Rocket propulsion and satellite deployment system

Abstract

A rocket propulsion and satellite deployment system, comprising a rocket comprising at least a base sector, an operating sector, and a transport sector; the base sector comprises a propellant and is configured to transport the sectors to a mission target; the operating sector comprises a rotating robotic arm pivoted to the operating sector; the transport sector is configured to hold a load intended to be delivered to the target by means of a rotation of the rotating robotic arm with respect to the operating sector, accelerating the load itself which is subsequently released in a direction opposite to the speed of the rocket, increasing, due to conservation of momentum, the speed of the rocket itself. The system is based on a so-called 'useful propellant', consisting of the satellites, rovers and orbiters themselves, which, through the rotational acceleration system, are used to increase the speed of the rocket in space. As well as providing an alternative to traditional propulsion, this system provides an innovative way of putting satellites into orbit, especially in non-earth orbit, which can also be used for longer missions with more than just one target.

Description

[0001] ROCKET PROPULSION AND SATELLITE DEPLOYMENT SYSTEM

[0002] The present invention relates to a rocket propulsion and satellite deployment system. Launch systems comprising launch and transfer vehicles equipped with liquid or solid propellant rocket motors, or combinations of both, are known.

[0003] GB2210839A discloses a spacecraft structure for orbital assembly and servicing including a payload module, a propulsion module, and a bus module. The bus module has at each end a latching fitting to match and mate during assembly with a latching fitting at an end of each of the payload and propulsion modules. The bus module includes sectionalized assemblies each having a matrix of identical cavities. The cavities receive replaceable submodules. The assemblies are secured to opposite parallel faces of a central truss frame which carries the latching fittings.

[0004] US2023141538A1 discloses a system for the release of satellites from a launch vehicle including: a torsion bar, having a first end which is fixed by means of support means to a launch vehicle and is locked in rotation around a longitudinal axis of the torsion bar, and a second end which is connected by means of hinge means to the launch vehicle and is free to rotate around the longitudinal axis; a launch arm extending perpendicularly from the torsion bar and comprising a torsion lever having a first end which is fixed to the torsion bar in an integral manner, and a guide having a first end connected to a second end of the torsion lever, and a second free end; a slider is fixed in an integral manner to a satellite to be launched and arranged to engage the guide in a sliding manner; a limit stop element designed to act upon the torsion lever to stop the rotation of the launch arm around the longitudinal axis.

[0005] Propulsion systems using liquid-propellant engines contain three primary elements, a fuel tank, an oxidant tank and the rocket thruster. The fuel and oxidant are forced into the thruster chamber by the pressure of the tank, where they ignite and are ejected through the rocket nozzle producing thrust.

[0006] While liquid engines can be stopped and restarted in flight, solid propellant engines burn continuously until all the propellant is consumed.

[0007] Transporting cargo into space is expensive, and the high cost is partly attributable to the sum of several expensive individual operations that are required to transport and deliver satellites and other cargo into orbit.

[0008] The last part of the orbital transport operation, i.e. the transport of the payload from low Earth orbit to the desired final destination of the terrestrial and non-terrestrial mission, is usually performed by an upper or final stage.

[0009] This stage is turned on and transports the payload to the final orbit. Sometimes this stage remains associated with the payload, satellite or cargo; but it is usually discarded in orbit.

[0010] Upper stages vary in their capacity for independent actions from a simple, small, passive solid rocket motor that provides only additional propulsion capability, which goes in the direction it is pointed when ignited, to very capable, re-startable liquid rocket motors capable of multiple restarts and significant manoeuvres using thrusters and related avionics.

[0011] Some active upper stages are capable of deploying multiple satellites.

[0012] The aim of the present invention is to provide a new system for propelling rockets and launching satellites into orbit in space that overcomes the drawbacks of the prior art.

[0013] Within the scope of this aim, a particular object of the invention is to provide a system that offers a significant reduction in overall conventional propellant consumption.

