121. Ergonomically designed check-out counter system for supermarket and merchandising industries

申请号: EP90300123.8

申请日: 1990-01-05

公开（公告）号: EP0396218A1

公开（公告）日: 1990-11-07

发明人: Vrooman, Carll DeWitt; Taylor, Dennis Ray

An ergonomically designed check-out counter system for supermarket and merchandising industries is characterised by provisions for differences in human heights, hand and position of operators and for ease in handling of merchandise to reduce fatigue and injury to the operators while providing maximum productivity under both light and heavy through put requirements. The check-out counter system includes one or more of the features of a housing defining the overall shape of the check-out counter system, a movable floor device (27) for receiving the cashier and for moving vertically up and down to position the cashier at a desired height regardless of the human height of the cashier, a movable chair device (40) positioned in the intermediate opening (24) for receiving the cashier and including adjustment devices (41,43) for moving the chair vertically and horizontally to desired positions thereby providing the cashier with the option of sitting or standing, a keyboard device (50) for entering price data of the merchandise which may be moved back and forth to accommodate right-handed and left-handed cashiers, and merchandise bagging devices (60,61,70,73) for easy handling and bagging of the merchandise after checking-­out by the cashier and providing for direct bagging by the cashier or bagging by a bagger.

122. 人工衛星用太陽光発電翼及び人工衛星

申请号: JP2015065659

申请日: 2015-03-27

公开（公告）号: JP2015189469A

公开（公告）日: 2015-11-02

发明人: クラウス・ジンメルマン; レネ・モイラー; トマス・フェッファーコーン; イェンス・ビルケル

【課題】簡明な手段により、輸送時にソーラーパネルが確実に支持されるようにした、人工衛星用太陽光発電翼を提供する。
【解決手段】少なくとも2枚の剛性ソーラーパネル14、16と少なくとも1枚の半剛性ソーラーパネル18、20とを含む複数枚のソーラーパネルを備え、それら複数枚のソーラーパネル14〜20が稼働時形態と輸送時形態とを取り得るように互いに連結されている人工衛星用太陽光発電翼10が記載されている。前記輸送時形態にあるときに前記複数枚のソーラーパネル14〜20が互いに重ね合わされた状態で保持されており、また、前記輸送時形態にあるときに前記半剛性ソーラーパネル18、20は自由振動可能な状態で2枚の前記剛性ソーラーパネル14、16の間に位置している。更に、少なくとも1つの人工衛星用太陽光発電翼10を備えた人工衛星が記載されている。
【選択図】図1

123. Attitude detection system for artificial satellite

申请号: US10189906

申请日: 2002-07-02

公开（公告）号: US06725133B2

公开（公告）日: 2004-04-20

发明人: Toshiaki Yamashita

An attitude detection system for an artificial satellite includes an interpolator for interpolating an angular-velocity signal to generate an interpolated angular-velocity signal, a sequential Kalman filter for generating a low-frequency attitude-angle signal, and an adder for adding the low-frequency attitude-angle signal and a high-frequency attitude-angle signal generated by a high-frequency angular sensor to generate a broad-band attitude-angle signal.

124. Attitude determination system for artificial satellite

申请号: US09610603

申请日: 2000-07-05

公开（公告）号: US06227496B1

公开（公告）日: 2001-05-08

发明人: Shoji Yoshikawa; Katsuhiko Yamada; Hiroshi Sakashita; Hiroo Yonechi

An attitude determination system for an artificial satellite capable of performing star identification without need for the aid of ground station includes an image processing module (17) for processing star images observed at predetermined time points by a star sensor (16) mounted on the artificial satellite (1) for arithmetically determining direction vectors of the observed stars, a rotation estimating module (18) for estimating a rotational motion of the artificial satellite (1) between an attitude of the artificial satellite at a predetermined time point and an attitude of the artificial satellite at another time point, an elongation estimating module (19) for estimating elongations between the direction vectors of plural stars the images of which are picked up at a same time point by the star sensor and estimating the elongations between the direction vectors of plural stars the images of which are picked up at different time points by the star sensor on the basis of the estimated rotational motion, a star identifying module (20) for establishing correspondences between a plurality of the stars for which relation of the elongation has been determined and stars on a star catalog for identifying the stars, and an attitude angle estimating module (21) for estimating an attitude angle of the artificial satellite on the basis of result of identification of the stars.

