Similar articles

Abstract: A spacecraft’s separation parameters directly affect its flying trace. If the parameters exceed their limits, it will be difficult to adjust the flying attitude of the spacecraft, and the spacescraft may go off-track or crash. In this paper, we present a composite optimization method, which combines angular velocities with external moments for separation parameters of large-eccentricity pico-satellites. By changing the positions of elastic launch devices, the method effectively controls the popping process under the condition of less change in the separation mechanism. Finally, the reasons for deviation of angular velocities and unreliable optimization results are presented and analyzed. This optimization method is proved through a ground test which offsets the gravity. Simulation and test results show that the optimization method can effectively optimize the separation parameters of large-eccentricity pico-satellites. The proposed method adapts particularly to the fixed and non-stable status elastic parameters, the distribution of all kinds of elastic devices, and large-eccentricity spacecrafts for which attitude corrections are difficult. It is generally applicable and easy to operate in practical applications.

一种大偏心皮卫星分离参数复合优化方法

[1]Chao J, Wang ZK, Zhang YL, 2015. Development of the new approach of formation initialization using spring separation mechanism considering J₂ perturbation. Adv Space Res, 55(11):2616-2627.

[2]Cui DL, Yan SZ, Li JL, et al., 2014. Dynamic analysis of satellite separation considering the flexibility of interface rings. J Aerosp Eng, 229(10):1886-1902.

[3]Cui DL, Zhao JL, Yan SZ, et al., 2015. Analysis of parameter sensitivity on dynamics of satellite separation. Acta Astronaut, 114(3):22-33.

[4]Fritz M, Berger PD, 2015. Can you relate in multiple ways? Multiple linear regression and stepwise regression. In: Kaufmann M (Ed.), Improving the User Experience Through Practical Data Analytics. Elsevier Inc., Boston, p.239-269.

[5]Hu J, Li HC, Zhou YP, 2012. The application of Levenberg-Marquardt algorithm in the image stitching. Telecom Mark, 2:149-154 (in Chinese).

[6]Hu XZ, Chen XQ, Tuo ZH, et al., 2013. Dynamics and transient perturbation analysis of satellite separation systems. Proc Inst Mech Eng G, 227(12):1968-1976.

[7]Hu XZ, Chen XQ, Zhao Y, et al., 2014a. Optimization design of satellite separation systems based on multi-island genetic algorithm. Adv Spac Res, 53(5):870-876.

[8]Hu XZ, Chen XQ, Tuo ZH, et al., 2014b. Simplified metrics of elastic potential energy for spacecraft separation dynamics. Acta Astronaut, 102:151-155.

[9]Hu XZ, Chen XQ, Zhao Y, et al., 2017. Active subspace approach to reliability and safety assessments of small satellite separation. Acta Astronaut, 131:159-165.

[10]Huang WH, Cao DQ, Han ZY, 2012. Advances and trends in dynamics and control of spacecrafts. Adv Mech, 42(4): 367-394.

[11]Iwasa T, Shi Q, Ando S, et al., 2007. Simplified SRS prediction method for pyroshock source of V-band clamp separation devices. 48^th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conf, p.1-12.

[12]Jiang C, Wang ZK, Zhang YL, 2015. Angular velocity depressing method of constrained and centroid biased on-orbit separation. Acta Aeronaut Astronaut Sin, 36(10): 3382-3392 (in Chinese).

[13]Jing C, Wang ZK, Fan L, et al., 2010. Dynamics analysis of the constrained and centroid biased on-orbit satellite separation. Flight Dynam, 28(1):76-79 (in Chinese).

[14]Lan W, Brown J, Toorian A, et al., 2006. CubeSat development in education and into industry. AIAA SPACE Forum, Article 7296.

[15]Leng JF, Gao X, Zhu JP, 2016. Application of multivariate linear regression statistical prediction model. Stat Dec, 7:82-85 (in Chinese).

[16]Li JL, Yan SZ, Tan XF, 2012. Modeling and simulation of clamp band dynamic envelope in a LV/SC separation system. Appl Mech Mater, 141:359-363.

[17]Li JL, Yan SZ, Tan XF, 2014. Dynamic-envelope analysis of clamp-band joint considering pyroshock of satellite separation. J Spacecr Rock, 51(5):1390-1400.

[18]Michaels D, Gany A, 2016. Modeling and testing of a tube-in-tube separation mechanism of bodies in space. Acta Astronaut, 129:214-222.

[19]Miyamoto K, Ui K, Miyashita S, et al., 2005. Tokyo tech separation demonstration TSD as M-V rocket sub-payload for nanosatellite separation mechanism. 56^th Int Astronautical Congress of the Int Astronautical Federation, the Int Academy of Astronautics, and the Int Institute of Space Law, Article IAC-05-B5.6.A.

[20]Paris C, 2015. Vibration tests on the preloaded LARES satellite and separation system. Aerosp Sci Technol, 42: 470-476.

[21]Qin ZY, Yan SZ, Chu FL, 2009. Axial stiffness analysis of clamp band system. J Astron, 30(5):2080-2085 (in Chinese).

[22]Qin ZY, Yan SZ, Chu FL, 2010. Dynamic analysis of clamp band joint system subjected to axial vibration. J Sound Vib, 329(21):4486-4500

[23]Qin ZY, Yan SZ, Chu FL, 2011. Dynamic characteristics of launch vehicle and spacecraft connected by clamp band. J Sound Vib, 330(10):2161-2173.

[24]Qin ZY, Yan SZ, Chu FL, 2012. Finite element analysis of the clamp band joint. Appl Math Model, 36(1):463-477.

[25]Qin ZY, Yan SZ, Chu FL, 2014. Influence of clamp band joint on dynamic behavior of launching system in ascent flight. J Aerosp Eng, 228(1):97-114.

[26]Singaravelu J, Jeyakumar D, Rao BN, 2011. Reliability and safety assessments of the satellite separation process of a typical launch vehicle. J Def Model Simul: Appl Method Technol, 9(4):369-382.

[27]Somanath S, Krishnan Kutty VK, Francis EJ, et al., 2001. Dynamics simulation of pyro actuated “ball lock” separation system for microsatellites to evaluate release shock. 9^th European Space Mechanisms and Tribology Symp, p.199-206.

[28]Tan XF, Yan SZ, 2010. Dynamic simulation and failure analysis of a clamp band system for spacecraft. J Tsinghua Univ (Sci Tech), 50:1205-1209 (in Chinese).

[29]Tayefi M, Ebrahimi M, 2009. Design and analysis of separation systems based on an optimization approach. 47^th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, p.436-445.

[30]Teng L, Jin ZH, 2016. Pico-satellite separation parameters optimization. J Astronaut, 37(10):1200-1206 (in Chinese).

[31]Wang QM, Meng XH, Yang QC, 2010. Research of simulation on programs of satellite secondary separation. J Syst Simul, 9(22):2217-2222 (in Chinese).

[32]Wu CJ, Xu XQ, 2014. New cage style pico-satellite deployer based on sliding guide structure. J Zhejiang Univ (Eng Sci), 48(3):548-554 (in Chinese).

[33]Wu CJ, Xu XQ, He XE, et al., 2013. A Novel Separation Mechanism Device for Controlling Pico-Satellite and Separation Method. China Patent, 201 210 573 701.

[34]Xie CX, Xu YT, Fu JZ, et al., 2014. Kinematic system design of the pico-satellite separation mechanism. J Astronaut, 35(6):626-632.