摘要:
A deployable antenna which has a larger aperture diameter by four-side links provided in at least three stages and which includes: six deployment link mechanisms (20) arranged radially from a central shaft so as to support an outer edge portion of a flexible reflector mirror surface; and one deployment driving mechanism (30) arranged at a lower portion of a center of arrangement of the six deployment link mechanisms, for unfolding the six deployment link mechanisms. Each of the six deployment link mechanisms includes a first four-side link (5), a second four-side link (6), and a third four-side link (7) arranged in an order from a position of the central shaft, around which the six deployment link mechanisms are arranged, toward an outer side of the each of the six deployment link mechanisms so that the each of the six deployment link mechanisms is structured to be foldable in three stages.
摘要:
An image pickup apparatus is provided with: an optical system including a lens or a reflecting mirror; an image pickup device having a light-receiving surface on which light rays from the optical system are focused and a plurality of light-receiving pixels which generate charges on the light-receiving surface by the light rays; a bias voltage generation unit which supplies power to the image pickup device; a signal processing unit which processes a signal output from the image pickup device and outputs the processed signal as image data; and a control unit which inputs into the image pickup device a driving clock that controls transmission of the charges generate in the light-receiving pixels of the image pickup device. The image pickup device is bent so that distortion aberration present in the optical system is eliminated.
摘要:
A connector (10) includes a plurality of contacts (13). The connector includes an insulator (11) having a plurality of through-holes (12) for receiving the contacts. A pair of contacts (13, 13') are disposed in each of the through-holes. Since two contacts (13) are disposed in the through-hole (12) in the insulator (11), even if a fault occurs in one of the contacts (13), signal transmission in the same line can continuously be used. Moreover, since large areas of contact portions (14) of the contacts are secured even in normal use, the capacity of electric current is increased.
摘要:
In a data/strobe encoding scheme circuit in which data and a strobe signal are transmitted through different lines, changes respectively in the data and the strobe signal are employed as clock signals for a latching operation, and the data is transmitted to a succeeding-stage circuit operating on a second clock signal. The circuit latches predetermined data by an FF circuit and passes a data pair including a signal indicating that the data has been latched and held therein as well as the latched data to the succeeding-stage circuit, activates, if assertion of a signal indicating reception of the data is received from the succeeding-stage circuit, again the FF circuit which has latched the data and has entered a stop state, and receives new data. There is provided a data/strobe encoding scheme circuit and a data/strobe encoding method, it is possible to implement a data/strobe encoding scheme circuit and a data/strobe encoding method capable of realizing a low-cost data/strobe encoding scheme which is independent of LSI device characteristics and which can be easily designed.
摘要:
A communication terminal which communicates with a communication device includes a position detecting section which detects a current position of the communication terminal, and a control section which automatically notifies the communication device of the current position obtained from the position detecting section, in response to an instruction from the communication device.
摘要:
Disclosed is a method for injecting a plurality of spacecrafts into different circum-earth or interplanetary orbits individually in a single launch. A plurality of spacecrafts coupled to an assist module are injected into an interplanetary orbit having a periodicity synchronous with the earth's revolution period. Then, in a maneuver for allowing the assist module to re-counter with and pass near to the earth (Earth swing-by), the assist module appropriately performs an orbital change maneuver and a separation maneuver for each of the spacecrafts in a sequential order. Through these maneuvers, a closest-approach point to the earth is changed for each of the spacecrafts so as to drastically change a subsequent orbital element for each of the spacecrafts. The assist module takes a sufficient time to determine a target orbit for each of the spacecrafts with a high degree of accuracy until a half month to several days before a closest-approach time in the Earth swing-by. Based on the determined orbit, the assist module makes an orbit correction of about several m/sec in a sequential order, and then separates the spacecrafts therefrom in a sequential order. In this process, an inertia navigation is performed based on an accelerometer mounted in the assist module and information about attitude.