125. 利用人造衛星的信號收信方法、服務提供方法、人造衛星之控制方法、收信終端以及人造衛星控制裝置

申请号: TW092127841

申请日: 2003-10-07

公开（公告）号: TW200412050A

公开（公告）日: 2004-07-01

发明人: 岩田忠良; 前田利秀; 石田隆張; 井上秀樹

〔課題〕防止品質劣化，在服務區域之任何地區中，都能夠由適合於通訊、廣播之仰角的衛星接受服務之提供。〔解決手段〕通信、廣播系統1係透過由衛星管制局2所控制的人造衛星之環繞衛星3，在通信、廣播中心局4和位於波束波點5內之移動台6或固定台7之間，進行通信服務及／或廣播服務的通信、廣播系統。藉由在可保持高的衛星仰角之時間帶進行此環繞衛星的切換，以防止通訊、廣播的品質劣化。

126. 人工衛星の軌道面制御方法

申请号: PCT/JP2014/051228

申请日: 2014-01-22

公开（公告）号: WO2014115753A1

公开（公告）日: 2014-07-31

发明人: 小泉　宏之; 青山　順一

【課題】主衛星のミッションを損なうことなく、しかも人工衛星の小型化及び軽量化を図った上で高い推力レベルの推進装置を備えた人工衛星と実質的に同等な軌道制御を実現することが可能な人工衛星の軌道面制御方法を提供することを目的とする。 【解決手段】主衛星と共に打ち上げられる複数の小型の人工衛星１１，１２をそれぞれの目的軌道へ投入する人工衛星の軌道面制御方法であり、主衛星の目的軌道Ｓ１に投入された小型の人工衛星１１，１２を低い推力レベルの推進装置を用いて軌道高度を変更させ、当該軌道高度における地球重力場の扁平性に起因する軌道面の遷移を利用して複数の人工衛星１１，１２をそれぞれの目的軌道Ｓ５，Ｓ９へ投入することを特徴とするものである。

127. Composite material for artificial satellite, frame for artificial satellite, and panel for artificial satellite

申请号: JP2012226068

申请日: 2012-10-11

公开（公告）号: JP2014076750A

公开（公告）日: 2014-05-01

发明人: OKUYAMA KEIICHI; YAMAGUCHI KOJI; SATO RYOICHI

PROBLEM TO BE SOLVED: To provide a lightweight and inexpensive heat insulation material for an artificial satellite used for a small-sized or extremely small-sized artificial satellite showing a severe temperature gradient, and capable of controlling the temperature of a loaded apparatus within a required range.SOLUTION: This heat insulation material is used in a small-sized or extremely small-sized artificial satellite showing a severe temperature gradient. The heat insulation material is mainly composed of an aromatic polyimide in which an aromatic compound is directly bonded with an imide bond. The aromatic polyimide contains carbon fibers. The carbon fibers have a wire diameter of 7 μm and a length of 130 μm. The coefficient of thermal conductivity λ is changed according to the mixing ratio of the carbon fibers.

128. ERGONOMIC SEATING ASSEMBLIES AND METHODS

申请号: US14235847

申请日: 2012-08-03

公开（公告）号: US20140239686A1

公开（公告）日: 2014-08-28

发明人: Nicholas M. Christianson; Jean Francois Gomrée; Rodney C. Schoenfelder; Jeffrey Weber; Shawn Monitor

Seating assemblies and methods are disclosed. A seating assembly (100) can comprise a seat, a back support (114), and a frame component (110). The frame component can extend from a bottom portion (118), positioned near an underside of the seat, to a top portion (120), configured to maintain the back support at a position above the seat. The back support can laterally extend from a left edge portion (1670) to a right edge portion (1672) and can include a spring member (122) at or near each of the left and right edge portions. The spring member can include at least one undulation or arc (1674) providing integrated rated compression adaptation to a user. The seating assembly can further comprise a tilt mechanism (408), engaged with the frame component, including one or more leaf springs (424) and a spring contact assembly. The spring contact assembly (426) can be positioned on a top side of the one or more leaf springs.

