Skip to main content
SpringerLink
Log in

A mechanism for a deployable optical structure of a small satellite

  • Published:
International Journal of Precision Engineering and Manufacturing Aims and scope Submit manuscript

Abstract

In this paper, we present a deployment mechanism that is applicable to a deployable optical structure where the focus is on satellite miniaturization. It is designed with a passive deployment mechanism that utilizes a spring hinge. In order to confirm the feasibility of the designed deployable mechanism, we theoretically analyze the alignment errors (de-space, tilt, and de-center) that influence the optical performance of the structure. The theoretical results are as follows: a de-space of 180.0 µm, a tilt of 1941.3 µrad, and a decenter of 45.3 µm. In addition, we measure alignment errors to evaluate the actual alignment errors for a manufactured deployable mechanism. The experimental results are as follows: a de-space of 180.2 µm, a tilt of 218.8 µrad, and a de-center of 617.5 µm. Finally, we investigate the factors causing the differences between the theoretical and experimental values, and we suggest a method for improving the alignment errors.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

Abbreviations

L :

length of panel

h:

height of deployment mechanism

r :

magnitude of joint clearance

sh :

magnitude of hole margin for the screw assembly

sr :

tightened degree of screw

θ :

rotation between global coordinate system and local coordinate system

\(\overrightarrow {cl_j }\) :

error vector due to joint clearance

\(\overrightarrow {cl_sh }\) :

maximum error vector when fastening spring hinge and hole

\(\overrightarrow {cl_sr }\) :

error vector by degree of tightening of screw

\(\overrightarrow {cl_j } (i)\) :

error vector due to joint clearance of i-th case

\(\overrightarrow {cl_j } (j)\) :

error vector due to joint clearance of j-th case

\(\overrightarrow {cl_sh } (k)\) :

error vector when fastening spring hinge and hole of k-th case

\(\overrightarrow {cl_sr } (l)\) :

error vector by degree of tightening of screw of l-th case

\(\overrightarrow {cl}\) :

error vector in a,b,c,d that are considered an error of all kinds

X:

x component of global coordinate

Y:

y component of global coordinate

Z :

z component of global coordinate

x :

x component of local coordinate

y :

y component of local coordinate

z :

z component of local coordinate

\(\overrightarrow {a_{ideal} }\) :

ideal position vector of \(\vec a\)

\(\overrightarrow {b_{ideal} }\) :

ideal position vector of \(\vec b\)

\(\overrightarrow {c_{ideal} }\) :

ideal position vector of \(\vec c\)

\(\overrightarrow {d_{ideal} }\) :

ideal position vector of \(\vec d\)

\(\overrightarrow {a_{real} }\) :

real position vector of \(\vec a\)

\(\overrightarrow {b_{real} }\) :

real position vector of \(\vec b\)

\(\overrightarrow {c_{real} }\) :

real position vector of \(\vec c\)

\(\overrightarrow {d_{real} }\) :

real position vector of \(\vec d\)

\(\overrightarrow {a_i }\) :

i-th case of real position vector of \(\vec a\)

\(\overrightarrow {b_j }\) :

j-th case of real position vector of \(\vec b\)

\(\overrightarrow {c_k }\) :

k-th case of real position vector of \(\vec c\)

\(\overrightarrow {d_l }\) :

l-th case of real position vector of \(\vec d\)

\(\overrightarrow {v_1 }\) :

\(\vec a_i - \vec b_j\)

\(\overrightarrow {v_2 }\) :

\(\vec b_j - \vec c_k\)

References

  1. NASA, “NSAS FBC Task Final Report,” http://mars.nasa.gov/msp98/misc/fbctask.pdf (Accessed 23 OCT 2015)

  2. eoProtal Directory, “GeoEye-1,” https://eoportal.org/web/eoportal/satellite-missions/g/geoeye-1 (Accessed 23 OCT 2015)

  3. Harrison, F. A., Craig, W. W., Christensen, F. E., Hailey, C. J., Zhang, W. W., et al., “The Nuclear Spectroscopic Telescope Array (Nustar) High-Energy X-ray Mission,” The Astrophysical Journal, Vol. 770, No. 2, pp. 103, 2013.

