SATELLITE LAUNCH PAD (SLP)

Abstract

ABSTRACT “SATELLITE LAUNCH PAD (SLP)” The present invention provides satellite launch pad (SLP). The launch pad itself contains an “Electromagnetic Solenoid Magnetic Accelerator”, which will launch the rocket (whose upper stage also contains a current carrying solenoid). This technology of propulsion doesn’t require any chemical fuel consumption and the power source will be the as usual solar panels. Hence, here the Sun is playing the role of fuel. In this way fuel consumption by the rocket can be minimized. SLP consumes some fuel to be in dynamic equilibrium, at the instant of launch, which is very small as compared to the fuel consumed by the rocket during the above discussed procedure. Figure 1

Specification

Description:TECHNICAL FIELD
[0001] The present invention relates to the field of satellite systems, and more particularly, the present invention relates to the satellite launch pad (SLP).
BACKGROUND ART
[0002] The following discussion of the background of the invention is intended to facilitate an understanding of the present invention. However, it should be appreciated that the discussion is not an acknowledgment or admission that any of the material referred to was published, known, or part of the common general knowledge in any jurisdiction as of the application's priority date. The details provided herein the background if belongs to any publication is taken only as a reference for describing the problems, in general terminologies or principles or both of science and technology in the associated prior art.
[0003] Solved problem of prior art - No fuel consumption and much lesser time consumption, before Hohmann Orbit Transfer.
[0004] Actual problem in the existing product - Chemical propulsion system is used during Orbit Raising Maneuver to achieve at least the escape speed during an interplanetary mission, where fuel is consumed and simultaneously time is also consumed during the above-mentioned process. This is a common process used before Hohmann Orbit Transfer.
[0005] There is one more propulsion system i.e. Gravity Field Propulsion. It seems to be very impossible with the current technologies, but there are some small theoretical works on this, which describes about the working of the engine, where space-time fabric is manipulated to generate a forward thrust.
[0006] In light of the foregoing, there is a need for Satellite launch pad (SLP) that overcomes problems prevalent in the prior art associated with the traditionally available method or system, of the above-mentioned inventions that can be used with the presented disclosed technique with or without modification.
[0007] All publications herein are incorporated by reference to the same extent as if each individual publication or patent application were specifically and individually indicated to be incorporated by reference. Where a definition or use of a term in an incorporated reference is inconsistent or contrary to the definition of that term provided herein, the definition of that term provided herein applies, and the definition of that term in the reference does not apply.
OBJECTS OF THE INVENTION
[0008] The principal object of the present invention is to overcome the disadvantages of the prior art by providing satellite launch pad (SLP).
[0009] Another object of the present invention is to provide satellite launch pad (SLP) that is a reusable machine.
[0010] Another object of the present invention is to provide satellite launch pad (SLP) that provides less time (in hours) for achieving escape speed.
[0011] Another object of the present invention is to provide satellite launch pad (SLP), wherein overall fuel consumption is relatively much lesser.
[0012] Another object of the present invention is to provide satellite launch pad (SLP), wherein rocket size gets reduced because the rocket only needs to reach the SLP (reachable by humans) rest kinetic energy will be provided by SLP, for deep space missions.
[0013] The advantages are provided in the form of a table - SLP vs. Currently Used Methods
SLP SLP Currently Us Currently Used Methods
Fuel source for the rocket- The Sun Fuel Source for the rocket- Chemical fuels
This is a reusable machine These are maneuvers, the rocket itself is the machine. Maneuvers are reusable procedure
Provides less time (in hours) for achieving escape speed Takes much longer time (weeks) to achieve escape speed
Overall fuel consumption is relatively much lesser Overall fuel consumption is more
Rocket size gets reduced because the rocket only needs to reach the SLP (reachable by humans) rest kinetic energy will be provided by SLP, for deep space missions. Bigger rockets are required for the same deep space missions.
[0014] Commercial Application of the Technology:
- Space Agencies can use it for Interplanetary Satellite Launches and Human Spaceflights, from other countries.
- With this moon can be reached within a day, so it can be used for Lunar tourism purpose in future.
[0015] The foregoing and other objects of the present invention will become readily apparent upon further review of the following detailed description of the embodiments as illustrated in the accompanying drawings.
SUMMARY OF THE INVENTION
