Design evaluation of a large deployable mesh reflector

被引:1
作者
Tsunoda, H
Hariu, K
Kawakami, Y
Sugimoto, T
Miyoshi, K
机构
[1] Adv Space Commun Res Lab, Onboard Antenna Technol Sect, Chiyoda Ku, Tokyo 1010032, Japan
[2] Mitsubishi Elect Corp, Space Syst Dept, Mech Engn Sect, Kanagawa 2478520, Japan
关键词
D O I
10.2514/2.3533
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The deployment force over the deployment resistance force must: be considered in the deployment force design of deployable mesh reflectors. Deployment tests are usually conducted on the ground using gravitational force compensation to evaluate the deployment force design. The design evaluations resulting from deployment tests using a test object with a diameter of 7 m are described. Twenty-four magnetically suspended sliders were also used to suspend the test object to reduce the frictional loss of horizontal motion and to compensate for gravitational force. The deployment force is designed as three times the mesh reaction force and is generated by helical coil springs. The complete deployment performance is confirmed by three deployment tests. An increase in the deployment resistance force is verified through asynchronous deployment of the deployable structures and the gravitational force compensation error of the mesh surface. Surface accuracy tests and static load tests under the same configurations as the deployment test were conducted to confirm that a large deployable mesh reflector with a 1.0-mm-rms error surface and 0.13-Hz structural rigidity can be achieved.
引用
收藏
页码:108 / 113
页数:6
相关论文
共 12 条
[1]  
AKAISHI A, 1994, P 19 INT S SPAC TECH, P711
[2]  
Ebisui T, 1996, T JPN SOC AERONAUT S, V39, P101
[3]   Development of flight hardware for a large, inflatable-deployable antenna experiment [J].
Freeland, RE ;
Bilyeu, GD ;
Veal, GR .
ACTA ASTRONAUTICA, 1996, 38 (4-8) :251-260
[4]  
HIGUCHI K, 1996, P 20 INT S SPAC TECH, P234
[5]   VLBI SPACE-OBSERVATORY PROGRAM (VSOP) SATELLITE [J].
HIROSAWA, H ;
HIRABAYASHI, H .
IEEE AEROSPACE AND ELECTRONIC SYSTEMS MAGAZINE, 1995, 10 (06) :17-23
[6]  
KAYA N, 1996, 47 INT ASTR C INT AS
[7]  
NATORI MC, 1995, 46 INT ASTR C INT AS
[8]   Two-dimensional deployable hexapod truss [J].
Onoda, J ;
Fu, DY ;
Minesugi, K .
JOURNAL OF SPACECRAFT AND ROCKETS, 1996, 33 (03) :416-421
[9]   Deployment test methods for a large deployable mesh reflector [J].
Tsunoda, H ;
Hariu, K ;
Kawakami, Y ;
Miyoshi, K ;
Nakagawa, J ;
Sugimoto, T .
JOURNAL OF SPACECRAFT AND ROCKETS, 1997, 34 (06) :811-816
[10]  
TSUNODA H, 1996, 47 INT ASTR C INT AS