WO2002030748A1 - Systeme et procede permettant de modifier et de controler les trajectoires d'engins naviguant dans l'espace ou le ciel et de modifier les trajectoires de corps inertes qui se deplacent dans l'espace - Google Patents

Systeme et procede permettant de modifier et de controler les trajectoires d'engins naviguant dans l'espace ou le ciel et de modifier les trajectoires de corps inertes qui se deplacent dans l'espace Download PDF

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Publication number
WO2002030748A1
WO2002030748A1 PCT/ES2001/000376 ES0100376W WO0230748A1 WO 2002030748 A1 WO2002030748 A1 WO 2002030748A1 ES 0100376 W ES0100376 W ES 0100376W WO 0230748 A1 WO0230748 A1 WO 0230748A1
Authority
WO
WIPO (PCT)
Prior art keywords
trajectory
angular momentum
modify
space
moment
Prior art date
Application number
PCT/ES2001/000376
Other languages
English (en)
Spanish (es)
Inventor
Manuel Dorado Gonzalez
Jose Luis Perez Fernandez
Miguel Morales Furio
Original Assignee
Cenita, S.A.
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 Cenita, S.A. filed Critical Cenita, S.A.
Priority to AU2001293875A priority Critical patent/AU2001293875A1/en
Publication of WO2002030748A1 publication Critical patent/WO2002030748A1/fr

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Classifications

    • 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
    • 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
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • B64G1/281—Spin-stabilised spacecraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • 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
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect

