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WO2009095929A1 - Dispositif pour déplacer les activités scientifiques d’une planète à une autre - Google Patents

Dispositif pour déplacer les activités scientifiques d’une planète à une autre Download PDF

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Publication number
WO2009095929A1
WO2009095929A1 PCT/IN2008/000233 IN2008000233W WO2009095929A1 WO 2009095929 A1 WO2009095929 A1 WO 2009095929A1 IN 2008000233 W IN2008000233 W IN 2008000233W WO 2009095929 A1 WO2009095929 A1 WO 2009095929A1
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WO
WIPO (PCT)
Prior art keywords
planet
usv
shift
another
activities
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/IN2008/000233
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English (en)
Other versions
WO2009095929A8 (fr
Inventor
Rushi Rakeshbhai Ghadawala
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of WO2009095929A1 publication Critical patent/WO2009095929A1/fr
Publication of WO2009095929A8 publication Critical patent/WO2009095929A8/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B64G1/105—Space science
    • B64G1/1064—Space science specifically adapted for interplanetary, solar or interstellar exploration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories
    • B64G1/2427—Transfer orbits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion
    • B64G1/413—Ion or plasma engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/401—Liquid propellant rocket engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/403—Solid propellant rocket engines

Definitions

  • This invention relates to the field of aerospace and aeronautics, more particular to the device to shift the scientific activities from one planet to another with the help of an Unnamed Space Vehicle (USV) using solar-ion propulsion system.
  • USV Unnamed Space Vehicle
  • Satellite is an object which has been placed into orbit by human endeavor for the different space depended application such objects are sometimes called artificial satellite to distinguish natural satellite such as moon. Whenever the mission of the satellite is accomplished, it stops functioning and keeps moving around the earth in its own orbit becoming nothing more than space garbage and leaving lesser room for the new ones. Therefore it becomes imperative that this "retired" satellite is brought back to earth with the help of space shuttles.
  • the two most common existing methods of obtaining de-orbiting observations or de-orbiting data are an instrument launched with a sounding rocket and an instrument on board a small satellite
  • the sounding rocket launch can generate high vibration and thermal environments. Accordingly the shock and vibration loads which a sounding rocket subjects a small payload (instrument) are high. Therefore, it is advantageous to provide a device whose payload design load factors are much lower than can typically be realized with a sounding rocket. Similarly it would be advantageous to provide an instrument package whereby the shock and vibration levels that need to be withstood are reduced as compared to a sounding rocket. Further, it would be also advantageous to provide a device which has more flexibility in the design of the payload; which can be launched at any convenient time with respect to desired observations; and whose observation time for obtaining information can be extended for several days. Still further it would be advantageous to provide an instrument package that can use generally available components.
  • Another existing method of orbit transferring techniques includes a spacecraft launched into an initial orbit that differs from the final orbit.
  • the launch vehicle however doesn't have sufficient capability to place the spacecraft into its mission orbit.
  • the spacecraft must be transferred to the mission orbit by using a spacecraft on-board propulsion system.
  • the high thrust propulsion system comprises a Liquid Apogee Engine (LAE) that burns a mixture of hydrazine and oxidizers to generate a thrust.
  • LAE Liquid Apogee Engine
  • High efficiency low thrust thrusters are fired for a period of several weeks to several months for transferring to the mission orbit.
  • orbit transfer alternative strategies are possible where the thrusters are fired for only a portion of each orbit where firing is most efficient. This is referred to as an on/off firing strategy.
  • Large thrust force can be obtained by generating a magnetic field about a positive ion accelerator which is disposed piercing through an aircraft space in the advancing direction, so that thrust force may be obtained by absorbing and injecting ions.
  • electrical attraction among a space having positive charge in the lower section of an ion propulsion engine, a space having negative charge in the upper section of the ion propulsion engine and the aircraft body may produce a large thrust force to provide a system for transferring an artificial satellite from a first orbit to a second orbit with a transfer stage enabled to be restarted and operate at low temperature.
  • the present invention Multi-crystalline solar panels, Orbit Maneuver System Engines and Xenon Ion Propulsion System where solar electric propulsion takes advantage of magnetism and electricity to push a spacecraft through space economically.
  • Xenon cylinders supplying the required fuel, there will be more room for scientific instruments on board.
