FIELD OF INVENTION

[001] The present invention is related to aerospace engineering. Particularly, the present invention related to movable space station. The present invention is also related to a space and serves to stay astronauts. The invention is relates to space engineering. More particularly, the present invention is related to spacecraft living compartments. The invention is also related to control of space craft or spaceship, and more particularly to systems and methods for controlling the orientation of spaceship. More particularly, the present invention related to a spaceship for the space travel system.

BACKGROUND & PRIOR ART

[002] As define by the NASA the spaceship“A spaceship is a vehicle designed to travel to and orbit in space. The payload, or what is carried into space - a telescope, sensor device, or people - is contained within the launch vehicle which lifts the payload into space. Today, launch vehicles have several stages that drop off during the launch, but in the future, the launch vehicle or spaceship will have only one stage.

[003] Most Earth-orbiting spacecraft look similar to one another because they all need to communicate with Earth, make power, and carry instruments. Countries all over the world work together to build these spacecraft and study the data they send back. Earth is very complex, so using a view point from space, we are measuring many types of things, including clouds, the amount of sun reaching Earth, the temperature of the land and the ocean, sea surface height, and ocean color. Collecting information over the oceans is especially important. Some of related previous works are listed herewith. [004] The design of the spacecraft and spaceship is crucial. A number of the parameters are need to be considered while design a spacecraft. The lot of works for design spaceship has done. Some of the works are listed herewith:

[005] RU2445241C2 present Roll Space house, characterized in that it consists of a cylinder, wherein the lift channels are around which is rotatable arranged inside the cylinder rotary volumetric room.

[006] RU2421381C2 represent a Space mobile home, characterized in that it has an elevator shaft with a wheel in the rear portion, the removable volume rooms and helical wheel.

[007] RU2660180C1 presents space equipment. Unit for landing and evacuation of astronauts from a spacecraft contains a tower with elevators permanently installed on a launching structure, protective structure with inclined lift, air conditioning, braking device, security door blocks, crew training and reception areas for evacuees, inclined sealed metal gallery with stairs, evacuation chute and fork-rail way for delivery by the inclined crew lift. Tumable platform-cabin of cleanliness with a soft inflatable adapter for landing a crew in a spaceship is fixed on the tower. Lower part of the gallery is connected to a protective structure, the upper one is connected to a cleaning platform-cabin. Evacuation chute is made of interconnected sections of troughs-slits and grooves-roller tables.

[008] US6332592B1 presents a method of velocity precision pointing of spin- stabilized spacecraft or rockets is disclosed. This method involves softening the ignition transient of the ramp up phase of thrust, which may be achieved by modification of the solid propellant, applying a coating of slow burning material upon the solid propellant varying the grain density of the solid propellant over an exposed surface area or as a function of propellant depth, where depth is defined in the direction of the bum surface area regression, pre-pressurizing the combustion chamber.

[009] CN108664035A present a multi-actuator aircraft distribution control method. The multi-actuator aircraft distribution control method is operated on an aircraft with a calculation cycle of T, wherein the executing mechanism of the aircraft comprises a flywheel and a thruster, and the method comprises the following steps of: acquiring the angular momentum p required by the aircraft; if the norm of/T is less than the moment threshold value F, the flywheel is selected as an executing mechanism, otherwise, the thruster is selected as an executing mechanism; distributing the angular momentum p according to the angular momentum output in the time of the flywheel T; and distributing the angular momentum p according to the output torque vector of the thruster. The invention also discloses a multi-actuator aircraft distribution control system. The multi actuator aircraft distribution control system comprises an angular momentum command module, an executing mechanism selection module and a control command output module. The technical scheme solves the optimization problem of the continuous distribution control of the multi-actuator of the spacecraft; the control of the flywheel can save energy consumption and balance the total angular momentum; the control efficiency can be increased and the fuel consumption can be reduced for the air-jet control.