Definitions

  • the present invention is related to a technique that allows to modify in a controlled way: (1) the trajectory of mills and, especially, of satellites or other space vehicles, directed, remote-controlled or autonomous, that move through space, ( 2) the trajectory of inert bodies that travel through space, and (3) the trajectory of rockets, missiles or other types of directed or remote-controlled devices that execute an aerial trajectory from the moment they launch until they reach their objective. , regardless of where their locations are located.
  • the field of application extends to: (1) the sectors of activity in which the development of devices is of interest in order to control trajectories of any type of space and / or aerial devices, to direct them, by direct or remote control , precisely to a certain place; (2) the sectors of activity whose interest is the study of inert bodies that travel through space (meteorites, asteroids, comets, 7) and the possibilities of acting on them to modify their trajectories.
  • the methods to modify trajectories of mills that move through space are based on
  • SUBSTITUTE SHEET (RULE 26) san in the use of propellers.
  • aerodynamic devices ailerons
  • adjustable propellers are used to modify trajectories of mills that move through the atmosphere.
  • the present invention implements a technique that allows to modify in a controlled way: (1) the trajectories of space devices such as satellites or other ships that move through space, (2) the trajectory of inert bodies that move through space, and (3) the trajectory of rockets, missiles or other types of directed or remote-controlled devices that execute an air trajectory from the moment it launches until it reaches its target, regardless of where their locations are located.
  • the invention aims to modify and control the trajectory of a space ingenuity, particularly of a satellite or a spacecraft that travels through space, whether manned, remote-controlled or autonomous. For this, it will be provided with:
  • first means capable of providing angular moments to the mill in the direction of the axis of displacement and in the two directions perpendicular to the previous one, and of
  • the means required for the implementation of the method according to the invention may be any currently existing or being developed.
  • SUBSTITUTE SHEET RULE 26 in the future.
  • mechanical devices can be incorporated, such as inertial flyers driven by a motor; or electromechanical devices such as rigid bulls within which mercury is rotated at the desired speed by an external electromagnetic field.
  • Propellers based on any type of technology can be used to provide pairs of forces perpendicular to the direction of travel (second means).
  • the technique to modify the trajectory of the space ingenuity is the following: when it is desired to modify the trajectory in which said ingenuity moves, said first means will be activated that provide the appropriate angular momentum in the direction of the trajectory that is to be changed and, a once the angular momentum is stabilized, said second means will be activated simultaneously, which will provide a pair of forces with component perpendicular to the angular momentum.
  • the trajectory of the ingenuity or spacecraft will change at the moment in which said first and said second means act simultaneously and until the operation of said second means is deactivated. From that moment, the ship will follow a rectilinear path defined by the direction of its speed.
  • the radius of the variation of the trajectory can be controlled at every moment acting on three parameters, namely: the speed of movement of the ship, the angular momentum and the torque.
  • the objective of the system and method according to the present invention is to modify the trajectory of an inert body that travels through space.
  • SUBSTITUTE SHEET (RULE 26)
  • the technique to modify the trajectory of said body consists in taking advantage of its natural rotation around one or more axes, providing, when it is desired to modify the trajectory of the body, a pair of forces with component perpendicular to the angular momentum.
  • the trajectory of the body will change the moment the torque pair acts and until it is deactivated. From that moment, the body will follow a rectilinear path defined by the direction of its speed.
  • the radius of the variation of the trajectory will be determined at each moment by the speed of movement of the body, the angular momentum of the body and the torque.
  • the object of the invention is to modify and control the trajectory of rockets, missiles or other types of directed or remote control devices that execute an aerial path from the moment it is launched until they reach their objective.
  • they will be provided with: (1) first means capable of providing angular moments to the ship in the direction of the axis that determines the direction of travel, and
  • second means capable of providing a pair of forces of different intensity and duration, the result of which is perpendicular to the direction of travel.
  • the means required for the practical execution of this third preferred embodiment may be any existing at present or developed in the future.
  • mechanical devices can be incorporated, such as a flywheel controlled by a motor, or part of the cylindrical fuselage can be rotated controlled by an engine; too
  • Electromechanical devices can be used, such as rigid bulls within which mercury is rotated at the desired speed through an external electromagnetic field.
  • propellants based on any type of technology
  • aerodynamic mechanisms ailerons or both can be used simultaneously.
  • the technique to modify the trajectory of the mill it is the following: when it is desired to modify the trajectory of the mill (rocket or missile) in air travel, said first means will be activated to provide the appropriate angular momentum in the direction of the path that it is desired to change and, once the angular momentum is stabilized, said second means will be activated simultaneously to provide a pair of forces with component perpendicular to the angular momentum.
  • the trajectory of the mill will change from the moment in which said first and second means act simultaneously and until the operation of said second means is deactivated. From that moment, the ingenuity will follow a rectilinear path defined by the direction of its velocity.
  • the radius of the variation of the trajectory can be controlled at every moment acting on three parameters: the speed of movement of the ship, the angular momentum and the pair of forces.
  • SUBSTITUTE SHEET fig. 1 schematically presents a satellite or spacecraft that incorporates the system according to the invention
  • fig. 2 represents, chemically, a celestial body that travels through space and to which the system and method according to the invention are applicable
  • fig. 3 is a schematic illustration of a vehicle; such as a missile or rocket, which incorporates the system and method according to the invention.
  • a parallelepiped marked in the figure with the reference number 11, which represents the space ingenuity that incorporates the object of the present invention, in this case , a ship or satellite.
  • the discs 12 (first means) provide the angular momentum in the desired direction.
  • the thrusters 13 (second means), located in pairs and symmetrically on all the faces of the parallelepiped, provide the pairs of forces.
  • the technique for controlling the trajectory of a spacecraft consists in activating said first means to provide an angular momentum in the direction of travel of the satellite or ship by rotating, in this case, one, two or the three discs 12, as appropriate, each with an adequate speed.
  • said second means in the present case activated the thrusters 13, the force pairs will be provided, simultaneously operating two of them located on parallel faces and not facing each other, in
  • the technique to modify the trajectory of said meteorite or other inert body that travels through space in one direction 21, consists in providing a pair of forces 23 perpendicular to the angular momentum 22 which, by its nature, will have the Body.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

