Development status of infrared earth sensors abroad

Sodern is a famous French star sensor and infrared earth sensor manufacturer. STD 15 and STD 16 are two typical dynamic biconical scanning earth sensors.

STD 15 has been applied to TC2 series, HIS2PASAT series, Hotbird series, WORLDSTAR series, N ILESAT series and other satellites since 19 1, mainly applied to geostationary orbit satellites. STD/KOOC-0/6 is mainly applied to all kinds of satellites in low earth orbit, and has been applied to SPOT 4, SPOT 5, ENVI2Sat, Helios/KOOC-0/A, Helios/KOOC-0/B, Helios 2A, Helios 2B, ADEOS/KOOC-0/,ADEOS 2, ETS7, ALOS and METOP 60.

In 2000, Sodern Company developed a miniature geostationary earth sensor STS02 (mainly working in geostationary orbit) without mechanical scanning structure to meet the development needs of satellite miniaturization. Compared with the previous unit scanning sensor, STS02 has the advantages of compact structure, small volume, light weight and low cost. It uses four crossed 32 yuan focal plane arrays (each array is composed of 2 × 16 units, and the length is about 102mm) as detection elements, and uses silicon thin film technology to realize the control connection between electromechanical control devices and micromechanical components. With this design, STS02, as a new infrared earth sensor, has been reduced by 2 /3 in size, reduced in mass from 3.5 kg to 1. 1 kg, and reduced in power consumption from 7.5W to 3.5W, which can better meet the development requirements of satellite miniaturization and miniaturization. Its accuracy can reach 0.07 ~ 0. 16, which meets the requirements of attitude control accuracy.

United States of America

Goodrich Company designed the world's first infrared sensor for spacecraft orientation in 1950s, and as a major manufacturer of NASA spacecraft, it produced a large number of high-performance infrared devices.

13- 4 10 is the latest generation of multi-2-mission horizon (MMS) produced by this company, which can be used for many types of spacecraft, including near-earth or 2-bit (Leo), medium-earth orbit (MEO) and geostationary orbit. It can provide a field of view of 16× 10, which is wider than the traditional infrared earth sensor. Its accuracy can also reach 0.05 ~ 0.08. In the aspect of microstructure, the sensor has also made a breakthrough, with the size of φ170 mm×120 mm. In addition, in the aspect of long life, the sensor can work in MEO orbit 10 years and in GEO orbit 15 years. The sensor has been selected as the main attitude sensor of the advanced UHF planning satellite of the US Air Force.

13- 4 10 adopts microstructure thermopile detector. When used in GEO orbit, two detectors are used, and the mass is less than 3 kg. When used in MEO, three probes are used and the mass is less than 4.5 kg. The power supply voltage is 2 1~70V ~ 70V DC, and the power consumption of each probe is less than 3W. When 13- 4 10 is used for attitude measurement, its deviation is much smaller than that of the conventional dynamic scanning sensor. When working in GEO orbit, the deviation is 0.0 13 and the rolling angle is 0.03. When working in MEO orbit, the deviation is 0.05 ~ 0.08.

13- 470-RH is a miniature static earth sensor. Compared with 13- 4 10, its performance has been further improved, and it has been successfully applied to such constellations as ORBCOMM, I2R ID IUM, GLOBALSTAR and more than 200 other satellites. It uses infrared thermopile focal plane array with double triangle structure as detector, and adopts appropriate optical processing and compensation algorithm to improve the measurement accuracy of the sensor. Because the 13- 470-RH probe can independently measure the attitude of one of the three axes, this double triangle configuration makes the three probes redundant with each other, ensuring its reliability and stability.

The field of view of 13- 470- RH is greater than 13- 4 10, and each probe is 20×14.8; Its size is φ 40 mm× 56 mm; Each probe weighs about 18 g, and the total mass of the whole set of equipment is about1kg; ; The power consumption of each probe is less than 300mW and the accuracy is 0.2. It can be seen that 13-470-RH has greatly improved compared with 13-4 10 in terms of field of view, size, quality and power consumption, and can better meet the development needs of satellite miniaturization.

Japan

CES3 is a cone scanning earth sensor produced by Astro Research Company in Japan. It consists of an optical head and an information processing circuit, and is equipped with a sun recognition probe. CES3 is mainly used for attitude control system of three-axis stabilized satellites with medium and low orbital altitude (100 ~ 3000 km). The scanning half-cone angle is 55, the scanning speed is 60 r/min, the resolution is 2 ′, and the field of view is 1.5× 1.5, which can achieve the accuracy (3σ. Its mass is 2.7kg, its size is φ 1 18mm×200mm, its power consumption is 2W, its normal working temperature range is -5 ~ 45℃, and its service life is more than 5 years.

Italy

ESS (Earth &; Sun elevations sen2sor) is an elevation detector used for attitude control of spinning satellites or three-axis stabilized satellites during orbit adjustment and rotation, which can be used for all kinds of satellites from low orbit to super synchronization. The sensor mainly includes two infrared earth elevation sensors and two slit sun elevation sensors, which work together and output current pulses. The rotation speed of the spacecraft and the elevation angles of the sun and the earth can be determined by the current pulses. At present, ESS has been successfully applied to more than 70 electronic communication satellites, scientific experimental satellites and remote sensing satellites, and its service life (GEO orbit) is as long as 15 years.

ESS earth sensor is mainly composed of earth sensor, sun sensor, mechanical interface, electronic circuit and data interface. The performance parameters of each part are as follows: Earth sensor: the working band is 14 ~ 16.25 micron, the field of view is 1.5× 1.5, and the random error is (3σ). Sun sensor: the working band is 0.4 ~ 1. 1μ m, the field of view is 80, the random error (3σ) is less than 0.0 1, and the system error (3σ) is less than 0.035; Mechanical part: the size is166mm×150mm×127mm, and the mass is less than1.4kg; ; Electronic circuit: input voltage is 15V, and power consumption is.

In addition, the working environment conditions of ESS are: rotating speed 10 ~ 100 r/min, working temperature -20 ~ 50℃, and storage temperature -30 ~ 60℃.

It can be seen that a single kind of sensor can no longer meet the requirements of high-precision attitude control system, so the combined sensor appears. The performance of the combined sensor in terms of accuracy, mass, volume and power consumption has been improved to some extent.