[0010] CN106125750B present a large-scale assembly attitude control method based on internal model principle. The weight of a large assembly spacecraft reaches a level of hundreds of tons to thousands of tons. A mode employed by the large assembly spacecraft is different from a mode that a common spacecraft employs a magnetic moment device for unloading. Moreover, there is no magnetic moment device matched with the interference of the large-scale assembly in engineering. The system modeling of the large-scale assembly comprises the steps: dynamics modeling of posture, dynamics modeling of an angular momentum of an executing mechanism, and detailed modeling of environment moments which comprises gravity gradient moment and an aerodynamic moment. The method gives consideration to a condition that the frequency components of the gravity gradient and aerodynamic moments are related with the angular velocity of a rail,

[0011] CN104290925B present an angular momentum control method of a spacecraft in an inertial system. The method is characterized in that a three-axis stabile control is performed in the inertial system, and the feedback design is performed based on the angular momentum and three-axis posture angle information of a performing mechanism to obtain a feedback controller. According to the method, that the gravity gradient torque is to be more than the pneumatic torque is removed

[0012] CN103231810B present a maneuvering unloading pitch axis angular momentum method by satellite pitching axis attitude. The maneuvering unloading the pitch axis angular momentum method by the satellite pitching axis attitude comprises step one, measuring and confirming the satellite pitch axis angular momentum hun-y needs to be unloaded; step two, confirming gravity gradient torque the satellite bears according to satellite rotational inertia; step three, estimating time tend needed by the maneuvering thetam of the satellite pitch axis and angular momentum humanu which is accumulated by the gravity gradient torque on the pitch axis in the maneuvering process.

[0013] US20080315039A1 present a spacecraft attitude controller balances external torques, including those resulting from gravity gradient and those resulting from other orbital disturbances, to achieve a comparatively stable, neutral attitude or orientation. Torque is balanced by selecting spacecraft attitude Euler angles and angular rates such that orbital disturbances and cross-coupling inertial effects are cancelled by the external forces, based on Euler's equation. A spacecraft attitude torque-balancing controller and related method compares spacecraft attitude angles and angular rates with an orbit reference frame, and provides instructions to conventional momentum management and propulsion controls to responsively adjust the spacecraft attitude and angular rates. This feedback loop drives to zero (or an acceptably small quantity) the rate of change of the difference between spacecraft and reference attitude and angular rates, thus minimizing the net accelerations on the vehicle. [0014] US3582019A present a rotor for three-axis stabilization of a passively damped gravity-gradient spacecraft, and more particularly to a rotor for yaw stabilization, yaw-roll decoupling, and bbration damping, when used in combination with an energy dissipator, for example, a ball-in-ball damper. The angular momentum vector of the rotor is oriented along the preferred pitch axis of the spacecraft. The motor is utilized to spin the rotor and produce a yaw controlling reaction torque of the spacecraft and, thereby, to overcome disturbing torques occasioned by thermal bending forces in gravity-gradient stabilizing booms, radiation pressure, residual magnetization and aerodynamic forces.

[0015] Groupings of alternative elements or embodiments of the invention disclosed herein are not to be construed as limitations. Each group member can be referred to and claimed individually or in any combination with other members of the group or other elements found herein. One or more members of a group can be included in, or deleted from, a group for reasons of convenience and/or patentability. When any such inclusion or deletion occurs, the specification is herein deemed to contain the group as modified thus fulfilling the written description of all Markush groups used in the appended claims.

[0016] As used in the description herein and throughout the claims that follow, the meaning of“a,”“an,” and“the” includes plural reference unless the context clearly dictates otherwise. Also, as used in the description herein, the meaning of “in” includes“in” and“on” unless the context clearly dictates otherwise.

[0017] The recitation of ranges of values herein is merely intended to serve as a shorthand method of referring individually to each separate value falling within the range. Unless otherwise indicated herein, each individual value is incorporated into the specification as if it were individually recited herein. All methods described herein can be performed in any suitable order unless otherwise indicated herein or otherwise clearly contradicted by context.

[0018] The use of any and all examples, or exemplary language (e.g.“such as”) provided with respect to certain embodiments herein is intended merely to better illuminate the invention and does not pose a limitation on the scope of the invention otherwise claimed. No language in the specification should be construed as indicating any non-claimed element essential to the practice of the invention.

[0019] The above information disclosed in this Background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art.

OBJECTIVE OF THE INVENTION

[0020] The principle objective of the present invention is to present a spaceship.

More specially, the objective of the present invention is to present a multipurpose space house /spaceship for space travel system. Another objective of the present invention is to present a space house or spaceship based on the principle of the spin angular momentum. Further objective of the present invention is to present a three chamber type spaceship with continues solar power.