[0014] A further object of the invention is to provide a system consisting of a new type of rocket capable of delivering a variable number of satellites, rovers, etc., to multiple planets or celestial bodies, as distinct from conventional rockets that are mostly capable of delivering the payload to a single target.

[0015] A further object of the invention is to provide a system that allows multiple missions to be combined into one, reducing the number of rockets needed to carry out the missions and thus reducing overall costs.

[0016] A further object of the invention is to provide a system that allows an increase of the mission speed together with a reduction in overall costs.

[0017] The above aim and objects, and others which will better appear hereafter, are achieved by a rocket propulsion and satellite deployment system, as claimed in the appended claims.

[0018] Further characteristics and advantages will become clearer from the description of preferred, but not exclusive, embodiments of the invention, illustrated by way of indicative and non-limiting purposes in the attached drawings, wherein:

[0019] Fig. 1 is a front schematic view illustrating a rocket according to the invention;

[0020] Fig. 2 is a side view of the rocket;

[0021] Fig. 3 is a front view illustrating the rotated arm;

[0022] Fig. 4 is a front schematic view illustrating a rocket according to a further aspect of the invention;

[0023] Fig. 5 is a front view of the rocket of Fig. 4 illustrating the rotated arms;

[0024] Fig. 6 is a top view of the rocket of Fig. 4 with arms at rest;

[0025] Fig. 7 is a detail view of the hinge assembly associating the rotating robotic arms to the support member of the rocket of Fig. 4.

[0026] With particular reference to figures 1-3, the system according to the invention, globally designated by reference numeral 1 , comprises a rocket comprising four sectors including a base sector 10, an operational sector 12, a transport sector 13, and a protection sector 14.

[0027] The base sector 10 comprises a conventional propellant and is configured to transport the other sectors to the orbit of the planet considered to be the first target of the mission, or to insert the other sectors into a trajectory with such a destination.

[0028] The sector base 10 can be constructed, according to the known art, as a so-called first stage.

[0029] According to the present invention, the operating sector 12 comprises a rotating robotic arm 21 hinged to the transport sector 13.

[0030] The robotic arm 21 is hinged to the transport sector 13 by means of a pin 22 associated to a support 24 which is connected to the transport sector 13.

[0031] The transport sector 13 is configured to store the payload 50, comprising satellites, rovers, etc., intended to be delivered into the destination orbit, by means of the robotic arm 21.

[0032] Part of the payload 50 may also be contained in the protection sector 14.

[0033] The rotating robotic arm 21 performs the task of accelerating the 'useful fuel' ('useful propellant', consisting of the same satellites, rovers, etc., which are the object of the delivery, as will be better described below) which is subsequently released in the direction C opposite to the speed of the rocket R, increasing the velocity of the rocket 1 , due to conservation of momentum.

[0034] The robotic arm can be made of any material capable of withstanding very high centripetal accelerations of more than 15,000 times the acceleration of gravity.

[0035] By way of example, such a material can be a particular type of carbon fibre, which is extremely resistant in these contexts. Carbon fibre also responds to another of the problems of this mission plan: thanks to some recent research, it appears that, if made in a special way, its density can be reduced by up to a third of its original density, thus combining both characteristics of strength and lightness.

[0036] Other suitable materials can be used for the purpose.

[0037] The length of the arm 21 is closely related to the speed to be reached by the object 50 as it is accelerated.

[0038] As an example, for technical and weight reasons, the arm can be between 30 and 10 metres in length with the material proposed here.

[0039] Longer or shorter lengths may prove to be more efficient in the future, for example if the material is sufficiently light and the arm is designed to be extensible.

[0040] The thickness and width of this rotating arm 21 depend on the specific structural and weight requirements, and are dimensioned so that they can withstand centripetal acceleration, taking into account the reduction of the overall weight of the spacecraft, and thus a reduction in resource consumption and an overall reduction in costs.

