KR970042094A - Alignment structure with satellite reaction wheel - Google Patents

Alignment structure with satellite reaction wheel Download PDF

Info

Publication number
KR970042094A
KR970042094A KR1019950061524A KR19950061524A KR970042094A KR 970042094 A KR970042094 A KR 970042094A KR 1019950061524 A KR1019950061524 A KR 1019950061524A KR 19950061524 A KR19950061524 A KR 19950061524A KR 970042094 A KR970042094 A KR 970042094A
Authority
KR
South Korea
Prior art keywords
reaction wheel
satellite
alignment structure
present
improve
Prior art date
Application number
KR1019950061524A
Other languages
Korean (ko)
Inventor
정도희
Original Assignee
석진철
대우중공업 주식회사
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 석진철, 대우중공업 주식회사 filed Critical 석진철
Priority to KR1019950061524A priority Critical patent/KR970042094A/en
Publication of KR970042094A publication Critical patent/KR970042094A/en

Links

Landscapes

  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

본 발명은 인공위성의 리엑션 휠(REACTION WHEEL)의 장착 정렬 구조에 관한 것으로, 보다 상세하게는 인공위성에 장착되는 리엑션 휠의 장착 정렬 구조를 피라미드 형태로 구성함으로서, 인공위성의 무게를 절감시켜 인공위성의 성능을 향상시킬 수 있고, 자세제어의 아정도 제고를 만족시키며 비용절감을 실현할 수 있도록 한 인공위성의 리엑션 휠 장착 정렬 구조에 관한 것으로, 피라미드 형태의 각 빗면(1~4) 소정의 위치에 각 리엑션 휠(20)을 장착하되, 상기 리엑션 휠(20)은 3축 제어에 의해 제어되도록 구성된다. 이와 같이 구성된 본 발명은 인공위성의 부피를 줄일 수 있고, 무게를 경감시킬 수 있으며, 기술을 축적시킬 수 있고, 고신뢰도 정밀 제어기술 및 모멘텀사이징(Sizing)등의 기술의 파급효과에 기여할 수 있는 특징이 있다.The present invention relates to a mounting alignment structure of a satellite reaction wheel (REACTION WHEEL), and more particularly, by configuring the mounting alignment structure of the reaction wheel mounted on the satellite in the form of a pyramid, by reducing the weight of the satellite to improve the performance of the satellite The present invention relates to an alignment structure with a reaction wheel mounted on a satellite, which can improve the performance, satisfactorily improve posture control, and realize cost reduction. Each reaction wheel (1-4) in the pyramid shape has a reaction wheel ( 20), the reaction wheel 20 is configured to be controlled by three-axis control. The present invention configured as described above can reduce the volume of satellites, reduce weight, accumulate technology, and contribute to the ripple effect of technologies such as high reliability precision control technology and momentum sizing There is this.

Description

인공위성의 리엑션 휠(REACTION WHEEL) 장착 정렬 구조Alignment structure with satellite reaction wheel

본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음Since this is an open matter, no full text was included.

제1도는 종래의 리엑션 휠이 인공위성에 장착되는 구조를 도시한 개략 구성도.1 is a schematic configuration diagram showing a structure in which a conventional reaction wheel is mounted on a satellite.

제2도는 본 발명에 의한 리엑션 휠이 인공위성에 장착되는 구조를 도시한 개략 구성도.2 is a schematic diagram showing a structure in which a reaction wheel according to the present invention is mounted on a satellite.

Claims (1)

피라미드 형태의 각 빗면(1~4) 소정의 위치에 각 리엑션 휠(20)을 장착하되, 상기 리엑션 휠(20)은 3축제어에 의해 제어되도록 구성됨을 특징으로 하는 인공위성의 리엑션 휠 장착 정렬 구조.Reaction wheel mounting arrangement structure of a satellite, characterized in that each reaction wheel 20 is mounted to a predetermined position on each of the pyramid-shaped oblique surface (1-4), the reaction wheel 20 is configured to be controlled by three-axis control .
KR1019950061524A 1995-12-28 1995-12-28 Alignment structure with satellite reaction wheel KR970042094A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1019950061524A KR970042094A (en) 1995-12-28 1995-12-28 Alignment structure with satellite reaction wheel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1019950061524A KR970042094A (en) 1995-12-28 1995-12-28 Alignment structure with satellite reaction wheel

Publications (1)

Publication Number Publication Date
KR970042094A true KR970042094A (en) 1997-07-24

Family

ID=66621477

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1019950061524A KR970042094A (en) 1995-12-28 1995-12-28 Alignment structure with satellite reaction wheel

Country Status (1)

Country Link
KR (1) KR970042094A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100467507B1 (en) * 2002-09-27 2005-01-24 한국항공우주연구원 Momentum Management Method for Pyramid Type Reaction Wheel on Geostationary Satellite

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100467507B1 (en) * 2002-09-27 2005-01-24 한국항공우주연구원 Momentum Management Method for Pyramid Type Reaction Wheel on Geostationary Satellite

Similar Documents

Publication Publication Date Title
CA2042038A1 (en) Fluidless multi-directional motion-damping mount
ATE356946T1 (en) ENERGY ABSORBER
CA2180321A1 (en) Mount for panel-shaped components
FR2710314B1 (en) 3-axis stabilized satellite with geocentric pointing in low orbit with orientable 1-axis solar generator.
AU2001230335A1 (en) Flight control system for an aircraft
GR940100381A (en) Multidirectional mechanical device dissipating energy, particularly for the constraint of structures in seismic zones.
IT9067051A1 (en) SYSTEM FOR ASSEMBLING BY WELDING PRINTED SHEET STRUCTURES, IN PARTICULAR SMALL SUB-GROUPS OF THE BODYWORK OR MECHANICAL PART OF VEHICLES.
CA2285495A1 (en) Sump stabilizer bar
WO2000012269A3 (en) Moment control unit for spacecraft attitude control
KR970042094A (en) Alignment structure with satellite reaction wheel
US3311322A (en) Servomechanisms responsive to a heat source
WO2003085257A3 (en) Satellite energy and attitude control system
KR880012382A (en) Rear suspension structure of car
Agrawal Attitude control of flexible spacecraft
Guerman Magnetic hysteresis damper for a satellite in an elliptic orbit
Nakamura et al. Control of under-actuated link structure in space
Agrawal et al. Experimental simulation of attitude control of flexible spacecraft
Sarychev Dynamics of a satellite with a passive aerodynamic orientation system
GR3022179T3 (en) Outside mirror for a vehicle.
KR970045536A (en) Mounting structure of the compressor cap
Modi et al. Dynamics and control of the Shuttle based SCOLE type large antenna system
JPS56114259A (en) Structural body of supporting shadow mask
Qi et al. A study of compound control in the case of the tracking and pointing system of a flexible antenna on a satellite
Sehnal et al. Aerodynamic torques affecting the attitude of a satellite moving in low Earth orbit
UEBA The solar pressure torque and the design of the attitude control system of the communication satellite with large antenna reflectors

Legal Events

Date Code Title Description
N231 Notification of change of applicant
A201 Request for examination
N231 Notification of change of applicant
E902 Notification of reason for refusal
E601 Decision to refuse application