| Document |
Document Title |
|
WO/2024/084029A1 |
The invention relates to a method for destroying a satellite (10) comprising cycles (2000) of updating an onboard memory (11) when the satellite is in outer space (100). Each update cycle comprises receiving, by a communication device (1...
|
|
WO/2024/082001A1 |
An embodiment provides a protective suit system that is configured for protecting an occupant in extreme environments. The system may comprise a base layer to be worn on the occupant that is configured for thermal regulation of the occup...
|
|
WO/2024/079609A1 |
The invention provides a method for the space debris detection, and a system that implements the method, which provides an algorithm for estimating the performance of a network of optical sensors distributed globally in different ground ...
|
|
WO/2024/074743A1 |
The invention relates to a microthruster applicable to space engineering that comprises printed circuit boards (PCBs) connected to each other, wherein the first board comprises a fuel tank (1) and an outlet nozzle (2) and the second boar...
|
|
WO/2024/074862A1 |
A magnetic arrangement for a solid state propulsion system. The propulsion system includes a spiraling inward and upward cone shape permanent magnet made of magnetic material such as superconductors or neodymium magnets. The propulsion s...
|
|
WO/2023/137082A9 |
A satellite includes a structural element that is deformable during a collision with space object(s). The structural element includes a first side, a second side spaced apart from the first side to define an interior portion between the ...
|
|
WO/2024/073763A1 |
Carbon nanostructure-based composites and methods of making and using thereof are described. The carbon nanostructure-based composites may be single-layered or multi-tiered composites. Such composites can be useful for radiation shieldin...
|
|
WO/2024/068395A1 |
The invention relates to a rocket engine (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), wherein the first tank is filled with a fuel and the second tank with an oxidising agent, such as liquid hydrogen peroxi...
|
|
WO/2024/071577A1 |
The present invention relates to a lunar gravity simulation system for testing performance of a lander, characterized by comprising: a plurality of first frames extending in the height direction; a plurality of second frames extending in...
|
|
WO/2024/071410A1 |
Provided is a liquid storage container in which a device is disposed and with which high durability can be achieved.　This liquid storage container includes: a seamless cylindrical container body in which a storage chamber capable of st...
|
|
WO/2024/073514A1 |
Systems and methods described herein include collapsible and deployable structures that may be used as antenna, collectors, reflectors, or other large structures. The systems and methods may use modular designs so that larger structures ...
|
|
WO/2024/068255A1 |
A control system for apparatus to be operated on an aircraft or spacecraft, such as a satellite attitude determination and control system "ADCS", comprises a controller configured to implement one or more real time processes during norma...
|
|
WO/2024/060313A1 |
Disclosed in the present invention is an SMA-wire-driven reusable release mechanism with a self-resetting function. The present invention uses a two-stage load reduction and one-stage release structure. First-stage load reduction involve...
|
|
WO/2024/062185A1 |
The invention relates to a spacecraft stack comprising: a stack of spacecraft (1) made up of a plurality of stages which are placed one on top of the other and each comprise a number of vehicles greater than or equal to N; a lower adapte...
|
|
WO/2024/057287A1 |
A deployable boom mechanism, such as for a spacecraft, has a boom and a boom drum. The boom can be wound onto the boom drum. The boom drum is rotatable in a deployment direction to deploy the boom by unwinding it from the boom drum. A dr...
|
|
WO/2024/053047A1 |
The present invention comprises at least one processor that outputs information about a mission on a celestial body other than the Earth by executing the processing corresponding to the operation by a user in accordance with the operatio...
|
|
WO/2024/054197A1 |
The invention relates to space engineering and can be used in the creation of a suborbital rocket plane with substantially vertical takeoff and landing. A rocket plane comprises a body (1), movable front and rear aerodynamic control surf...
|
|
WO/2024/045778A1 |
Provided is a space debris collision avoidance method taking an orbit altitude adjustment task into consideration. The method comprises: when a spacecraft has a requirement for consecutive orbital transfer, acquiring a collision risk val...
|
|
WO/2024/049385A1 |
The present invention comprises a source (S) generating heat and/or radiation; a body (2) located on a space vehicle; at least one avionics chamber (A) on the body (2), in which the avionics equipment is provided; at least one panel (P) ...
|
|
WO/2024/049384A1 |
The present invention relates to a source (S) generating heat and/or radiation; a body (2) located on a space vehicle; at least one avionics chamber (A) on the body (2), in which the avionics equipment is provided; at least one panel (P)...
|
|
WO/2024/042287A1 |
The invention relates to a device for separating a second part (14) from a first part (12), comprising a first interface (16) intended to be attached to the first part and a second interface (18) intended to be attached to the second par...
|
|
WO/2024/038756A1 |
In a passive radar satellite 1, one or a plurality of radar openings 18 are attached to a satellite bus unit 14 by way of a radar opening drive device 17 having a variable attachment angle, wherein: in the radar openings 18, one or a plu...
|
|
WO/2024/038548A1 |
[Problem] To provide a spacecraft that has an improved heat discharging capability. [Solution] A spacecraft (1) according to one embodiment of the present invention comprises: a body (300) which has mounted therewithin multiple devices i...
|
|
WO/2024/035451A1 |
A method includes obtaining (402) thermal energy from a structure (112) to be cooled, where the structure includes micro-channels (208). The method also includes providing (402) the thermal energy to a water-based polymer network (206), ...
|
|
WO/2024/033532A1 |
This disclosure relates to a carrier device (100) for securing a payload in spacecraft, having a carrier surface (102), the carrier surface (102) being provided with an arrangement of local resonators (108), which each comprise at least ...