SUMMARY

[0021] A spaceship for the space travel system, comprising :a first circular chamber, wherein the first circular chamber in a circular motion and configured to maintain gravity which is comfortable to the human walk ; a second circular chamber, the second circular chamber in a rest position and configured to maintain gravity which is approximate zero, wherein The first circular chamber and the second circular chamber that rotates in opposite direction of each other and create centripetal acceleration which is approximately equal to the gravitational acceleration of the earth; plurality of motors, wherein the Plurality of motors are used to rotate the spaceship, the first circular chamber & the second circular chamber; and at least one rest chamber, wherein the rest chamber is configured to remain at a rest position when the first circular chamber and the second circular chamber are in motion and configured between the first circular chamber and the second circular chamber. BRIEF DESCRIPTION OF DRAWINGS

[0022] Further clarify various aspects of some example embodiments of the present invention, a more particular description of the invention will be rendered by reference to specific embodiments thereof which are illustrated in the appended drawings. It is appreciated that these drawings depict only illustrated embodiments of the invention and are therefore not to be considered limiting of its scope. The invention will be described and explained with additional specificity and detail through the use of the accompanying drawings.

[0023] In order that the advantages of the present invention will be easily understood, a detail description of the invention is discussed below in conjunction with the appended drawings, which, however, should not be considered to limit the scope of the invention to the accompanying drawings, in which:

[0024] Figure 1 shows the top view of the first circular chamber and therefore the top view of the spaceship.

[0025] Figure 2 shows representation to support the mathematical derivation according to the present invention.

[0026] Figure 3 shows a rest chamber of the spaceship.

[0027] Figure 4 shows exemplary representation of the space ship according to present invention , including structure, connection and configuration of the first circular chamber, the rest chamber and the second circular.

[0028] Figure 5 represent the drawings to describe the mathematics basis of the spaceship of the space travel system according to the present invention. DETAIL DESCRIPTION

[0029] The present disclosure presents a spaceship for the space travel system.

The Space ship comprises a first circular chamber, a second circular chamber, plurality of motors, at least one rest chamber, and a plurality of solar panels. The first circular chamber is in circular motion and configured to maintain gravity which is comfortable to the human walk.

[0030] The second circular chamber is in a rest position and configured to maintain gravity which is approximate zero, wherein the first circular chamber and the second circular chamber that rotates in opposite direction of each other and create centripetal acceleration which is approximately equal to the gravitational acceleration of the earth. The Plurality of motors are used to rotate the spaceship, the first circular chamber & the second circular chamber; and At least one rest chamber is configured to remain at a rest position when the first circular chamber and the second circular chamber are in motion and it is configured between the first circular chamber and the second circular chamber.

[0031] The pluralities of solar panels are used as power source of the spaceship.

The present spaceship for the space travel system is configured in such a manner that the net spin angular momentum of the whole spaceship is zero. The plurality of the motors are attached together and placed in at least one rest chamber.

[0032] The pluralities of solar panels are configured in such positions at the first circular chamber & the second circular chamber in such a manner to get maximum power from sunlight. The present spaceship is constructed in such a manner that locomotion of the humans from the one chamber to another chamber is possible.

[0033] Figure 1 shows the top view of the first circular chamber and therefore the top view of the spaceship.

[0034] For the exemplary purposes, the outer radius of the first circular chamber is 100 Meters and Inner radius is 94 Meters. The Outer radius from point A to B is indicated in the Figure 1. Therefore the height of the first circular chamber is designed to 6 Meters, and length of the from the outer surface to inner surface of the first circular chamber is configured to 8 Meters. So total outer surface area of this exemplary first circular chamber of the spaceship is around 3771 (6 * 22/7 * 2* 100) meter square and inner surface area of around 4727 (2*22/7*94*8) meter square. The total volume of first circular chamber will become (22/7*6 ^L 2*8) meter cube is equal to 1,810.285714285 meter cube.

[0035] The plurality of metal rods (2) are connected around to the module of same length and this metal rod edges are connected together with the solar panels ( 3,4,5 6) around the complete module for all metal rods .

[0036] Each solar panel for example solar panel (3 ) has both faces, means two solar panels are connected opposite faces together to form position of solar panel (3). Similarly solar panel (4), solar panel (5) and solar panel (6) are designed and configured in such that all the solar panels are perpendicular to each other. So as a result of these arrangements of the solar panels (3, 4, 5, 6) the efficiency of converting solar energy to electrical energy is increases from all sides of the chamber. When the First circular chamber moves in the circular motion then this solar panels also move in circular motion.

