Field of the invention:

The present invention relates to generation of thrust through electric energy and more particularly, the present invention relates to electrically powered engine for spacecraft or satellite.

Background of the invention

Space propulsion technology can generally be divided into chemical propulsion, electric propulsion and other propulsion technologies such as solar sails, rope propulsion, and the like. At present, most of the spacecraft's main propellers use chemical propulsion.

Chemical propulsion is the use of chemical energy to propel spacecraft into a predetermined space orbit and to achieve on-orbit maneuvering. The most prominent feature of chemical propulsion is the ability to provide high thrust, which has long been the most used propulsion technology in the aerospace industry. The chemical engine is a control execution component that is currently required for long-life three-axis attitude -controlled stable satellites and spacecrafts.

Current, electric propulsion system uses the electrical energy generated by solar panel windsurfing or nuclear reactors to provide energy to the propellant, allowing the propellant to produce jet velocities that are much higher than those produced by conventional chemical thrusters.

However, both chemical propulsion and current electric propulsion need to carry a certain amount of working fluid, which not only occupies the platform weight of the spacecraft, but also greatly increases the launching cost. At the same time, the orbital operating life of the spacecraft depends mainly on the amount of fuel carried, and relies on carrying fuel.

Therefore, there is a need to provide an electrical propulsion system for spacecraft which overcomes above-mentioned drawbacks.

Objects of the invention:

An object of the present invention is to provide eliminate any kind of fuel in spacecraft for generating force and only use electric power for propulsion.

Another object of the present invention is to keep satellite in orbital position much longer than 10 years.

Summary of the invention

Accordingly, the present invention provides a system for propulsion of an object. The object includes the system configured there within. The system comprises an electric motor placed on frame at one end, and a plurality of blades rotatably configured on a shaft of the electric motor. Specifically, each blade of the plurality of blades is configured with a magnetic coil on the tip thereof.

The system further comprises an iron bar positioned on the frame at another end at a predefined distance from the plurality of the blades. This negates the magnetic forces and causes no displacement. Specifically, the magnetic coil is configured to receive power to create magnetism therein when the blade comes in close proximity to the iron bar.

Upon starting the motor in clockwise direction, the force of iron bar is against the direction of rotating blades thus the force of magnet is equilibrated by the force of rotating blades, and as the plurality of blades are rotating in circular motion, its own displacement force is zero thereby providing only force of iron bar which is directional force present which moves the object in a given direction.

Brief description of the Figures

Figure 1 shows a schematic drawing of the system of propulsion of an object, in accordance with the present invention.

Detailed description of the embodiments:

The foregoing objects of the present invention are accomplished and the problems and shortcomings associated with the prior art, techniques and approaches are overcome by the present invention as described below in the preferred embodiments.

The present invention provides an electrical system for propulsion of an object. In an embodiment, the object may a spacecraft and similar crafts which require fuel for propulsion. In preferred embodiment, the system of the present invention ois configured within the object in order to propel the object.

Referring now to figure 1, there is shown a system (100) for propulsion of an object (not shown). In described above, the system (100) is configured within the object in order to propel it within /on a medium such as water or air. For example, if the system (100) is to be used for propelling the spacecraft, the system (100) is configured inside the spacecraft rear location in order to propel the spacecraft without having a requirement of fuel.

The system (100) comprises an electric motor (10) placed on a frame (20) at one end. Specifically, the frame (20) is any solid framework on which motor is placed in such a way that the motor (10) functions without any hassles. In an embodiment, the electric motor (10) is operated by solar power from the solar panel placed over the object such as spacecraft. Specifically, when the system (100) is configured in a spacecraft, the only power available is solar power in abundance. Hence, in the present system, the electrical motor (10) is operated by solar power.

The system (100) further includes a plurality of blades rotatably configured on a shaft of the motor (10). In preferred embodiment, the plurality of blades is three blades (30). However, it may be evident to those skilled in the art to use more than three blades as per requirement.

In an embodiment, the each blade (30) of the plurality of blades is configured with a magnetic coil (30a) on the tip thereof. The magnetic coil (30a) receives power used from the solar panel for creating magnetic field therein.

Further, the system (100) comprises an iron bar (40) positioned on the frame (20) at another end at a predefined distance from the plurality of the blades (30) thereby negating the magnetic forces and causing no displacement. In an embodiment, the distance between the tip of plurality of blade (30) and the iron bar (40) is 1-5 mm. In preferred embodiment, the iron bar (40) includes magnet configured thereon.

During operation, upon starting the motor (10) in clockwise direction, the force of iron bar (40) is against the direction of rotating blades (30) thus the force of magnet in the magnetic coil (30a) is equilibrated by the force of rotating blades (30). As the plurality of blades are rotating in circular motion, its own displacement force is zero thereby providing only force of iron bar which is directional force present which moves the object in a given direction.

In an embodiment, the magnetic coil (30a) of the tip of each blade (30) is configured to receive power from the solar energy when the each blade of the plurality of blades (30) come in close proximity to the iron bar (40) i.e at about 90 degree. This is achieved by use of proximity sensors placed within the magnetic coil. When the proximity sensors comes close to iron bar (40), the switch supplying power to the magnetic coil (30a) gets on which automatically allows the magnetic coil to receive power for creating magnetism in the magnetic coil (30a). This selective magnetism in the magnetic coil (30a) on the tip of blade (30) is required to avoid repulsion of between the iron bar (40) and the magnetic coil (30a) which moves away from 90 degree to 110 degree or more.

In another aspect, the present invention provides a system for propulsion of an object. Specifically, the system is configured within the object to be propelled. Component of this system are similar to components of the system (100) except that this system comprises magnets (50) configured on a tip of each blade of the plurality of blades (30).

During operation, upon starting the motor in anti-clockwise direction, the magnet (50) configured on the tip of the blade attracts the force of magnetic coil configured on the iron bar (40) and rotating force of the electric motor absorb the applied force on the magnet by the magnetic coil and only one force remain of magnetic coil’s which displace the object in one direction.

In an embodiment, the electric motor is operated using a solar power received from the solar panels configured on the spacecraft.

The system (100) helps the spacecraft to remain in orbit for longer periods as compared to conventional method of generating thrust in the spacecraft.

The system of the present invention can be used for spacecraft designed for reaching to the Moon, Mars and any other planet as there is no requirement of fuel in the propulsion system of the present invention. Due to non-requirement of the fuel, the system (100, 200) can generate continuous thrust and can achieve higher speed in the space. Advantages of the invention

1. The propulsion system of the present invention eliminate any kind of fuel in spacecraft for generating force and only use electric power for propulsion.

2. The propulsion system of the present invention keeps satellite in orbital position much longer than 10 years. The foregoing descriptions of specific embodiments of the present invention have been presented for purposes of illustration and description. They are not intended to be exhaustive or to limit the present invention to the precise forms disclosed, and obviously many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the present invention and its practical application, to thereby enable others skilled in the art to best utilize the present invention and various embodiments with various modifications as are suited to the particular use contemplated. It is understood that various omission and substitutions of equivalents are contemplated as circumstance may suggest or render expedient, but such are intended to cover the application or implementation without departing from the scope of the present invention.