[0041] According to the embodiment shown in figures 1-3, the arm 21 has a length of 10 metres and a thickness and width of 0.5 metres.

[0042] These parameters are, as already pointed out, open to modification, for example to achieve an improvement in rocket efficiency and an overall cost reduction.

[0043] The arm 21 is provided with the pin 22 which joins the rotating part, through its centre of rotation, to the support 24 which connects the arm itself to the upper part of the spacecraft, i.e. to the transport sector 13.

[0044] Advantageously, according to this embodiment, the support 24 is made of carbon fibre, the same used for the arm 21 , and also for pin 22.

[0045] The length of the support 24 is, in this example, substantially equal to the length of the arm 21 .

[0046] Advantageously, the arm 21 has a counterweight 23 placed at the opposite end from the centre of rotation, formed by the pin 22, of the arm 21 .

[0047] The counterweight 23 stabilises the rotating structure and, according to this embodiment, is the same width and thickness as the arm (0.5 metres), and 0.5 metres in length.

[0048] The arm 21 is powered by an energy source of a different nature depending on the rocket used and its destination; for example, if it is sufficiently close to the sun, a power supply via solar panels can be used; otherwise, other types of energy, e.g. nuclear batteries, are used .

[0049] According to this embodiment, a power supply through the use of a nuclear engine, of the type used for example in the Voyager probes, consisting of MHW RTG, Multi Hundred-watt Radioisotope Thermoelectric generator, is considered.

[0050] The energy source is advantageously located in transport sector 13.

[0051] The operating sector 12 comprises an external covering 25 that surrounds this section of the rocket at least during the exit phase from the atmosphere.

[0052] The external covering 25, which prevents the section from burning during the exit phase from the atmosphere, may be entirely similar to the cladding component of the rest of the rocket, used in conventional rockets.

[0053] The covering 25 is detached from the operating sector 12 before the rotating arm 21 begins its operation to deliver the satellites 50.

[0054] The covering 25 can be separated from the rocket in conjunction with base sector 10.

[0055] As described above, the transport sector 13 performs the task of transporting and storing the payload 50, consisting of satellites, rovers, etc., which will subsequently be delivered, via the robotic arm 21 , into their destination orbit.

[0056] The transport sector 13 also houses the aforementioned nuclear engines necessary for the proper functioning of the rotating arm.

[0057] The number, function and mass of the satellites and other items constituting the payload, depend on the objects of the mission. The payload items must comply with certain structural characteristics that will enable them to withstand, without damage, the very high centripetal acceleration to which they will be subjected.

[0058] To date, satellites with a low mass and dimensions of less than 200 kg are available.

[0059] The transport sector 13 advantageously accommodates the mechanism, not visible in the figures, which allows the docking of the satellite 50 and the rotating arm 21 , powered by suitable engines, that ensures the correct attachment and, consequently, delivery of the satellite (or rover, etc.) to its destination.

[0060] Transport sector 13 comprises an external covering, for example similar to that of operational sector 12, which, unlike that of operational sector 12, remains attached to the rocket throughout the duration of the mission, and does not separate together with the first sector 10.

[0061] The final part of the rocket 1 is the protection sector 14 consisting of a cone that performs the function of protecting the rocket during its exit from the atmosphere.

[0062] The protection sector 14 can also store a possible additional payload, for example a CubeSat, a miniaturised satellite designed for interplanetary exploration and of very low mass.

[0063] In the example shown here, the dimensions of cone 14 are such that the diameter of the cone coincides with the height of the cone itself, and both are 3 metres.

[0064] This cone was made using the Von Karman cone model (Haack series with c = 0).

[0065] According to an embodiment of the present invention, a power system comprising nuclear engines is provided, configured to provide power to the rotating arm and the robotic arm which acts as a coupling system between the satellites and the arm.

[0066] The operation of the rocket propulsion and satellite deployment system, according to the present invention, comprises four phases or steps.