129. 인공위성용 힌지 장치

申请号: KR1020080007065

申请日: 2008-01-23

公开（公告）号: KR100942172B1

公开（公告）日: 2010-02-12

发明人: 박희창; 김병인; 이성휘; 김진희; 김경원; 김선원; 김규선; 진익민; 이상률; 이주진

본 발명은 인공위성용 힌지 장치에 관한 것으로서, 더욱 상세하게는 우주공간의 극한환경(극 고온, 극저온현상)에서도 인공위성에서 태양전지판이 원활히 전개되고, 인공위성이 우주선에 실려 우주로 쏘아 올려질 때 발생되는 진동에도 잘 견디며, 상기 태양전지판의 완전 전개되어 우주공간에서 비행시, 발생되는 진동 및 충격 등에도 잘 견디는 특징이 있다. 이와 같이, 본 발명은 우주공간의 극한환경에서도 태양전지판이 전개되도록 인공위성과 태양전지판을 연결하거나 태양전지판과 태양전지판을 연결하는 힌지부에 있어서, 상기 인공위성 또는 태양전지판의 일단부에 결합부재에 의해 부착되는 제 1플레이트와; 상기 태양전지판의 일단부에 결합부재에 의해 부착되되, 상기 제 1플레이트와 끝단부가 축에 의해 결합되어 태양전지판을 전개시키는 제 2플레이트와; 상기 제 1플레이트와 제 2플레이트에 상호 연결되어 제 1플레이트와 제 2플레이트를 탄성적으로 전개되도록 형성된 인장 스프링을 포함하여 구성되는 것을 특징으로 하는 특징이 있다. 인공위성, 태양전지판, 힌지장치, 플레이트, 인장 스프링

130. SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL

申请号: EP16705226.5

申请日: 2016-01-22

公开（公告）号: EP3212503B1

公开（公告）日: 2017-11-22

发明人: WALKER, Andrew, Nicholas

131. PARTICLE BEAM TREATMENT SYSTEM, AND BEAM POSITION CORRECTION METHOD THEREFOR

申请号: EP12848652.9

申请日: 2012-09-21

公开（公告）号: EP2777766A1

公开（公告）日: 2014-09-17

发明人: HANAKAWA, Kazushi; SUGAHARA, Kengo; ODAWARA, Shuhei; HARADA, Hisashi; IKEDA, Masahiro; OTANI, Toshihiro; HONDA, Taizo; YOSHIDA, Katsuhisa

A particle beam treatment system includes an accelerator system (2) that accelerates a charged particle beam and a beam transport system (3) that transports a high-energy beam emitted from the accelerator to an irradiation location, wherein the beam transport system (3) is provided with at least one steering electromagnet (33) and at least one beam position monitor (34) corresponding to the at least one steering electromagnet (33), and wherein the at least one beam position monitor (34) supplies an excitation current for correcting a beam position, which periodically varies, to the at least one steering electromagnet (33).

132. Attitude determination system for artificial satellite

申请号: US919193

申请日: 1997-08-28

公开（公告）号: US6102338A

公开（公告）日: 2000-08-15

发明人: Shoji Yoshikawa; Katsuhiko Yamada; Hiroshi Sakashita; Hiroo Yonechi

An attitude determination system for an artificial satellite capable of performing star identification without need for the aid of ground station includes an image processing module (17) for processing star images observed at predetermined time points by a star sensor (16) mounted on the artificial satellite (1) for arithmetically determining direction vectors of the observed stars, a rotation estimating module (18) for estimating a rotational motion of the artificial satellite (1) between an attitude of the artificial satellite at a predetermined time point and an attitude of the artificial satellite at another time point, an elongation estimating module (19) for estimating elongations between the direction vectors of plural stars the images of which are picked up at a same time point by the star sensor and estimating the elongations between the direction vectors of plural stars the images of which are picked up at different time points by the star sensor on the basis of the estimated rotational motion, a star identifying module (20) for establishing correspondences between a plurality of the stars for which relation of the elongation has been determined and stars on a star catalog for identifying the stars, and an attitude angle estimating module (21) for estimating an attitude angle of the artificial satellite on the basis of result of identification of the stars.

133. Artificial satellite attitude control system

申请号: US606660

申请日: 1984-05-03

公开（公告）号: US4617634A

公开（公告）日: 1986-10-14

发明人: Kiichiro Izumida; Ritaroh Kasai

A system for controlling an attitude of an artificial satellite to decide the present attitude of the satellite on a spatial coordinate and angular velocities of rotation about body axes of the satellite, by the use of inertial sensors and star sensors, to calculate an objective attitude of the satellite on the basis of the present attitude information, the angular velocities of rotation about the body axes and orbit information received from a ground station so that the attitude of the satellite and the changing rate thereof are controlled simultaneously.