[0037] Figure 2 shows representation to support the mathematical derivation according to the present invention. These figure describes the mathematical condition of the angular speed by the above conditions when the First circular chamber /module moves with angular velocity of 0.3 rad/sec then the First circular chamber/ module simulates earth’s acceleration due to gravity (on surface) like a centripetal force.

[0038] Figure 3 shows a rest chamber of the spaceship. The figure 3 shows top view rest chamber. One end (8) of the rest chamber is one of the ends of this module having dimensions depend on the size of the module. The two large size solar panels (12) - is attached together facing opposite direction and similarly this type arrangement of the solar panels are placed on four sides of this module.

[0039] The connecter (13,10) is placed to connect and holds the solar panels and therefore the module. This rest chamber is divided in the two parts, a first part (21) of the rest chamber and a second part (22) of the rest chamber shown in Figure 4 in detail. The surround area (9) of the first part and the second part of the rest chamber is shown in Figure 3. This surrounding area is empty and anybody can move through this from one end of module (8) to remaining three sides of the rest chamber through these module tubes. The orthogonal view and connection from the first chamber , the rest chamber and a second circular chamber by the connecting rods (20) shown in the Figure 4.

[0040] Figure 4 shows structure, connection and configuration of the first circular chamber, the rest chamber and the second circular. The First circular chamber and the second circular chamber are similar to each other in size and configuration. These chambers are connected to each other by connecting rods (20). The four connecting rods (20) are connected from center of the first circular chamber to center of the rest chamber through the upper part ( 21) of the rest chamber and also the same with the second circular chamber to chamber the lower part (22) of the rest chamber .

[0041] The connecting rods (20) which are connected to the upper sub chamber (21) and the lower sub chamber (22) of the rest chamber are free to rotate clock and anti-clock wise direction with respective to the rest chamber. Whereas the connecting rods are not free to rotate inside the first circular chamber and the second circular chamber. But when the connecting rods in motion those rotate the first circular chamber and the second circular chamber . The connecting rods through the first circular chamber are directly connected to plurality of large size motor placed inside the upper sub chamber (21) of the rest chamber .

[0042] The connecting rods through direction of the second circular chamber are similarly connected to the plurality of motor placed inside of the lower sub chamber (22) of the rest chamber.

[0043] Now these plurality of motors placed at the upper sub chamber (21) and the lower sub chamber (22) are in rest chamber facing opposite direction and back side of this motors are connected together to form a cylinder having four connecting rods coming from each side of cylinder or central duct (23).

[0044] A connecting rod (15) is the rod connected to the outer surface (16) of the first circular chamber and a set of solar panels (14) are connected between at least two connecting rods. The first circular chamber is connected to the rest chamber through the connecting means (18) . The connecting rods from the connecting mean (18) is connected to the rest chamber through the connecting means(19)

[0045] The plurality of the solar panels (12) are placed in the position represented as a triangle shape (17) , these solar panels are connected to the rest chamber .

[0046] The second circular chamber has an outer surface (25). The second circular chamber has a connection (26) of the connecting rods with

[0047] The solar power from the plurality of the solar panels placed at the different positions of the first circular chamber, the second circular chamber and the rest chamber are utilized by the plurality of large size motors. These motors are configured to rotate in opposite direction of each other . The angular velocity of first circular chamber, the second circular chamber depends on the speed with which the motors rotate.

[0048] Figure 5 represent the drawings to describe the mathematics basis of the spaceship of the space travel system according to the present invention.

[0049] For the exemplary purpose, if the first circular chamber is rotating in the clock wise direction and the second circular chamber is rotating in the anti clockwise direction . Then their respective spin angular momentums are in opposite direction and they cancel out each other therefore net spin angular momentum of the entire spaceship is zero so the center chamber will stay at rest with respective to the first circular chamber and the second circular chamber . So now on the surface (16,25) of first circular chamber has centripetal acceleration equal to the acceleration of earth , and a human can stand on this surface whereas in rest chamber human can floats due to zero gravity. One can go from one chamber to another by controlling the angular speed of plurality of the motors and using the column duct for transporting inside the spaceship.

[0050] Mathematical calculation for the example according to present invention

[0051] The matematical calculation according to figure 2.

[0052] Mathematical calculation according to Figure 2 is as follows:.