A thruster assembly, including a switch connected to a power source, a thruster, a propellant tank for storing and pressurising a propellant, and a propellant channel for guiding the propellant to the thruster. The thruster includes a space for receiving the propellant from the propellant channel, an electrically controlled heating element, a thruster body having a first thermal expansion coefficient, a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body, and a nozzle, wherein the valve component includes a sealing surface closing the nozzle in a first temperature, and the electrically controlled heating element in response to actuation of the switch heats said thruster to a second temperature where the thermal expansion of the thruster opens the nozzle.

To achieve an objective to enable a plurality of management business operators managing space objects flying in space, to share and carry out danger analysis efficiently. In a space traffic management system (500), a plurality of space traffic management devices (100) are connected to each other via a communication line. Each of the plurality of space traffic management devices includes a space information recorder (101), a danger alarm device (102), a danger analysis device (103), a danger avoidance action assist device (104), and a security device (105). The space information recorder includes a space object ID, orbital information, and public condition information; and a business device ID and public condition information. The plurality of space traffic management devices (100) have data format compatibility and share the space object ID and the business device ID, and share orbital information corresponding to the space object ID among business devices that comply with the public condition information.

A high efficiency satellite transmitter comprises an RF amplifier chip in thermal contact with a radiant cooling element via a heat conducting element. The RF amplifier chip comprises an active layer disposed on a high thermal conductivity substrate having a thermal conductivity greater than about 1000 W/mK, maximizing heat conduction out of the RF amplifier chip and ultimately into outer space when the chip is operating within a satellite under normal transmission conditions. In one embodiment, the active layer comprises materials selected from the group consisting of GaN, InGaN, AlGaN, and InGaAlN alloys. In one embodiment, the high thermal conductivity substrate comprises synthetic diamond.

A high efficiency satellite transmitter comprises an RF amplifier chip in thermal contact with a radiant cooling element via a heat conducting element. The RF amplifier chip comprises an active layer disposed on a high thermal conductivity substrate having a thermal conductivity greater than about 1000 W/mK, maximizing heat conduction out of the RF amplifier chip and ultimately into outer space when the chip is operating within a satellite under normal transmission conditions. In one embodiment, the active layer comprises materials selected from the group consisting of GaN, InGaN, AlGaN, and InGaAlN alloys. In one embodiment, the high thermal conductivity substrate comprises synthetic diamond.

A transfer system for supplying a receiving tank of a receiving spacecraft with a supply gas from a supply spacecraft. A transfer tank is disposed on the supply spacecraft and configured to retain a supply gas. A transfer line is coupled to the transfer tank, and one end thereof may be coupled to the receiving tank. A transfer valve is operatively coupled to the transfer line. A heating system is thermally coupled to the transfer tank. A control system is operatively coupled to the transfer valve and the heating system. The control system is operable to cause a transfer quantity of the supply gas to be heated, and to open the transfer valve, such that a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes the transfer quantity of the supply gas to flow to the receiving tank.

The present invention discloses a partition satellite mission planning method for earliest completion of regional target coverage, which includes the following steps: 1. partitioning a to-be-observed rectangular region; 2. allocating observation resources to different regions and selecting certain coverage opportunities and coverage modes thereof to minimize completion time corresponding to a formed coverage solution. The present invention can obtain a satisfactory solution capable of finishing complete coverage of regional targets as early as possible with sufficient observation resources through suitable calculation resources and achieve balance between the consumption of calculation resources and optimality of solutions, so that satellite resources can be fully used to conduct the quick and effective coverage search for important regional targets in a real environment.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.

A solar power generator includes a support, a plurality of first electrodes disposed on one side of the support, a solar cell module mounted to the support, and a plurality of second electrodes disposed on the opposite side of the support. The solar cell module is electrically connected to a pair of the first electrodes via a transmission line for module connection. Three pairs of the second electrodes are electrically connected one-to-one to three pairs of the first electrodes via a transmission line for passage of current. Three of the second electrodes are electrically connected to one of the first electrode via the transmission line for passage of current.

A solar power generator includes a support, a plurality of first electrodes disposed on one side of the support, a solar cell module mounted to the support, and a plurality of second electrodes disposed on the opposite side of the support. The solar cell module is electrically connected to a pair of the first electrodes via a transmission line for module connection. Three pairs of the second electrodes are electrically connected one-to-one to three pairs of the first electrodes via a transmission line for passage of current. Three of the second electrodes are electrically connected to one of the first electrode via the transmission line for passage of current.