n次测量对应的灰度值DNkj和入瞳辐照度Ekj。结合像元的背景信号值DNk0，通过最小二乘法建立线性响应关系，得到像元k的绝对辐射定标系数Gk，具体公式如下：(10) Under the condition of keeping φ constant, repeat steps (5) to (9) to obtain the gray value DN kj and entrance pupil irradiance E kj corresponding to the n measurements of pixel k. Combined with the background signal value DN k0 of the pixel, the linear response relationship is established by the least square method, and the absolute radiation calibration coefficient G k of the pixel k is obtained. The specific formula is as follows:
本发明说明书中未作详细描述的内容属本领域技术人员的公知技术。The content that is not described in detail in the description of the present invention belongs to the well-known technology of those skilled in the art.
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