    Article  Google Scholar 

  4. Xu, Z., Guannan, Y., Hai, H., and Xinsheng, W., “Deployment Analysis and Test of a Coilable Mast for BUAA Student Micro-Satellite,” Proc. of IEEE 3rd International Symposium on Systems and Control in Aeronautics and Astronautics (ISSCAA), pp. 1329–1332, 2010.

    Google Scholar 

  5. eoProtal Directory, “DST (Dobson Space Telescope,” https://eoportal.org/web/eoportal/satellite-missions/d/dst (Accessed 21 OCT 2015)

  6. Nakamura, Y., Eishima, T., Nagai, M., Funase, R., Enokuchi, A., et al., “University of Tokyo's Ongoing Student-Lead Pico-Satellite Projects-Cubesat Xi and Prism,” Proc. of 55th International Astronautical Congress, IAC-04-1AA-4.11.4.06, 2004.

    Google Scholar 

  7. Hachkowskil, M. R., “Mechanism Design Principles for Optical-Precision, Deployable Instruments,” Proc. of 41st Structures, Structural Dynamics, and Materials Conference and Exhibit, AIAA-2000-1409, 2000.

    Google Scholar 

  8. Telescope-Optics, “5.3. Misalignment,” http://www.telescope-optics. net/induced2.htm (Accessed 21 OCT 2015)

  9. Lee, S.-Y., Kim, G., Lee, Y.-S., and Kim, G.-H., “Optical Design and Tolerance Analysis of a New Off-Axis Infrared Collimator,” Int. J. Precis. Eng. Manuf., Vol. 15, No. 9, pp. 1883–1888, 2014.

    Article  Google Scholar 

  10. Angelidis, A. and Vosniakos, G.-C., “Prediction and Compensation of Relative Position Error Along Industrial Robot End-Effector Paths,” Int. J. Precis. Eng. Manuf., Vol. 15, No. 1, pp. 63–73, 2014.

    Article  Google Scholar 

  11. Akhadkar, C. A., Deoghare, A. B., and Vaidya, A. M., “Influence of Joint Clearance on Kinematic and Dynamic Parameters of Mechanism,” IOSR Journal of Mechanical and Civil Engineering, Vol. 10, No. 6, pp. 39–52, 2014.

    Article  Google Scholar 

  12. Schwab, A. L., Meijaard, J. P., and Meijers, P., “A Comparison of Revolute Joint Clearance Models in the Dynamic Analysis of Rigid and Elastic Mechanical Systems,” Mechanism and machine theory, Vol. 37, No. 9, pp. 895–913, 2002.

    Article  MATH  Google Scholar 

  13. £uczak, S., “Guidelines for Tilt Measurements Realized by Mems Accelerometers,” Int. J. Precis. Eng. Manuf., Vol. 15, No. 3, pp. 489–496, 2014.

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. School of Aerospace and Mechanical Engineering, Korea Aerospace University, 76, Hanggongdaehak-ro, Deogyang-gu, Goyang-si, Gyeonggi-do, 10540, South Korea

    Junwoo Choi, Dongkyu Lee, Kukha Hwang & Byungkyu Kim

Authors
  1. Junwoo Choi
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Dongkyu Lee
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Kukha Hwang
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Byungkyu Kim
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Byungkyu Kim.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Choi, J., Lee, D., Hwang, K. et al. A mechanism for a deployable optical structure of a small satellite. Int. J. Precis. Eng. Manuf. 16, 2537–2543 (2015). https://doi.org/10.1007/s12541-015-0325-5

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12541-015-0325-5

Keywords

Search

Navigation