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1.
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Pangea Propulsion
| Numéro d'application |
019193315 |
| Statut |
En instance |
| Date de dépôt |
2025-05-26 |
| Propriétaire |
PANGEA AEROSPACE S.L. (Espagne)
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| Classes de Nice ? |
- 07 - Machines et machines-outils
- 42 - Services scientifiques, technologiques et industriels, recherche et conception
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Produits et services
Aeronautical engines; motors for aeronautical purposes; aircraft engines; rocket engines for the propulsion of aircraft; aircraft propulsion systems and apparatus; propulsion systems and apparatus for air vehicles, aircraft and platforms in aeronautical and space environments. Technical research in the field of aeronautics; design and development of aeronautical engines; engineering, design, research and technological development services in the field of propulsion systems for vehicles, aircraft and platforms in aeronautical and space environments; technical feasibility studies of engines and propulsion systems for vehicles, aircraft and platforms in aeronautical and space environments; technical consultation in the field of aerospace engineering.
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2.
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Miscellaneous Design
| Numéro d'application |
019193335 |
| Statut |
En instance |
| Date de dépôt |
2025-05-26 |
| Propriétaire |
PANGEA AEROSPACE S.L. (Espagne)
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| Classes de Nice ? |
- 07 - Machines et machines-outils
- 42 - Services scientifiques, technologiques et industriels, recherche et conception
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Produits et services
Aeronautical engines; motors for aeronautical purposes; aircraft engines; rocket engines for the propulsion of aircraft; aircraft propulsion systems and apparatus; propulsion systems and apparatus for air vehicles, aircraft and platforms in aeronautical and space environments. Technical research in the field of aeronautics; design and development of aeronautical engines; engineering, design, research and technological development services in the field of propulsion systems for vehicles, aircraft and platforms in aeronautical and space environments; technical feasibility studies of engines and propulsion systems for vehicles, aircraft and platforms in aeronautical and space environments; technical consultation in the field of aerospace engineering.
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3.
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Pangea
| Numéro d'application |
019193312 |
| Statut |
En instance |
| Date de dépôt |
2025-05-26 |
| Propriétaire |
PANGEA AEROSPACE S.L. (Espagne)
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| Classes de Nice ? |
- 07 - Machines et machines-outils
- 42 - Services scientifiques, technologiques et industriels, recherche et conception
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Produits et services
Aeronautical engines; motors for aeronautical purposes; aircraft engines; rocket engines for the propulsion of aircraft; aircraft propulsion systems and apparatus; propulsion systems and apparatus for air vehicles, aircraft and platforms in aeronautical and space environments. Technical research in the field of aeronautics; design and development of aeronautical engines; engineering, design, research and technological development services in the field of propulsion systems for vehicles, aircraft and platforms in aeronautical and space environments; technical feasibility studies of engines and propulsion systems for vehicles, aircraft and platforms in aeronautical and space environments; technical consultation in the field of aerospace engineering.
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4.
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AEROSPIKE ENGINES, LAUNCH VEHICLES INCORPORATING SUCH ENGINES AND METHODS
| Numéro d'application |
18271834 |
| Statut |
En instance |
| Date de dépôt |
2022-01-11 |
| Date de la première publication |
2024-02-29 |
| Propriétaire |
PANGEA AEROSPACE, S.L. (Espagne)
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| Inventeur(s) |
- Rossi, Federico
- Argemí Samsó, Adrià
- Palumbo, Nicola
- Bergström, Rasmus
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Abrégé
An aerospike engine configured to be connected to a liquid methane tank, and to a liquid oxygen tank is provided. The aerospike engine comprises a centerbody including an aerospike nozzle, an external skirt, and a combustion chamber being defined between the external skirt and the centerbody. The centerbody is additively manufactured from one or more copper alloys and has a plurality of centerbody internal cooling channels. The external skirt is additively manufactured from one or more copper alloys and has a plurality of skirt internal cooling channels. The aerospike engine is configured to supply liquid methane and liquid oxygen through the internal cooling channels to the combustion chamber. Also disclosed are stages of a launch vehicle and a launch vehicle comprising such an aerospike engine, as well as methods for re-entry for a re-usable stage of a launch vehicle comprising an aerospike engine.