[0067] In a first step, the rocket 1 , comprising the four sectors 10, 12, 13, 14, takes off from a launch site and, using the conventional propulsion provided by the propellant in the base sector 10, and other propulsion methods (gravitational assists, for example), reaches the orbit of the first target planet or celestial body of the mission.

[0068] After exiting the atmosphere, but before the start of the second phase, the sector 10 and the external covering 25 of operating sector 12 separate from the rest of the rocket, which continues its journey through space.

[0069] In a second phase, through the robotic arm, powered by nuclear engines, located in sector 13, the object of the first 'delivery', e.g. satellite 50, and the arm 21 are joined together.

[0070] The arm 21 then begins to rotate around the centre of rotation, until it reaches the set speed, at which point the release of satellite 50 takes place, in direction C of figure 3; the payload will maintain the speed obtained, entering into orbit of the planet.

[0071] Through this process, due to conservation of momentum, the spacecraft will gain speed.

[0072] The amount of speed depends on the mass of the satellite 50, its delivery velocity and the remaining mass of the rocket.

[0073] This process can be repeated as many times as there are payload items, satellites, rovers, etc., to be delivered to the planet.

[0074] In a third phase, following the delivery operation(s), the spacecraft resumes its journey towards its second target, having gained speed either through the delivery of the satellites or through other procedures, e.g. gravitational assists around the planet where the first delivery takes place.

[0075] Once the second target is reached, the second step can be repeated, delivering the satellites to the planet that constitutes the second target of the mission.

[0076] The process can be repeated for other targets until delivery of all satellites, rovers, etc.

[0077] In a fourth phase, the rocket continues its journey beyond Neptune, exploring the furthest parts of the solar system, having been accelerated by both traditional methods and the delivery of 'useful propellant'.

[0078] With particular reference to figures 4-7, the system, according to a further aspect of the invention, globally designated by reference numeral 101 , comprises a rocket comprising four sectors including a base sector and operational sector, not shown in the figures, a transport sector 113, and a protection sector 114.

[0079] The base sector comprises a conventional propellant and is configured to transport the other sectors to the orbit of the planet considered to be the first target of the mission, or to insert the other sectors into a trajectory with such a destination.

[0080] According to this aspect of the invention, the operating sector comprises a double rotating robotic arm 121 hinged to the transport sector 113 by means of a pin 122 associated to a support 124 which is connected to the transport sector 113.

[0081] The double rotating robotic arm 121 is constituted by two rotating members, designated by numerals 1211 and 1212 and associated to the support 124 by a pin 122.

[0082] The transport sector 113 is configured to store the payload 150, comprising satellites, rovers, etc., intended to be delivered into the destination orbit, by means of the double robotic arm 121.

[0083] Part of the payload 150 may also be contained in the protection sector 114.

[0084] As shown in figure 5, the rotating members 1211 , 1212 deploy the payloads by rotating in opposite directions in a synchronized manner.

[0085] Each rotating members 1211 , 1212 performs the task of accelerating the payload element 150 which is subsequently released, as described above.

[0086] Advantageously, each arm 121 has a counterweight placed at the opposite end with respect to the centre of rotation, formed by the pin 122, of the arm 121. The counterweight stabilises the rotating structure.

[0087] In practice, it has been found that the invention achieves its intended aim and objects by providing a rocket propulsion and satellite deployment system based on the use of centrifugal force and a rotating arm, starting from space itself and not from the surface of the Earth.

[0088] The system according to the present invention configures a new type of propulsion, called 'useful propellant', consisting of the same satellites, orbiters, etc. that are the subject of the delivery.

[0089] The theoretical basis of the system according to the present invention is based on a study of these same applicants, described at the Regeneron International Science and Engineering Fair (ISEF) in 2024, and summarised in the article published online: (https : / / partner.projectboard.world / isef / project / phys051t-accelerate-is-easier-than- decelerate) The system according to the present invention allows for a significant reduction in overall conventional propellant consumption by replacing it with 'useful propellant'.