L'invention concerne un système et un procédé permettant de modifier et de contrôler les trajectoires d'engins naviguant dans l'espace ou le ciel et de modifier la trajectoire de corps inertes qui se déplacent dans l'espace. Selon l'invention, on peut modifier de façon contrôlée la trajectoire d'engins spatiaux, commandés, commandés à distance ou autonomes, qui se déplacent dans l'espace ainsi que la trajectoire de fusées, de missiles ou d'autres types de dispositifs commandés ou commandés à distance qui empruntent une trajectoire aérienne, entre l'instant de leur lancement et l'instant où ils atteignent leur objectif, quelle que soit leur position. Ce système consiste à fournir à l'objet un moment angulaire ou de profiter de son propre moment angulaire pour produire, moyennant application d'une paire de forces perpendiculaires audit moment angulaire, un changement de trajectoire dont le rayon sera déterminé par le rapport entre les intensités du moment angulaire et de la paire de forces.
PCT/ES2001/000376 2000-10-10 2001-10-09 Systeme et procede permettant de modifier et de controler les trajectoires d'engins naviguant dans l'espace ou le ciel et de modifier les trajectoires de corps inertes qui se deplacent dans l'espace WO2002030748A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2001293875A AU2001293875A1 (en) 2000-10-10 2001-10-09 System and method for modifying and controlling trajectories of spacecrafts during space or air navigation and to modify trajectories of inert bodies moving in space

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ESP200002444 2000-10-10
ES200002444A ES2171355B1 (es) 2000-10-10 2000-10-10 Un sistema y un metodo para modificar y controlar trayectorias de ingenios en navegacion espacial o aerea, y para modificar trayectorias de cuerpos inertes que se desplazan por el espacio.

Publications (1)

Publication Number Publication Date
WO2002030748A1 true WO2002030748A1 (fr) 2002-04-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/ES2001/000376 WO2002030748A1 (fr) 2000-10-10 2001-10-09 Systeme et procede permettant de modifier et de controler les trajectoires d'engins naviguant dans l'espace ou le ciel et de modifier les trajectoires de corps inertes qui se deplacent dans l'espace

Country Status (3)

Country Link
AU (1) AU2001293875A1 (fr)
ES (1) ES2171355B1 (fr)
WO (1) WO2002030748A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2340893A1 (es) * 2007-03-28 2010-06-10 Centro De Investigacion De Rotacion Y Torque Aplicada, S.L. Procedimiento para acelerar cuerpos moviles.
CN106628260A (zh) * 2016-11-17 2017-05-10 上海卫星工程研究所 一种航天器推力器共面双备份的布局设计方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3866025A (en) * 1972-03-17 1975-02-11 Rca Corp Spacecraft attitude control system
US4288051A (en) * 1976-09-18 1981-09-08 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Method and apparatus for controlling a satellite
US5222023A (en) * 1991-04-02 1993-06-22 Space Systems/Loral, Inc. Compensated transition for spacecraft attitude control
US5315158A (en) * 1993-05-17 1994-05-24 Danielson Arnold O Integrated roll control and power supply system and method
US5335179A (en) * 1992-12-24 1994-08-02 General Electric Co. Unified spacecraft attitude control system with pseudo-complementary paired thrusters
EP0937644A2 (fr) * 1998-02-23 1999-08-25 Space Systems/Loral, Inc. Appareil, système et méthode de stabilisation d'axes sur un engin spatial

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3866025A (en) * 1972-03-17 1975-02-11 Rca Corp Spacecraft attitude control system
US4288051A (en) * 1976-09-18 1981-09-08 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Method and apparatus for controlling a satellite
US5222023A (en) * 1991-04-02 1993-06-22 Space Systems/Loral, Inc. Compensated transition for spacecraft attitude control
US5335179A (en) * 1992-12-24 1994-08-02 General Electric Co. Unified spacecraft attitude control system with pseudo-complementary paired thrusters
US5315158A (en) * 1993-05-17 1994-05-24 Danielson Arnold O Integrated roll control and power supply system and method
EP0937644A2 (fr) * 1998-02-23 1999-08-25 Space Systems/Loral, Inc. Appareil, système et méthode de stabilisation d'axes sur un engin spatial

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2340893A1 (es) * 2007-03-28 2010-06-10 Centro De Investigacion De Rotacion Y Torque Aplicada, S.L. Procedimiento para acelerar cuerpos moviles.
CN106628260A (zh) * 2016-11-17 2017-05-10 上海卫星工程研究所 一种航天器推力器共面双备份的布局设计方法
CN106628260B (zh) * 2016-11-17 2018-11-23 上海卫星工程研究所 一种航天器推力器共面双备份的布局设计方法

Also Published As

Publication number Publication date
ES2171355A1 (es) 2002-09-01
AU2001293875A1 (en) 2002-04-22
ES2171355B1 (es) 2003-12-01

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