Electromagnetic interorbital launch assembly

Abstract

The present invention relates to an interorbital launch assembly (1) for transporting cargo in outer space, comprising at least two electromagnetic launchers (2) for launching a cargo pod (3) and further comprising: - an electromagnetic gun (4) which in turn comprises a hollow launch tube (5) and a system of electromagnets (6) that are attached along the outside of the hollow launch tube, - an energy storage system (7), - a navigation and / or control system (8), - a communications system (9), - a docking system (10) for docking the cargo pod (3) to the electromagnetic gun (4), - a propulsion system (11), and - a launch calculation system (12).

Description

[0001] DESCRIPTION

[0002] AN ELECTROMAGNETIC INTERORBITAL LAUNCH SET

[0003] TECHNICAL SECTOR

[0004] The present invention falls within the field of space launch systems, specifically the set of interorbital electromagnetic launchers for cargo pods in space.

[0005] BACKGROUND OF THE INVENTION

[0006] In the last decade, the aerospace industry has undergone one of the most significant transformations within the sector: the miniaturization of satellites. This has enabled the creation of smaller, more efficient satellites, facilitating their launch and operation. Thus, thanks to the development of smaller electronic components and electric propulsion, the sector has been boosted by the expansion into the creation of lighter and more efficient satellites that require fewer resources for launch and operation. However, reaching higher orbits remains a challenge due to the increased amount of fuel required, which necessitates more robust and complex rockets.

[0007] Currently, several types of interorbital launch vehicles have been developed, which are essential for transporting payloads between different orbits around the Earth. These primarily involve additional rockets attached to satellites, for example. These systems are crucial for the construction and maintenance of space infrastructure, including space stations and satellites. However, current launch vehicle technology relies heavily on chemical fuels, which generate waste and are costly.

[0008] The present invention improves existing technology by enhancing its efficiency and reducing the costs of transporting materials and equipment between different orbits, thus facilitating both the construction and maintenance of space infrastructure and providing a significant step towards more sustainable access to space. EXPLANATION OF THE INVENTION

[0009] The present invention introduces a set of electromagnetic launchers that can be placed in different orbits. These launchers are designed to transport payloads from low Earth orbit to specific locations as needed with high precision, thereby optimizing resource use and reducing environmental impact. This significant advancement is achieved through the use of electromagnetic technology, employing Gauss gun technology for propulsion, with the consequent advantage of minimizing reliance on chemical fuels, thus promoting a more sustainable and efficient solution for space exploration and utilization.

[0010] One aspect of the invention relates to an interorbital launch assembly for transporting payloads in space comprising at least two electromagnetic launchers for launching a payload pod.

[0011] In a preferred embodiment, the electromagnetic launcher of the invention comprises at least:

[0012] - an electromagnetic cannon, also known as a Gauss cannon, comprising in turn a hollow launch tube and a system of electromagnets coupled externally along the hollow launch tube,

[0013] - an energy storage system,

[0014] - a navigation and / or control system,

[0015] - a communications system,

[0016] - a coupling system between the electromagnetic gun and the loading pod,

[0017] - a propulsion system, and

[0018] - a launch calculation system.

[0019] In another preferred embodiment, the electromagnetic cannons capture and / or launch the payload pod by decelerating or accelerating it with the electromagnet system. This allows for reaching orbits farther from Earth and controlling their elliptical or circular shapes according to the intended destination for the payload.

[0020] In a preferred embodiment, the electromagnetic launcher has a loading port and a rear launch port, each located at one end of the hollow launch tube. Furthermore, both ports are capable of performing both loading and launching functions, giving the interorbital launch system the advantage of high adaptability, versatility, and significantly improved effectiveness in various launching scenarios for the propellant pods.

[0021] In another preferred embodiment, the electromagnetic launcher is provided with at least one solar energy harvesting system.

[0022] Furthermore, in a preferred embodiment, the loading pod is provided with at least:

[0023] - a ferromagnetic tractor unit ensuring interaction with the electromagnetic system of the electromagnetic cannon,

[0024] - a cargo container,

[0025] - a communications system, and

[0026] - A cold gas propulsion system to control the movement of the payload pods in space. This propulsion system can be controlled by the navigation system and / or the electromagnetic launcher control system.

