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1. 发明申请

WO2023091492A1 SATELLITE HAVING ACTIVELY COOLED ELECTRIC THRUSTER 审中-公开
公开(公告)号：WO2023091492A1
公开(公告)日：2023-05-25
申请号：PCT/US2022/050115
申请日：2022-11-16
申请人： EARTH OBSERVANT INC.
发明人： ROSENBLAD, Nathan , THEIN, Christopher
IPC分类号： B64G1/40 , B64G1/50 , F03H1/00 , F25B9/14 , G21C1/00 , G21C19/04
摘要： A satellite having a cooling system to remove heat from an electric rocket engine using a working fluid. The cooling system can include a pump that circulates working fluid along a cooling loop between the rocket engine and a radiator. The cooling system can also utilize thermoacoustic, Stirling refrigeration, and/or heat pipe techniques. One or more reservoirs can be provided to store the working fluid, and in some forms a secondary reservoir can be provided to aid in management of a center of mass of the satellite. A fluid reaction loop can be provided in which working fluid is accelerated to impart a torque on the satellite. In some forms, the working fluid can be utilized as both a coolant and a propellant for the rocket engine. The electric rocket thruster can also include one or more internal pathways for the conveyance of working fluid.

2. 发明申请

WO2023059413A1 DUCTED ELECTROAERODYNAMIC THRUSTERS 审中-公开
公开(公告)号：WO2023059413A1
公开(公告)日：2023-04-13
申请号：PCT/US2022/042437
申请日：2022-09-02
申请人： MASSACHUSETTS INSTITUTE OF TECHNOLOGY
发明人： BARRETT, Steven , XU, Haofeng , BROWN, Arthur , GOMEZ VEGA, Nicolas
IPC分类号： F03H1/00 , B64G1/40
摘要： Electroaerodynamic devices and their methods of operation are disclosed. In one embodiment, ions are formed by dielectric barrier discharge using a time-varying voltage differential applied between a first electrode and a second electrode. The ions are then accelerated in a downstream direction using a second voltage differential applied between a third electrode and the first and/or second electrodes, where the third electrode is located downstream from the first and second electrodes. The ions may then collide with naturally charged molecules and/or atoms within a fluid to accelerate the fluid in the downstream to create an ionic wind and an associated thrust.

3. 发明申请

WO2023037138A1 ELECTRODELESS PLASMA THRUSTER WITH CLOSE RING-SHAPED GAS DISCHARGE CHAMBER 审中-公开
公开(公告)号：WO2023037138A1
公开(公告)日：2023-03-16
申请号：PCT/IB2021/058145
申请日：2021-09-07
申请人： KHALIFA UNIVERSITY OF SCIENCE AND TECHNOLOGY
发明人： SHUMEIKO, Andrei Ivanovich , JARRAR, Firas Salah , SWEI, Sean Shan Min
IPC分类号： F03H1/00 , B64G1/40
摘要： An electrodeless plasma thruster with close ring-shaped gas discharge chamber (1,10) can include a gas discharge chamber (1,10) close ring shaped in fluid communication with a propellant storage system (10,70). An antenna (3,30) can be positioned on the exterior of the gas discharge tube (1,10). A guide tube (2,20) can be coupled with the gas discharge chamber (1,10) at a first end and have a second open end. A magnetic system (7,50) can be positioned on the second end of the guide tube (2,20). The magnetic system (7,50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11,80) and a control module (12,90).

4. 发明申请

WO2022251763A2 ANNULAR AEROSPIKE NOZZLE WITH WIDELY-SPACED THRUST CHAMBERS, ENGINE INCLUDING THE ANNULAR AEROSPIKE NOZZLE, AND VEHICLE INCLUDING THE ENGINE 审中-公开
公开(公告)号：WO2022251763A2
公开(公告)日：2022-12-01
申请号：PCT/US2022/071688
申请日：2022-04-13
申请人： STOKE SPACE TECHNOLOGIES, INC.
发明人： MCCULLOUGH, Thomas, Ryan , FELDMAN, Thomas , LAPSA, Andrew , SANDER, Zachary
IPC分类号： F02K9/88 , B64G1/40 , B64G1/62 , F02K9/00 , F02K9/66 , F02K9/80 , F02K9/86 , F02K9/97 , B64G1/002 , B64G1/58 , F05D2250/31
摘要： An annular aerospike nozzle for a vehicle, such as an upper stage rocket, is disclosed. The annular aerospike nozzle includes a centerbody and a plurality of thrust chambers spaced around the centerbody. Each thrust chamber has a throat and a nozzle portion extending aft of the throat. The nozzle portion has an exit dimension Dexit at an aft end. Each thrust chamber is spaced away from adjacent thrust chambers by a spacing distance Dspace, such that Dspace ≥ M * Dexit, where M ≥ 1.