  • a satellite launched into an orbit which approaches the earth's surface closer than 200 km will not circulate for long.
  • the air drag is sufficient to cause the orbit to spiral in quite quickly to the dense lower atmosphere in which the frictional heating soon evaporates the satellite. It is still necessary to use vertical sounding rockets in spite of their limitations.
  • the main object of the present invention is to shift a satellite orbit from one planet to another with the help of an Unmanned Space Vehicle (USV).
  • USV Unmanned Space Vehicle
  • the basic requirements to de-orbiting satellites are flight testing of electric/ion population and other deep-space technologies while performing scientific observations of the planet.
  • FIG. 2 the schematic diagram of the Xenon Ion Propulsion
  • the present invention device is a solar powered USV that will be having ion propulsion system along with solar propulsion system.
  • the USV will be placed in rocket boosters and with the help of rocket boosters, it will be externally launched like a space shuttle to enable it to go beyond the atmospheric limit of the earth with sufficient escape velocity.
  • xenon cylinders will be attached to the USV in the power unit 4 for providing ion propulsion for furthering the mission, with the help of ion propulsion system the USV will be attached to the satellite which is revolving in the orbit of the earth.
  • the satellite which is attached to the USV with the help of robotic arm in the payload unit 2 will be de-orbited with the xenon engines of ion propulsion system and will be shifted to other orbit of another planet/satellite.
  • Electricity generated by solar panels made from multi-crystalline solar panels which is shown in Fig. 1, of the USV will be stored in the USV to help the mission or operational requirements.
  • Ion propulsion is a technology that involves ionizing gas to propel the spacecraft. Instead of a spacecraft being propelled with standard chemicals, xenon gas (which is similar to neon or helium, but heavier) is electrical charged or ionized. Then it is electrically accelerated at a speed of about 30 km/s. When xenon ions are exhausted at such high speed; they push the spacecraft in the opposite direction.
  • xenon gas which is similar to neon or helium, but heavier
  • Fig. 2 shows the xenon-ion propulsion system
  • xenon atoms are injected into an ionization chamber and ionized by electron bombardment. Then the propellant is electrostatically accelerated through a series of biased grids.
  • Ions ejected by the XIPS, travel in a stream at a speed of 30 km/s, nearly 10 times that of a conventional chemical thruster.
  • the high efficiency of the system leads to a reduction in propellant mass of upto 90% for a satellite which is designed for 12-15 years operation. Less propellant translates to a reduced launch cost, a bigger payload or a larger satellite lifetime or any combination of these.
  • attitude disturbances during thruster operations are reduced simplifying the station keeping task.
  • attitude disturbances during thruster operations are reduced simplifying the station keeping task.
  • force from an ion engine resulting in acceleration in small overtime, it can still enable the build up of a high velocity, making this type of propulsion also helpful for interplanetary probes.
  • ion propulsion In circumstances where ion propulsion is appropriate, it can push a spacecraft upto about 10 times as fast as chemical propulsion.
  • the ion propulsion system although highly efficient and very gentle in its thrust, can not be used for any application in which a rapid acceleration is required. Ion propulsion on a probe gradually imparts input velocity of about 3.6 km/s to the spacecraft.
  • the probe If the probe carries a larger solar array, it certainly would have a slightly higher acceleration and if it carries more xenon propellant also, it can reach a much higher final velocity by simply thrusting longer.
  • Solar electric propulsion takes advantage of magnetism and electricity to push a spacecraft through space. Electricity, generated by the USVs solar panels, gives a- positive electrical charge to atoms inside the chamber. They are pulled by magnetism towards the back of the ship and then pushed by magnetic repulsion out of the ship.
  • the present invention is economical and efficient planetary observation system.
  • the present invention is not limited to change the orbit of a satellite from one planet to another but also eliminates the need for sending land rovers or extra probes for any mission of observation and data collection of any planet.
  • xenon cylinders supplying the required fuel, there will be more room for scientific instruments of board.
  • technology will ensure more compact instrument, resulting in the overall reduction of the size and mass of the spacecraft and thereby further increasing its efficiency.
  • Solar-electric propulsion would make such a mission possible because an ion engine can run almost continuously and outperform any chemical rocket for such long flights.
  • the present invention will thus facilitate to shift scientific analysis activities to other planets.
  • the invention is economical and efficient planetary observation system to change the orbit of a satellite from one planet to another and eliminate the need for sending land rovers or extra space probes for any mission or observation and data collection of any planet.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)
  • Electrostatic Separation (AREA)