[0090] The new type of rocket according to the invention is capable of delivering a variable number of satellites, rovers, etc., to multiple planets or celestial bodies, and differs from conventional rockets, which deliver the payload to a single target.

[0091] The new type of rocket according to the invention allows multiple missions to be combined into one, reducing the number of rockets needed and, consequently, the overall costs.

[0092] The rocket propulsion and satellite deployment system, based on the concept of 'useful propellant', according to the present invention, not only provides an alternative to traditional propulsion, but also provides an innovative system for putting satellites into orbit, especially in non-earth orbit, which is also applicable to longer missions, with not just one target.

[0093] The system according to the present invention is primarily useful outside the Earth's atmosphere, where it is not hindered by the friction of the atmosphere; nevertheless, with possible adaptations, it is advantageously usable also in the terrestrial environment.

Claims

CLAIMS1. A rocket propulsion and satellite deployment system, characterized in that it comprises a rocket (1 , 101) comprising at least a base sector (10), an operating sector (12), and a transport sector (13, 113); said base sector (10) comprising a propellant and being configured to transport said sectors to a mission target; said operational sector (12) comprising at least one rotating robotic arm (21 , 121 , 1211 , 1212) hinged to said operational sector (12); said transport sector (13, 113) holding at least one load (50, 150) to be delivered to said target; each of said loads (50, 150) being delivered to said target by a rotation of said rotating robotic arm (21 , 121) with respect to said operational sector (12) accelerating said load (50, 150) which is released in a direction (C) opposite to the speed (R) of said rocket (1 , 101), increasing said speed of said rocket (1 , 101 ) by conservation of momentum.

2. The system, according to claim 1 , characterized in that it comprises two robotic arms (1211 , 1212) hinged to said operational sector and rotating in opposite directions; each of said robotic arms holding a respective load (150).

3. The system, according to claim 1 or 2, characterized in that said robotic arm (21 , 1211 , 1212) is hinged to said transport sector (13, 113) by means of a pin (22, 122) associated to a support (24, 124) which is connected to said transport sector (13, 113).

4. The system according to one or more of the preceding claims, characterized in that said arm (21 , 121) has a counterweight member (23) located at the opposite end with respect to the center of rotation.

5. The system according to one or more of the preceding claims, characterized in that said rocket (1 , 101) further comprises a protection sector (14, 114) consisting of a cone protecting said rocket (1 , 101 ) during its exit from the atmosphere.

6. The system according to one or more of the preceding claims, characterized in that said rotating robotic arm (21 , 121) is powered by an energy source, such as solar panels, electric motors, or nuclear batteries.

7. The system, according to one or more of the preceding claims, characterized in that said energy source is constituted by MHW RTG, Multi Hundred-watt Radioisotope Thermoelectric generator.

8. The system, according to one or more of the preceding claims, characterized in that said energy source is located in said transport sector (13, 113).

9. The system, according to one or more of the preceding claims, characterized in that said operational sector (12) comprises an external covering (25) that envelops said operating sector (12) at least during the phase of exit from the atmosphere.

10. The system, according to one or more of the preceding claims, characterised in that said covering (25) is separated from said operating sector (12) before said rotating arm (21 ) begins its operation of delivering said payload (50, 150).

11. The system, according to one or more of the preceding claims, characterized in that said transport sector (13, 113) receives a mechanism configured to hook said load (50,150) to said rotating arm (21 , 121); said transport sector (13, 113) comprising an external covering.

12. The system, according to one or more of the preceding claims, characterized in that said external covering of said transport sector (13, 113) remains joined to said rocket (1 , 101 ) throughout the duration of said mission, not separating together with said first sector (10).

13. The system, according to any one or more of the preceding claims, characterized in that said protection sector (14, 114) contains an additional load.

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