5. 发明申请

WO2022238660A1 ENGIN SPATIAL DE DISTRIBUTION ÉLECTRIQUE, ET PROCÉDÉ ASSOCIÉ 审中-公开
公开(公告)号：WO2022238660A1
公开(公告)日：2022-11-17
申请号：PCT/FR2022/050901
申请日：2022-05-11
申请人： CENTRE NATIONAL D'ÉTUDES SPATIALES , SAFRAN AIRCRAFT ENGINES , THALES
发明人： BULTEL, Pascal , DURAND, Gautier , THIRY, Nicolas , ANSART, Marie , BOUHOURS, Gilles , DUCHEMIN, Olivier , MARCHANDISE, Frédéric
IPC分类号： B64G1/10 , B64G1/40 , B64G1/42 , B64G1/62 , B64G1/64 , B64G1/16 , B64G1/1078 , B64G1/401 , B64G1/402 , B64G1/405 , B64G1/646 , B64G2001/1071
摘要： L'invention concerne un engin spatial (1) pour la distribution d'énergie électrique à des engins clients (2) en des points situés dans l'espace libre, en orbite et/ou sur un corps céleste, l'engin spatial (1) comprenant une structure principale (10) équipée d'un propulseur électrique (10A), d'un propulseur chimique (10B) et d'un générateur solaire (10C), un premier contenant (11) de carburant destiné au propulseur électrique (10A), et un deuxième contenant (12) de carburant destiné au propulseur chimique (10B), l'engin spatial (1) étant modulable de sorte que : la structure principale (10) peut être couplée/découplée alternativement au premier contenant (11) ou au deuxième contenant (12), le premier contenant (11) et le deuxième contenant (12) pouvant être couplées/découplés l'un de l'autre, le générateur solaire (10C) d étant prévu pour être déployé ou rétracté.

6. 发明申请

WO2022167539A1 TRÄGERRAKETE UND VERFAHREN ZUM BETREIBEN EINER TRÄGERRAKETE 审中-公开
公开(公告)号：WO2022167539A1
公开(公告)日：2022-08-11
申请号：PCT/EP2022/052612
申请日：2022-02-03
申请人： LARCH, Sascha
发明人： LARCH, Sascha
IPC分类号： B64G1/40 , B64G1/00 , B64G1/62
摘要： Eine Trägerrakete mit einem eine Längsachse (Z, Z') aufweisenden Raketenkörper (2; 102), der zumindest eine von einem vorwiegend parallel zur Längsachse (Z, Z') wirksamen Rückstoßantrieb (36; 136) antreibbare Antriebsstufe (3; 103) aufweist,wobei die Trägerrakete mit einer Mehrzahl von mittels jeweils eines Rotorantriebs antreibbaren Rotoren versehen ist, deren jeweilige Rotorachse im Wesentlichen parallel zur Längsachse des Raketenkörpers ausgerichtet ist, zeichnet sich dadurch aus, dass eine mit dem Raketenkörper (2; 102) und/oder der Antriebsstufe (3; 103) gekoppelte oder koppelbare und davon entkoppelbare, separate Startstufe (5; 105) vorgesehen ist, die die Mehrzahl von äußeren Rotoren (52) aufweist, dass die äußeren Rotoren (52) nach Art eines Multikopters radial außerhalb des Raketenkörpers (2; 102) diesen umgebend angeordnet sind, dass der jeweilige Rotorantrieb (53) zumindest einen Elektromotor als Antriebsmaschine aufweist, dass die Startstufe (5; 105) mit zumindest einer Stromspeichereinrichtung (58; 158) zur Speicherung von elektrischer Energie und zur Versorgung der äußeren Rotorantriebe (53) mit elektrischer Energie versehen ist und dass zumindest ein Teil der Rotorantriebe (53) bei einer Autorotation der äußeren Rotoren (52) in einem Generatormodus betreibbar ist, in dem elektrische Energie erzeugbar ist, und dass die betreffenden Rotorantriebe (53) ausgebildet sind, um die erzeugte elektrische Energie in die jeweils zugeordnete Stromspeichereinrichtung (58; 158) zurückzuführen.