[0027] This type of electromagnetic technology employed offers several advantages, among which its enormous versatility stands out, since it can allow a set of electromagnetic launchers located in different orbits, specifically designed to move payloads from low Earth orbit to other specific orbits, as needed; in addition, the electromagnetic launcher of the invention has the ability to both accelerate and decelerate the payload pods.

[0028] BRIEF DESCRIPTION OF THE DRAWINGS

[0029] To complement the description being made and in order to help a better understanding of the characteristics of the invention, a set of drawings is included as an integral part of said description, in which, for illustrative and non-limiting purposes, the following has been represented:

[0030] Figure 1 shows a three-dimensional view of an electromagnetic launcher and its components. Figure 2 shows a three-dimensional view of the propellant pod or projectile.

[0031] Figure 3.- Shows a three-dimensional view of the sheath without caps and with the load visible.

[0032] Figure 4.- Shows a set of electromagnetic launchers.

[0033] PREFERRED EMBODIMENT OF THE INVENTION

[0034] A detailed explanation of an example of a preferred embodiment of the electromagnetic launcher that is the subject of the present invention is then provided with the help of the figures referred to above.

[0035] An interorbital launch assembly (1) (see figure 4), for transporting payloads in space comprising two electromagnetic launchers (2), for launching a payload pod (3) from a low Earth orbit, also called LEO (acronym for Low Earth Orbit) to a higher geostationary orbit, although it could be launched even to any other intermediate Earth orbit, whether that destination orbit is circular or elliptical.

[0036] Where each electromagnetic launcher (2), shown in Figure 1, which is designed for the interorbital transport of cargo pods (3) (see Figure 2), is equipped with:

[0037] - an electromagnetic cannon (4) comprising in turn a hollow launch tube (5) and an electromagnet system (6) coupled externally along the hollow launch tube, having a loading mouth (13) and a rear launch mouth (14), each being at one end of the hollow launch tube (5),

[0038] - an energy storage system (7) or capacitor bank,

[0039] - a navigation and / or control system (8),

[0040] - a communications system (9),

[0041] - a coupling system (10) between the electromagnetic gun (4) and the loading pod (3),

[0042] - a propulsion system (11),

[0043] - a launch calculation system (12), and - a solar energy collection system (15) to supply power to the launcher.

[0044] Furthermore, the cargo pod (3) or projectile is a container intended to house satellites, and is equipped with: - a ferromagnetic tractor head (16) ensuring interaction with the electromagnet system (6),

[0045] - a cargo container (17), with protective covers for the cargo; see Figure 3 for the cargo arrangement. In this case, the cargo consists of satellites inside. - a communications system (18), and

[0046] - a cold gas propulsion system (19).

Claims

CLAIMS 1. An interorbital launch assembly (1) for transporting payloads in space characterized in that it comprises at least two electromagnetic launchers (2) for launching a payload pod (3).

2. An interorbital launch assembly (1), according to claim 1, wherein the electromagnetic launcher (2) comprises at least: - an electromagnetic cannon (4) comprising in turn a hollow launch tube (5) and an electromagnet system (6) coupled externally along the hollow launch tube, - an energy storage system (7), - a navigation and / or control system (8), - a communications system (9), - a coupling system (10) between the electromagnetic gun (4) and the loading pod (3), - a propulsion system (11), and - a launch calculation system (12).

3. An interorbital launch assembly (1), according to claim 1 or 2, wherein the electromagnetic cannons (4) capture and / or launch the charge pod (3) by decelerating or accelerating with the electromagnet system (6).

4. An interorbital launch assembly (1), according to any of claims 1 to 3, characterized in that the electromagnetic launcher (2) has a loading mouth (13) and a rear launching mouth (14), each being at one end of the hollow launch tube (5) and both mouths have the ability to perform both functions, loading and launching.

5. An interorbital launch assembly (1), according to any of claims 1 to 4, characterized in that the electromagnetic launcher is provided with at least one solar energy harvesting system (15).

6. An interorbital launch assembly (1), according to any of claims 1 to 5, characterized in that the payload pod (3) is provided with at least: - a ferromagnetic tractor unit (16) ensuring interaction with the electromagnet system (6), - a cargo container (17), - a communications system (18), and - a cold gas propulsion system (19), to control the movement of the cargo pods (3) in space.

Images