[0016] The present invention relates to satellite launch pad (SLP).
[0017] Only the design and the design-oriented calculations of the SLP are needed to be protected. Because the idea of "Electromagnetic Solenoid Magnetic Accelerator" and "Nuclear Space Propulsion System" (if required) previously exists. The uniqueness is in the way of application of both. The technical difference between the conventional process and my solution is given below.
SLP SLP Currently Us Currently Used Method
It includes the use of - Rocket propulsion System i.e. using the rocket engine to achieve the escape speed; Gravity Assist i.e. using the gravity of a planet and its translational speed to increase the speed and Orbit Raising Maneuver i.e. achieving the escape speed by propelling at the perigee and changing the orbit. And finally transfers to the Hohmann Transfer Orbit. It uses the Magnetic force, delivered to the docked rocket by the surrounding main solenoid and the added force by a paramagnetic sheet (which gets magnetized when comes within the magnetic field region of the solenoid) surrounding the main rocket, to achieve the sufficient escape speed, and finally transfers to the Hohmann Transfer Orbit.
It does not require Recoil Thrusters. It requires Recoil Thrusters to stay in a dynamic equilibrium, at the instant of launch.
It uses chemical fuel the all the above maneuvers It uses the Sun to generate sufficient electricity.
Rocket does not need any attached solenoid in its upper stage The upper stage contains a solenoid to generate a reverse magnetic field.
[0018] While the invention has been described and shown with reference to the preferred embodiment, it will be apparent that variations might be possible that would fall within the scope of the present invention.
BRIEF DESCRIPTION OF DRAWINGS
[0019] So that the manner in which the above-recited features of the present invention can be understood in detail, a more particular description of the invention, briefly summarized above, may have been referred by embodiments, some of which are illustrated in the appended drawings. It is to be noted, however, that the appended drawings illustrate only typical embodiments of this invention and are therefore not to be considered limiting of its scope, for the invention may admit to other equally effective embodiments.
[0020] These and other features, benefits, and advantages of the present invention will become apparent by reference to the following text figure, with like reference numbers referring to like structures across the views, wherein:
[0021] Fig.1 Schematic layout of the maneuver; and
[0022] Fig. 2 Schematic view of launch pad mechanism.
DETAILED DESCRIPTION OF THE INVENTION
[0023] While the present invention is described herein by way of example using embodiments and illustrative drawings, those skilled in the art will recognize that the invention is not limited to the embodiments of drawing or drawings described and are not intended to represent the scale of the various components. Further, some components that may form a part of the invention may not be illustrated in certain figures, for ease of illustration, and such omissions do not limit the embodiments outlined in any way. It should be understood that the drawings and the detailed description thereto are not intended to limit the invention to the particular form disclosed, but on the contrary, the invention is to cover all modifications, equivalents, and alternatives falling within the scope of the present invention as defined by the appended claim.
[0024] As used throughout this description, the word "may" is used in a permissive sense (i.e. meaning having the potential to), rather than the mandatory sense, (i.e. meaning must). Further, the words "a" or "an" mean "at least one" and the word "plurality" means "one or more" unless otherwise mentioned. Furthermore, the terminology and phraseology used herein are solely used for descriptive purposes and should not be construed as limiting in scope. Language such as "including," "comprising," "having," "containing," or "involving," and variations thereof, is intended to be broad and encompass the subject matter listed thereafter, equivalents, and additional subject matter not recited, and is not intended to exclude other additives, components, integers, or steps. Likewise, the term "comprising" is considered synonymous with the terms "including" or "containing" for applicable legal purposes. Any discussion of documents, acts, materials, devices, articles, and the like are included in the specification solely for the purpose of providing a context for the present invention. It is not suggested or represented that any or all these matters form part of the prior art base or were common general knowledge in the field relevant to the present invention.
[0025] In this disclosure, whenever a composition or an element or a group of elements is preceded with the transitional phrase "comprising", it is understood that we also contemplate the same composition, element, or group of elements with transitional phrases "consisting of", "consisting", "selected from the group of consisting of, "including", or "is" preceding the recitation of the composition, element or group of elements and vice versa.