134. PROPULSION SYSTEM FOR SMALL ARTIFICIAL SATELLITES

申请号: PCT/EP2016/067680

申请日: 2016-07-25

公开（公告）号: WO2017021191A1

公开（公告）日: 2017-02-09

发明人: ROSSETTINI, Luca; ALBANO LOPES, Gonçalo Daniel

A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

135. METHOD AND APPARATUS FOR CHANGING ORBIT OF ARTIFICIAL SATELLITE

申请号: PCT/JP1989000819

申请日: 1989-08-11

公开（公告）号: WO1990001447A1

公开（公告）日: 1990-02-22

发明人: NIPPON TELEGRAPH AND TELEPHONE CORPORATION

The method and apparatus for changing the orbit of an artificial satellite in accordance with the present invention comprises causing an orbit changing device (1) to approach a target satellite (2) in a space, combining them, forming a dumb-bell like combination system, generating propelling force in the orbit changing device to generate simultaneously an orbit speed increment and rotation around the gravitational center to the gravitational center of the combination system so as to put the combination system onto a transition orbit (02), cutting off the combination system at a timing at which the axial direction of the combination system becomes perpendicular to the speed vector on the transition orbit, putting the target satellite on a final target orbit (03) and putting the orbit changing device thus cut off on an orbit different from that of the target satellite.

136. Attitude detection system for artificial satellite

申请号: US10189906

申请日: 2002-07-02

公开（公告）号: US20030004620A1

公开（公告）日: 2003-01-02

发明人: Toshiaki Yamashita

An attitude detection system for an artificial satellite includes an interpolator for interpolating an angular-velocity signal to generate an interpolated angular-velocity signal, a sequential Kalman filter for generating a low-frequency attitude-angle signal, and an adder for adding the low-frequency attitude-angle signal and a high-frequency attitude-angle signal generated by a high-frequency angular sensor to generate a broad-band attitude-angle signal.

137. 인공위성 중계기내 ＲＦ 송신장치

申请号: KR1019990047211

申请日: 1999-10-28

公开（公告）号: KR1020010039006A

公开（公告）日: 2001-05-15

发明人: 이무홍; 허원혁

PURPOSE: An RF transmitting apparatus in an artificial satellite repeater is provided to make a compact size of an RF transmitting apparatus by implementing a circuit by using a single temperature compensating variable amplifier, and reduce a production cost and shorten a production term as production processes are reduced by implementing the whole components in a single metal housing. CONSTITUTION: An attenuator(1000) receives a 10GHz extreme high frequency(EHF) signal from a front block, attenuates the amplitude of the signal to a proper level, and outputs it to a multiplier(2000). The multiplier(2000) receives the 10GHz EHF signal from the attenuator(1000), multiplies the frequency of the 10GHz EHF signal and outputs it to a band-pass filter(3000). The band-pass filter(3000) receives a 20GHz EHF signal from the multiplier(2000), filters it to pass only a desired frequency band of the 20GHz EHF signal and outputs it to a variable attenuator(4000). When an attenuation set level is determined according to a user's selection, the variable attenuator(4000) receives the 20GHz EHF signal from the band-pass filter(3000), attenuates the amplitude of the EHF signal corresponding to the attenuation set level, and outputs it to a three-step variable amplifier(6000). A temperature compensation driving circuit(5000) measures a temperature of an artificial satellite repeater, and outputs a corresponding temperature compensation control voltage to the three-step variable amplifier(6000). The three-step variable amplifier(6000) of which an amplification level is adjusted by the temperature compensation control voltage outputted from the temperature compensation driving circuit(5000), receives the 20GHz EHF signal from the variable attenuator(4000) and amplifies the amplitude of the 20GHz EHF signal to a proper level.

138. 人造衛星之整合與測試的方法及裝置

申请号: TW088120177

申请日: 1999-11-18

公开（公告）号: TW479146B

公开（公告）日: 2002-03-11

发明人: 喬瑟夫.安德森; 雷蒙.瑞肯

一種人造衛星整合與測試的系統及方法裝置其中一人造衛星(12)被組合和執行很多測試在一單一的試驗腔室(10)內，因此避免假如多重的測試腔室被使用所需的多重的安裝和分解操作，以及避免於測試腔室之間移動人造衛星的需求。