Abstract

La présente invention concerne un dispositif pour déplacer les activités scientifiques d'une planète à une autre, lequel dispositif touche au domaine aérospatial et aéronautique. L'invention concerne plus particulièrement un dispositif pour déplacer les activités scientifiques d'une planète à une autre à l'aide d'un véhicule spatial sans pilote (USV) qui utilise un système de propulsion ionique solaire. Le dispositif est constitué d'un véhicule spatial sans pilote (USV) solaire, d'un système de propulsion électromagnétique solaire et de cylindres de xénon, le système de propulsion électromagnétique solaire du USV unique étant destiné à obtenir une énergie plus importante grâce à l'utilisation d'une source perpétuelle d'énergie. Les cylindres de xénon sont fixés à la chambre de décharge du USV dans l'unité de puissance (4) pour fournir une propulsion ionique.
PCT/IN2008/000233 2008-01-28 2008-04-08 Dispositif pour déplacer les activités scientifiques d’une planète à une autre Ceased WO2009095929A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IN187/MUM/2008 2008-01-28
IN187MU2008 2008-01-28

Publications (2)

Publication Number Publication Date
WO2009095929A1 true WO2009095929A1 (fr) 2009-08-06
WO2009095929A8 WO2009095929A8 (fr) 2010-01-14

Family

ID=40912321

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IN2008/000233 Ceased WO2009095929A1 (fr) 2008-01-28 2008-04-08 Dispositif pour déplacer les activités scientifiques d’une planète à une autre

Country Status (1)

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WO (1) WO2009095929A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190104965A (ko) * 2019-09-02 2019-09-11 한국과학기술원 우주물체의 궤도 수명 및 생존성 예측 방법 및 장치

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0780295B1 (fr) * 1995-12-22 2002-10-02 Hughes Electronics Corporation Agencement de charge utile modulaire
US20040164205A1 (en) * 2003-02-21 2004-08-26 The Boeing Company Deployable spacecraft mount for electric propulsion
US20040245407A1 (en) * 2001-07-30 2004-12-09 D'ausilio Robert F. In orbit space transportation & recovery system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0780295B1 (fr) * 1995-12-22 2002-10-02 Hughes Electronics Corporation Agencement de charge utile modulaire
US20040245407A1 (en) * 2001-07-30 2004-12-09 D'ausilio Robert F. In orbit space transportation & recovery system
US20040164205A1 (en) * 2003-02-21 2004-08-26 The Boeing Company Deployable spacecraft mount for electric propulsion

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190104965A (ko) * 2019-09-02 2019-09-11 한국과학기술원 우주물체의 궤도 수명 및 생존성 예측 방법 및 장치
KR102049504B1 (ko) 2019-09-02 2019-11-28 한국과학기술원 우주물체의 궤도 수명 및 생존성 예측 방법 및 장치

Also Published As

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