Classes IPC ?
- B64G 1/00 - Véhicules spatiaux
- B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
- F02K 9/64 - Chambres de combustion ou de poussée comportant des aménagements pour le refroidissement
- F02K 9/76 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande combinés avec un autre ensemble fonctionnel à propulsion par réaction avec un autre moteur-fuséeMoteurs-fusées à plusieurs étages
- F02K 9/97 - Tuyères de fusée
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5.
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AEROSPIKE ENGINES, LAUNCH VEHICLES INCORPORATING SUCH ENGINES AND METHODS
| Numéro d'application |
EP2022050426 |
| Numéro de publication |
2022/152688 |
| Statut |
Délivré - en vigueur |
| Date de dépôt |
2022-01-11 |
| Date de publication |
2022-07-21 |
| Propriétaire |
PANGEA AEROSPACE, S.L. (Espagne)
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| Inventeur(s) |
- Rossi, Federico
- Argemí Samsó, Adrià
- Palumbo, Nicola
- Bergström, Rasmus
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Abrégé
An aerospike engine configured to be connected to a liquid methane tank, and to a liquid oxygen tank is provided. The aerospike engine comprises a centerbody including an aerospike nozzle, an external skirt, and a combustion chamber being defined between the external skirt and the centerbody. The centerbody is additively manufactured from one or more copper alloys and has a plurality of centerbody internal cooling channels. The external skirt is additively manufactured from one or more copper alloys and has a plurality of skirt internal cooling channels. The aerospike engine is configured to supply liquid methane and liquid oxygen through the internal cooling channels to the combustion chamber. Also disclosed are stages of a launch vehicle and a launch vehicle comprising such an aerospike engine, as well as methods for re-entry for a re-usable stage of a launch vehicle comprising an aerospike engine.
Classes IPC ?
- F02K 9/97 - Tuyères de fusée
- F02K 9/64 - Chambres de combustion ou de poussée comportant des aménagements pour le refroidissement
- F02K 9/76 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande combinés avec un autre ensemble fonctionnel à propulsion par réaction avec un autre moteur-fuséeMoteurs-fusées à plusieurs étages
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6.
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Return to base space launch vehicles, systems and methods
| Numéro d'application |
17290699 |
| Numéro de brevet |
11912441 |
| Statut |
Délivré - en vigueur |
| Date de dépôt |
2019-11-05 |
| Date de la première publication |
2022-01-20 |
| Date d'octroi |
2024-02-27 |
| Propriétaire |
PANGEA AEROSPACE, S.L. (Espagne)
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| Inventeur(s) |
- Argemi Samso, Adria
- Bergstrom, Rasmus
- Rossi, Federico
- Palumbo, Nicola
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Abrégé
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.
Classes IPC ?
- B64G 1/62 - Systèmes de retour sur terreDispositifs de freinage ou d'atterrissage
- B64G 1/00 - Véhicules spatiaux
- B64G 1/42 - Aménagements ou adaptations des systèmes fournissant l'énergie
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7.
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RETURN TO BASE SPACE LAUNCH VEHICLES, SYSTEMS AND METHODS
| Numéro d'application |
EP2019080235 |
| Numéro de publication |
2020/094640 |
| Statut |
Délivré - en vigueur |
| Date de dépôt |
2019-11-05 |
| Date de publication |
2020-05-14 |
| Propriétaire |
PANGEA AEROSPACE, S.L. (Espagne)
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| Inventeur(s) |
- Argemi Samso, Adria
- Bergstrom, Rasmus
- Rossi, Federico
- Palumbo, Nicola
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Abrégé
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.
Classes IPC ?
- B64G 1/00 - Véhicules spatiaux
- B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
- B64G 1/42 - Aménagements ou adaptations des systèmes fournissant l'énergie
- B64G 1/62 - Systèmes de retour sur terreDispositifs de freinage ou d'atterrissage
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