|
|
WO/2024/033273A1 |
According to one aspect, the present disclosure relates to a device for reducing the electric charge of a space vehicle, the device comprising: a substrate (201) made of a conductor or semiconductor which is configured to be electrically...
|
|
WO/2024/028817A1 |
A system for generating magnetic fields in one or more axis, the system system comprising a primary electromagnet comprising a first coil having a first axis a first secondary electromagnet comprising a second coil having a second axis, ...
|
|
WO/2024/023409A1 |
The invention relates to a power supply assembly (1) for a plasma thruster (2) of a spacecraft (100) for controlling a keeper current (Ikeeper) supplied to a keeper electrode (22) of the plasma thruster. The power supply assembly takes i...
|
|
WO/2024/021399A1 |
The present invention provides an all-electric propulsion satellite orbit transfer method based on autonomous task planning, comprising: step S1, a ground telemetry, tracking, and control system formulates an orbit transfer strategy, and...
|
|
WO/2024/022208A1 |
Disclosed in the present invention is a large-area flexible solar cell wing capable of unfolding in two steps. The solar cell wing comprises a lifting mechanism, an extension mechanism, flexible solar cell arrays capable of unfolding in ...
|
|
WO/2024/023971A1 |
The core part of this invention is in introducing the third body (bodies) launched from the servicing spacecraft. The third body, which can be an unsophisticated and disposable device, should be equipped with the double capabilities of d...
|
|
WO/2024/023410A1 |
The invention relates to an annular enclosure (10) for an intermediate stage of a multi-stage aerospace launcher, the annular enclosure (10) comprising at least two segments (12) together forming a ring defining an axial direction (DA), ...
|
|
WO/2024/019721A1 |
The invention includes engines adapted for using apparatuses and methods for instantiating chemical reactants in a nanoporous carbon powder, and further includes uses for such engines and vehicles incorporating such engines. The inventio...
|
|
WO/2024/018092A1 |
Bolt release system for spacecraft and launcher separation systems, that comprises: a release device (1); a bolt (2) connected to the release device (1) and protruding therefrom; a first retaining means (3), with at least one end surface...
|
|
WO/2024/019806A1 |
In some implementations, a device may obtain historical orbital data indicative of orbital movement of a set of satellites over a period of time, the set of satellites comprising at least a subset of satellites of the satellite constella...
|
|
WO/2024/017850A1 |
A satellite radar antenna array is formed as a generally planar structure comprising a plurality of panels. Each panel comprises a plurality of antenna transmit/receive modules; each antenna transmit/receive module comprises a stack of p...
|
|
WO/2024/016045A1 |
Disclosed herein is a method for remote monitoring, comprising determining, from event signals obtained from an event-based vision sensor, a rate of those event signals generated in response to changes associated with a specific object a...
|
|
WO/2024/013460A1 |
A reusable orbital vehicle (14) for a space transport system (10) comprises a fuselage (22) the shape of which widens in a direction extending from the front end (24) of the reusable orbital vehicle to a rear end (26) of said fuselage (2...
|
|
WO/2024/015975A2 |
Methods and systems are provided to enable a virtual FlatSat and distributed node architecture. The virtual platform may be or include a SaaS platform that enables multiple users to access computing nodes. The computing nodes may enable ...
|
|
WO/2024/015232A1 |
Implementations of the disclosed subject matter provides a system having an artificial light source disposed at a distance from earth or other celestial body, where the artificial light source is configured to project one or more beams o...
|
|
WO/2024/013698A1 |
A stage of a rocket is disclosed. The rocket stage may include: a body, and a plurality of foldable propulsion units spaced around a circumference of the body, where each propulsion unit comprises: a folding beam; at least one motor moun...
|
|
WO/2024/015326A1 |
The current disclosure provides systems and methods of directly measuring angular velocity and angular acceleration of space objects and using the measured angular velocity and angular acceleration as inputs into new and unique algorithm...
|
|
WO/2024/015450A2 |
A self-contained identification tag arranged to be attachable to a resident space object (RSO) comprising: a processor; an antenna, an energy gatherer arranged to gather energy from the environment; and an energy store arranged to receiv...
|
|
WO/2024/013570A1 |
There is described a spacecraft docking system (D) for and method of capturing and coupling a target spacecraft (T) to a servicing spacecraft (S) provided with the spacecraft docking system (D), the target spacecraft (T) having a propuls...
|
|
WO/2024/014460A1 |
There is provided a technique for achieving inter-satellite optical communication for a satellite having a limited calculation capability. One aspect of the present disclosure relates to an earth station, including: a data acquisition un...
|
|
WO/2024/009293A1 |
Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled wi...
|
|
WO/2024/002772A1 |
A system (1) for thermal regulation of a spacecraft (S), comprising: - a hot source (C) interface, - a radiator (10) having a thermally conductive body (11) comprising at least one radiative surface (12), - two separate single-phase cool...
|
|
WO/2024/006680A1 |
A modular satellite apparatus (10) for testing materials in a space setting is provided. The apparatus (10) includes a lower member (101) and an upper member (102), as well as rear support members (103), medial support members (104), fro...
|
|
WO/2024/006087A1 |
A pulsar-based timing and lateration system includes a detector system. In according with certain embodiments, the detector system includes a plurality of detectors, each one configured for detecting X-ray photons and generating output s...
|
|
WO/2024/004355A1 |
This heat control structure comprises: a plurality of sheet-like or plate-like graphite members; a first holding member that holds the plurality of graphite members at a first end portion in the longitudinal direction of the plurality of...
|
