Linear Two-Axis MOEMS Sun Sensor and the Need for MEMS in Space

Pedersen, Mangor

doi:10.2514/6.iac-03-u.2.b.02

Cited by 17 publications

(5 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Knowing the position of the satellite in its orbit, and the local vector of the magnetic field allows determining the relative orientation of the satellite with respect to the Earth. When SwissCube is not in the shadow of the earth, the attitude determination system is completed by third set of MEMS sensors, micromachined Sun sensors developed and fabricated at the Danish Technical University (DTU) [32]. One sensor is mounted on each face of the spacecraft, as illustrated in Figure 9.…”

Section: (Swiss) Cubesatmentioning

confidence: 99%

MEMS for space

Rooij

Gautsch

Briand

et al. 2009

TRANSDUCERS 2009 - 2009 International Solid-State Sensors, Actuators and Microsystems Conference

View full text Add to dashboard Cite

Future space exploration will emphasize on cost effectiveness and highly focused mission objectives. Missions costs are directly proportional to its total weight, thus, the trend will be to replace bulky and heavy components of space carriers, communication and navigation platforms and of scientific payloads.MEMS devices are ideally suited to replace several of these components in the future, first by substituting larger and heavier components (e.g. a gyroscope), then by replacing entire subsystems (e.g., inertial measurement unit), and finally by enabling the microfabrication of highly integrated picosats. This progressive approach will also enable new mission scenarios and more detailed investigations of the space environment and of planetary surfaces.Very small satellites (1 to 100 kg) stand to benefit the most from MEMS technologies because reaching the desired performance levels is only possible using a highly integrated approach. The small satellites are typically used for science or technology demonstration missions, with much higher risk tolerance than multi-ton telecommunication satellites. In addition, the ability to mass produce MEMS components opens a new approach to space exploration in the future by sending constellations of nano and picosatellites into space.Examples of such miniaturization and successful use of MEMS for space and planetary missions are described in this paper.

show abstract

Section: (Swiss) Cubesatmentioning

confidence: 99%

MEMS for space

Rooij

Gautsch

Briand

et al. 2009

TRANSDUCERS 2009 - 2009 International Solid-State Sensors, Actuators and Microsystems Conference

View full text Add to dashboard Cite

show abstract

“…The two methods described above do not show much difference in average error, and only a reduction of coefficients of the fitted polynomial results from adopting the physical modeling method. Pedersen et al considered the physical modeling method in developing a MEMS sun sensor, without considering the cross-coupling and shadowing effects [8]. It is claimed, in this case, that the slit thickness is minimal such that the shadow effect can be ignored.…”

Section: Introductionmentioning

confidence: 99%

“…Optical error due to the imperfection in geometry of the slit and the photo-cells can also contribute to the overall modeling errors. Optical error includes cross-coupling effect where the sensor output according to the incident angle of the light coming through the slit causes both azimuth and elevation angle errors, and the shadowing effect where the sensor output is affected by the slit thickness that causes a reduction in the actual area where the sunlight illuminates the photo-cell [5,6,[8][9][10].…”

Section: Introductionmentioning

confidence: 99%

A new modeling and validation of two-axis miniature fine sun sensor

Chang

Yun

Lee

2007

Sensors and Actuators A: Physical

View full text Add to dashboard Cite

“…So on many occasions, the total mass and power consumption will increase. For example in ADCS of AAUSAT II six coarse sun sensors are used [14] , ADCS of PIONEER spacecraft has 6 sun sensors [15] and 6 coarse sun sensors are applied in SCISAT ADCS [16] . Hence, a sun sensor with a small mass, low power and a wide FOV that can be replaced with two or more sensors will largely save mass and power.…”

Section: Introductionmentioning

confidence: 99%