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1. 发明申请

WO2022251762A2 A NON-AXISYMMETRIC HEAT SHIELD, A NOZZLE DEFINED AT LEAST PARTIALLY BY THE HEAT SHIELD, AN ENGINE INCLUDING THE NOZZLE, AND A VEHICLE INCLUDING THE ENGINE 审中-公开
公开(公告)号：WO2022251762A2
公开(公告)日：2022-12-01
申请号：PCT/US2022/071686
申请日：2022-04-13
申请人： STOKE SPACE TECHNOLOGIES, INC.
发明人： MCCULLOUGH, Thomas, Ryan , FELDMAN, Thomas
IPC分类号： B64G1/58 , B64G1/40 , B64G1/62 , F02K1/78
摘要： A heat shield for protecting a windward side of a vehicle from a high enthalpy flow is disclosed. The heat shield includes a centerbody sidewall and a centerbody base extending aft of the centerbody sidewall. The centerbody sidewall and the centerbody base define a heat shield outer surface that is non-axisym metric. Also disclosed is an aerospike nozzle defined at least partially by the heat shield, an engine including a high pressure chamber and the aerospike nozzle, and a vehicle including the engine.

2. 发明申请

WO2021257002A1 SPACECRAFT POWERED BY ELECTROMAGNETIC WAVES WITH PRIMARY AND SECONDARY TUNNEL FOR ACCELERATING IN THE VACUUM AND GENERATING ELECTRICITY TO PROPEL THE CRAFT 审中-公开
公开(公告)号：WO2021257002A1
公开(公告)日：2021-12-23
申请号：PCT/SI2021/000006
申请日：2021-06-09
申请人： ENERGETIK, SILVANO BIZJAK S.P.
发明人： BIZJAK, Silvano
IPC分类号： B64G1/12 , B64G1/40 , B64G1/42 , B64G1/44 , B64G1/54 , B64G1/60 , B64G1/62 , B64G1/409 , B64G1/421 , B64G1/425 , B64G1/443 , B64G1/543
摘要： The subject-matter of invention is a spacecraft powered by electromagnetic waves with a primary and secondary tunnel for acceleration in the interplanetary, interstellar and intergalactic space and generation of electricity to power the craft. Its advantages are: it is environmentally-friendly, suitable for long-range flights, almost inaudible, and it generates electricity from its own electromagnetic waves. At the launch, it consumes less energy than current spacecrafts. The crew is protected from cosmic radiation. In the space, the Element (A) accommodating the crew and Element (B) are rotating in opposite directions, which enables gravitation in the living space of Element (A) generated by constant rotating, thereby creating centrifugal force that keeps the crew with feet on the floor in their rooms. The craft needs small-size hydrogen-powered electricity generators (BI11) to charge the batteries (BII4) in case of general failure. Optionally, wings of any form, bearing additional solar cells (BI10), may be incorporated in the spacecraft. The modular design of the craft enables that it can be easily disassembled to facilitate maintenance.

3. 发明申请

WO2020094640A1 RETURN TO BASE SPACE LAUNCH VEHICLES, SYSTEMS AND METHODS 审中-公开
公开(公告)号：WO2020094640A1
公开(公告)日：2020-05-14
申请号：PCT/EP2019/080235
申请日：2019-11-05
申请人： PANGEA AEROSPACE, S.L.
发明人： ARGEMI SAMSO, Adria , BERGSTROM, Rasmus , ROSSI, Federico , PALUMBO, Nicola
IPC分类号： B64G1/00 , B64G1/40 , B64G1/42 , B64G1/62
摘要： A stage for a space launch vehicle is provided. The space launch vehicle has a main body including a first end and a second end, and defines a central longitudinal axis between the first end and the second end. The stage comprises a stage rocket engine arranged at or near the first end of the stage to propel the launch vehicle vertically upwards at take-off. The stage furthermore comprises a plurality of fans for providing lift during a landing procedure of the stage, wherein the fans have a rotational axis arranged substantially perpendicular to the central longitudinal axis. Also provided are space launch vehicles and methods for transporting a payload into space.

4. 发明申请

WO2019210286A1 FURLABLE SAIL DEVICES, SYSTEMS, AND METHODS 审中-公开
公开(公告)号：WO2019210286A1
公开(公告)日：2019-10-31
申请号：PCT/US2019/029537
申请日：2019-04-27
申请人： ROCCOR, LLC
发明人： TURSE, Dana , DAVIS, Bruce , FRANCIS, William , TOMCHEK, Andrew , ADAMS, Larry , MEDINA, Kamron
IPC分类号： B64G1/62
摘要： Furlable sail devices, systems, and methods are provided in accordance with various embodiments. For example, some embodiments include a system and/or device that may include: a furlable boom; a furlable sail coupled with a distal end of the furlable boom; and/or a shear take-up mechanism coupled with a root end of the furlable sail. In some embodiments, the shear take-up mechanism applies tension to the furlable sail. The shear-take up mechanism may include one or more springs coupled with the root end of the furlable sail. In some embodiments, the furlable sheet includes a structural sheet. The structural sheet may include one or more areas with bending stiffness. The structural sheet may be fabricated to be self-supporting. In some embodiments, the furlable boom includes a slit-tube boom. Some embodiments may be configured as deorbit sails.