7. 发明申请

WO2022147507A1 SYSTEM AND METHOD FOR MAGNETICALLY INDUCED ELECTROSPRAY THRUSTERS 审中-公开
公开(公告)号：WO2022147507A1
公开(公告)日：2022-07-07
申请号：PCT/US2022/011049
申请日：2022-01-03
申请人： UNIVERSITY OF SOUTHERN CALIFORNIA
发明人： ANTYPAS, Robert , WANG, Joseph
IPC分类号： B64G1/40 , B05B5/00 , H01J37/08
摘要： A device and method for emitting an electrospray of ionized particles is disclosed, comprising a reservoir, an emitter in communication with the reservoir and having openings, wherein the openings are configured to permit release of the liquid media therefrom in response to a dynamic magnetic field; and an element for generating a dynamic magnetic field that runs through the emitter. The element may comprise two orthogonal Helmholtz coil pairs. In another example embodiment, an electrospray thruster is disclosed. The electrospray thruster may comprise: a reservoir for accommodating a volume of liquid media capable of being ionized; an emitter grid comprising a plurality of emitters, wherein each emitter of the plurality of emitters is in communication with the reservoir and comprises an opening disposed therethrough; and an element for causing the liquid media to be ionized from the emitter by a dynamic magnetic field.

8. 发明申请

WO2022116955A1 一种推力室的双层结构加工方法及航天器推力室审中-公开
公开(公告)号：WO2022116955A1
公开(公告)日：2022-06-09
申请号：PCT/CN2021/134260
申请日：2021-11-30
申请人：蓝箭航天空间科技股份有限公司
发明人：杨瑞康 , 宣智超 , 常克宇 , 袁宇 , 黄乐 , 周涛
IPC分类号： G05B19/418 , B64G1/40
摘要：一种航天器推力室双层结构的加工方法，其包括提供第一壁结构（1）、第二壁结构（2）和凸肋（4）；使第一壁结构（1）和第二壁结构（2）相互靠近，并第一壁结构（1）和所述第二壁结构（2）在端部封闭，由此形成由第一壁结构（1）、第二壁结构（2）和凸肋（4）组成的内部为密闭空间的组合结构；使密闭空间为负压，然后将组合结构进行第一加压处理，接下来，在密闭空间与外界连通的情况下进行第二加压处理，其中第二加压处理的最大压力大于第一加压处理的最大压力，由此使组合结构焊接为一体，获得双层结构。加工方法工艺简单，制造周期短，且成本低。

9. 发明申请

WO2022112718A1 SYSTEME DE TRANSPORT SPATIAL REUTILISABLE 审中-公开
公开(公告)号：WO2022112718A1
公开(公告)日：2022-06-02
申请号：PCT/FR2021/052094
申请日：2021-11-25
申请人： ARIANEGROUP SAS
发明人： PRAMPOLINI, Marco , BOURGOING, Alexis
IPC分类号： B64G1/00 , B64G1/40 , B64G1/62
摘要： Un système (1) de transport spatial destiné à être monté sur un lanceur spatial (100) comprenant un dispositif de propulsion (2) ré-allumable et des volets (3) orientables situés à une seconde extrémité (12) et une unité de contrôle (4), chaque volet (3) comprenant moyen d'actionnement configuré pour modifier l'orientation dudit volet (3), ladite unité de contrôle (4) étant configurée pour commander l'activation du dispositif de propulsion (2) et commander individuellement l'orientation des volets (3) afin de mettre en œuvre les étapes suivantes : une étape de lancement durant laquelle le dispositif de propulsion (2) est éteint et les volets (3) sont dans une position rétractée; une étape de retour durant laquelle l'unité de contrôle (4) déploie les volets (3) et commande individuellement l'orientation des volets (3) pour ralentir le système (1), le dispositif de propulsion (2) étant éteint; une étape d'atterrissage durant laquelle l'unité de contrôle (4) commande le dispositif de propulsion (2) et les moyens d'actionnement pour orienter les volets (3) pour ralentir et effectuer un retournement du système (1).

10. 发明申请

WO2022104408A1 A PLASMA REACTOR 审中-公开
公开(公告)号：WO2022104408A1
公开(公告)日：2022-05-27
申请号：PCT/AU2021/051068
申请日：2021-09-16
申请人： NON LINEAR PLASMA PTY LTD AS TRUSTEE OF THE NON LINEAR PLASMA DISCRETIONARY TRUST
发明人： RENNIE, Scott
IPC分类号： F03H1/00 , H05H1/04 , B64G1/40
摘要： A plasma reactor is provided together with a method for generating kinetic energy to propel a craft. The reactor includes an inlet for plasma; a reactor core having an interior chamber and an exterior chamber, the interior chamber being configured to rotate within the exterior chamber; a pair of opposing polar field generators, a first polar field generator connected proximal to an inlet of the interior chamber, and a second polar field generator connected proximal to an outlet of the interior chamber, the pair of polar field generators configured to induce a current in the plasma to generate a toroidal flow therein, wherein the toroidal flow compresses the plasma into a z-pinch flow in a central column between the first polar field generator and the second polar field generator; turbine blades located between the interior chamber and the exterior chamber for generating thrust to convert the z-pinch flow to kinetic energy; and an outlet.

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