[0026] The present invention is described hereinafter by various embodiments with reference to the accompanying drawing, wherein reference numerals used in the accompanying drawing correspond to the like elements throughout the description. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiment set forth herein. Rather, the embodiment is provided so that this disclosure will be thorough and complete and will fully convey the scope of the invention to those skilled in the art. In the following detailed description, numeric values and ranges are provided for various aspects of the implementations described. These values and ranges are to be treated as examples only and are not intended to limit the scope of the claims. In addition, several materials are identified as suitable for various facets of the implementations. These materials are to be treated as exemplary and are not intended to limit the scope of the invention.
[0027] The present invention relates to satellite launch pad (SLP).
[0028] Only the design and the design-oriented calculations of the SLP are needed to be protected. Because the idea of "Electromagnetic Solenoid Magnetic Accelerator" and "Nuclear Space Propulsion System" (if required) previously exists. The uniqueness is in the way of application of both. The technical difference between the conventional process and my solution is given below.
SLP SLP Currently Us Currently Used Method
It includes the use of - Rocket propulsion System i.e. using the rocket engine to achieve the escape speed; Gravity Assist i.e. using the gravity of a planet and its translational speed to increase the speed and Orbit Raising Maneuver i.e. achieving the escape speed by propelling at the perigee and changing the orbit. And finally transfers to the Hohmann Transfer Orbit. It uses the Magnetic force, delivered to the docked rocket by the surrounding main solenoid and the added force by a paramagnetic sheet (which gets magnetized when comes within the magnetic field region of the solenoid) surrounding the main rocket, to achieve the sufficient escape speed, and finally transfers to the Hohmann Transfer Orbit.
It does not require Recoil Thrusters. It requires Recoil Thrusters to stay in a dynamic equilibrium, at the instant of launch.
It uses chemical fuel the all the above maneuvers It uses the Sun to generate sufficient electricity.
Rocket does not need any attached solenoid in its upper stage The upper stage contains a solenoid to generate a reverse magnetic field.
[0029] The device will be operated in the outer space. So, no environmental damage will be confronted while implementing it. Additionally, no such environmental damage will be confronted while developing, except while placing it in the orbit, the rocket used to place it will release exhausts into the environment, as it does, typically, during conduct of launch.
[0030] All the innovative features of SLP are as follows-
- It uses the Solenoid Magnetic Accelerator system.
- It can use Nuclear Space Propulsion System.
- It also uses a paramagnetic sheet to provide extra magnetic thrust.
- The rocket also has an added solenoid in its upper stage.
[0031] Applications of the invention are -
- Interstellar and interplanetary satellite and rover-based missions.
- Interplanetary human spaceflight missions.
- Lunar human spaceflight missions.
- Lunar tourism (if possible)
[0032] Various modifications to these embodiments are apparent to those skilled in the art from the description and the accompanying drawings. The principles associated with the various embodiments described herein may be applied to other embodiments. Therefore, the description is not intended to be limited to the 5 embodiments shown along with the accompanying drawings but is to be providing the broadest scope consistent with the principles and the novel and inventive features disclosed or suggested herein. Accordingly, the invention is anticipated to hold on to all other such alternatives, modifications, and variations that fall within the scope of the present invention and appended claims.
, Claims:CLAIMS
We Claim:
1) A satellite launch pad (SLP) for launching spacecraft using electromagnetic propulsion, the satellite launch pad comprising:
- a primary solenoid magnetic accelerator surrounding the launch platform and configured to generate a magnetic field to propel a spacecraft;
- a paramagnetic sheet affixed around the spacecraft, which becomes magnetized upon entering the magnetic field of the primary solenoid, thereby augmenting the magnetic thrust applied to the spacecraft.
2) The satellite launch pad as claimed in claim 1, wherein launch pad further comprising a recoil thruster system designed to stabilize the launch pad by maintaining dynamic equilibrium during the launch phase.
3) The satellite launch pad as claimed in claim 1, wherein the electromagnetic propulsion system is powered by solar energy collected from solar panels on the launch platform, thereby reducing the need for chemical fuels.
4) The satellite launch pad as claimed in claim 1, wherein the spacecraft includes a secondary solenoid in its upper stage, configured to produce a reverse magnetic field, facilitating additional propulsion during the ascent phase.

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