5. 发明申请

WO2018226287A1 SPACECRAFT LANDING AND SITE-TO-SITE TRANSPORT FOR A PLANET, MOON OR OTHER SPACE BODY 审中-公开
公开(公告)号：WO2018226287A1
公开(公告)日：2018-12-13
申请号：PCT/US2018/023284
申请日：2018-03-20
申请人： DREXLER, Jerome
发明人： DREXLER, Jerome
IPC分类号： B64G1/10 , B64G1/24 , B64G1/40 , B64G1/42 , B64G1/62
摘要： A method, operable in the presence of ambient cosmic rays, is provided for braking a craft upon approach to a planet, moon or other space body, e.g. in preparation for landing. Deuterium-containing particle fuel material is projected in a specified direction outward of the craft, which interacts with both the cosmic rays and their principal decay product muons to generate energetic micro-fusion products that produce a braking thrust on the craft for a specified trajectory. The micro-fusion products may push directly against the craft, e.g. upon a pressure plate, or upon a sail or parachute connected to the craft, to decelerate the craft. A prepositioned automated landing system at a landing site may project the fuel material toward the craft based on telemetry tracking of an incoming craft and likewise directly disperse the material cloud to form a braking cushion at the landing site. The micro-fusion landing system may be part of a site-to-site transport, where the craft was launched using either conventional chemical rockets or micro-fusion for accelerating thrust.

6. 发明申请

WO2014021744A3 METHOD AND DEVICE FOR LAUNCHING RING-SHAPED AND GRID-LIKE SURFACES INTO OUTER SPACE 审中-公开
标题翻译：用于将环形和网状表面开放到外部空间的方法和装置
公开(公告)号：WO2014021744A3
公开(公告)日：2014-06-19
申请号：PCT/RU2013000661
申请日：2013-07-31
申请人： ALEKSANDROV OLEG ALEKSANDROVICH
发明人： ALEKSANDROV OLEG ALEKSANDROVICH
IPC分类号： B64G1/16 , B64G1/40 , B64G1/62
CPC分类号： B64G9/00
摘要： The group of inventions relates to methods and means for launching useful payloads into orbit from the surface of a planet. The useful payload to be launched can be annular, flat, convex or concave in shape or have a grid-like (trussed) surface. Such a payload is placed horizontally on rocket stages having fuel tanks and rocket engines. The rocket stages conform with the outline of the useful payload in horizontal projection and include elements similar to the load-bearing elements of the useful payload. Individual component load-bearing elements of the rocket stages and of the useful payload are given an aerodynamic shape or are provided with fairings. In a tandem system, the outline rocket stages are arranged in the form of layers having the breadth of the outline projection and a thickness that corresponds to the volume of the fuel tank of a rocket stage. Large numbers of low-thrust rocket engines are arranged around the outline of the payload to be launched, taking into account the concentration of masses at various points of the useful payload. During the return of the useful payload and the rocket stages in the atmosphere, the effects of grid-like or annular wings are utilized. This enables the launch of non-standard useful payloads into space without the need for modular assembly or deployment in orbit or for a process of folding on Earth, thus reducing labour costs and the cost of launching and creating space facilities in outer space.
摘要翻译：发明的一组涉及从地球表面发射有用的有效载荷到轨道的方法和装置。待发射的有用载荷可以是环形，平坦，凸形或凹入的形状或具有格子状（桁架）表面。这样的有效载荷水平放置在具有燃料箱和火箭发动机的火箭级上。火箭级符合水平投影中有用有效载荷的轮廓，并包括与有用载荷的承载元件相似的元件。火箭级和有用有效载荷的单个部件承载元件具有空气动力学形状或提供整流罩。在串联系统中，轮廓火箭级以具有轮廓突起的宽度的层的形式布置，并且其厚度对应于火箭级的燃料箱的体积。考虑到有用载荷的各个点的质量集中，大量的低推力火箭发动机围绕要发射的有效载荷的轮廓布置。在有用的有效载荷和大气中的火箭级的返回期间，利用网格状或环形翼的效果。这使得能够将非标准有用的有用载荷发射到空间中，而不需要在轨道上进行模块化组装或部署，或者在地球上进行折叠过程，从而降低劳动力成本以及在外层空间中发射和创建空间设施的成本。

7. 发明申请

WO2013015840A1 CAPSULE SYSTEM, SERVICE MODULE, AND REUSEABLE REENTRY PAYLOAD AND DOCKING MODULE 审中-公开
标题翻译：胶囊系统，服务模块和可重复的反射装载和锁定模块
公开(公告)号：WO2013015840A1
公开(公告)日：2013-01-31
申请号：PCT/US2012/022799
申请日：2012-01-26
申请人： EXCALIBUR ALMAZ USA, INC. , ZELON, Jon
发明人： ZELON, Jon
IPC分类号： B64G1/12 , B64G1/64 , B64G1/62
CPC分类号： B64G1/14 , B64G1/60 , B64G1/62 , B64G1/646 , B64G2001/1092
摘要： A modular spacecraft comprising: a capsule module comprising a common bulkhead, and an additional spacecraft module comprising a common bulkhead, wherein said capsule module's common bulkhead is attached to said additional spacecraft module's common bulkhead.
摘要翻译：一种模块化航天器，包括：胶囊模块，包括一个公共舱壁，以及一个附加的航天器模块，包括一个公共舱壁，其中所述胶囊模块的通用舱壁连接到所述附加的航天器模块的公共舱壁上。

8. 发明申请

WO2022199886A1 ATMOSPHÄRENWIEDEREINTRITTS- UND LANDEVORRICHTUNG FÜR EINE RAKETENSTUFE UND VERFAHREN FÜR DEN WIEDEREINTRITT EINER RAKETENSTUFE IN DIE ATMOSPHÄRE 审中-公开
公开(公告)号：WO2022199886A1
公开(公告)日：2022-09-29
申请号：PCT/EP2022/025099
申请日：2022-03-11
申请人： KLAUS, Sebastian
发明人： KLAUS, Sebastian
IPC分类号： B64G1/00 , B64G1/62 , B64G5/00
摘要： Die Erfindung offenbart eine Atmosphärenwiedereintritts- und Landevorrichtung (1) für eine Raketenstufe (2) zum sicheren Wiedereintritt einer Raketenstufe (2) in die Atmosphäre und zur sicheren Wasserung einer Raketenstufe (2) und ein entsprechendes Verfahren. Die Vorrichtung weist einen Bailute (3) auf, der konfiguriert ist, um in einem ersten Zustand gefaltet und in einem zweiten Zustand entfaltet vorzuliegen, wobei der Bailute (3) in dem gefalteten Zustand so an einer Raketenstufe (2) anordbar ist, dass die Aerodynamik der Raketenstufe durch den Bailute (3) nicht beeinträchtigt ist, und wobei der Bailute in entfaltetem Zustand die Raketenstufe (2) im Wesentlichen umhüllt. Die Vorrichtung umfasst des Weiteren einen Umhüllungsmechanismus, der eingerichtet ist, eine Umhüllung der Raketenstufe mit dem Bailute durchzuführen sowie einen Befüllungsmechanismus, der eingerichtet ist, den Bailute in entfaltetem Zustand bei einem Wiedereintritt in die Atmosphäre mit Luft aus einer Grenzschicht zu befüllen, die zwischen dem vor der Oberfläche der Vorrichtung beim Wiedereintritt gebildeten Plasma und der Oberfläche der Vorrichtung entsteht. Des Weiteren ist eine Steuerung vorgesehen, die eingerichtet ist, den Umhüllungsmechanismus und den Befüllungsmechanismus zu steuern.

9. 发明申请

WO2021166876A1 人工衛星、推薬管理方法、地上設備、および、管理事業装置审中-公开
公开(公告)号：WO2021166876A1
公开(公告)日：2021-08-26
申请号：PCT/JP2021/005619
申请日：2021-02-16
申请人：三菱電機株式会社
发明人：迎　久幸
IPC分类号： B64G1/26 , B64G1/62
摘要：メガコンステレーションを構成する衛星が、ミッションを終了した後に、宇宙空間に大量に滞留することを防ぐことを目的とする。人工衛星は、推進装置を具備する。人工衛星は、推進装置に用いられる推薬であって、人工衛星が衛星設計寿命である第１期間Ｌ１年の軌道上運用後に、軌道離脱してから第１期間Ｌ１年未満の期間で大気圏突入するために必要な量の推薬を保有する。地上設備は、人工衛星が、衛星設計寿命である第１期間Ｌ１年の軌道上運用後に、軌道離脱してから第１期間Ｌ１年未満の期間で大気圏突入するために必要な量の推薬を保有するように人工衛星を制御する。

10. 发明申请

WO2020254984A2 AN APPARATUS FOR CONTROLLING A SPACECRAFT'S ATMOSPHERIC REENTRY 审中-公开
公开(公告)号：WO2020254984A2
公开(公告)日：2020-12-24
申请号：PCT/IB2020/055651
申请日：2020-06-17
申请人： ALHUBAIL, Jasem
发明人： ALHUBAIL, Jasem
IPC分类号： B64G1/10 , B64G1/14 , B64G1/24 , B64G1/62 , B64C1/00 , B64G1/242 , B64G1/244
摘要： An aerodynamic louver system used in one or more of the following operations: control, adjust, or stabilize, aid in controlling, adjusting or stabilizing a spacecraft's orientation, angle of attack, lift, or position. There could be multiple of these systems on the spacecraft's body, working together to control the aerodynamic forces acting on the body of the spacecraft.

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