WO2002030748A1

WO2002030748A1 - 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

Info

Publication number: WO2002030748A1
Application number: PCT/ES2001/000376
Authority: WO
Inventors: Manuel Dorado Gonzalez; Jose Luis Perez Fernandez; Miguel Morales Furio
Original assignee: Cenita, S.A.
Priority date: 2000-10-10
Filing date: 2001-10-09
Publication date: 2002-04-18
Also published as: AU2001293875A1; ES2171355B1; ES2171355A1

Abstract

The invention relates to a 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. According to the invention, it is possible to controllably modify the trajectory of controlled, remote-controlled or autonomous spacecrafts moving in space; the trajectory of rockets, missiles and other types of controlled or remote-controlled devices executing an air trajectory from the moment of launching until the moment when they reach their target regardless of the location thereof. This technique involves providing an angular moment to the object or making use of its own angular moment with the purpose of changing the trajectory by applying a force couple perpendicular to said angular moment, the radius thereof being determined by the relationship of the intensities of the angular moment and the force couple.

Description

"A system and method to modify and control trajectories of space or air navigation devices, and to modify trajectories of inert bodies that travel through space"

Object of the invention

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, ...) and the possibilities of acting on them to modify their trajectories.

Background of the technique According to the applicant's knowledge, there is no background on this new technique.

At present, the methods to modify trajectories of mills that move through space are based on

SUBSTITUTE SHEET (RULE 26) san in the use of propellers. To modify trajectories of mills that move through the atmosphere, aerodynamic devices (ailerons) and also adjustable propellers are used.

Description of the invention

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.

In a first preferred embodiment, 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:

(1) 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

(2) second means capable of providing the mill with pairs of forces of different intensities and durations of time whose results are perpendicular to the directions defined above.

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. For example: to provide the angular momentum in the direction of travel (first means) 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. In a second preferred embodiment, 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.

According to a third preferred embodiment, 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. For this, 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

(2) 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. For example: to provide angular momentum in the direction of travel (first means) 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

REPLACEMENT JA RULE 26 Electromechanical devices can be used, such as rigid bulls within which mercury is rotated at the desired speed through an external electromagnetic field. To provide pairs of forces perpendicular to the direction of travel (second means), either propellants, based on any type of technology, aerodynamic mechanisms (ailerons) or both can be used simultaneously.

As for 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.

Brief description of the drawings

The technique that is the subject of the patent will be described below, referring to the accompanying drawings, in which:

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; and 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.

Detailed description of preferred embodiments

According to a first preferred embodiment and referring to Fig. 1, there is illustrated 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, such as a satellite or 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. On the other hand, by activating 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

SUBSTITUTE SHEET (RULE 26) fig. 1, so that the forces they provide have the same direction, different direction and, because their points of application are not on the same straight line, do not cancel and provide a torque. From the moment in which both first and second means work simultaneously and during the time of application of the pair, the ship will describe a curvilinear trajectory whose radius will be determined by the relationship between the angular momentum and the pair of forces. In the instant in which said second means cease to act, that is, when the application of said pair of forces is interrupted, the ship will follow a rectilinear trajectory corresponding to the tangent of the curvilinear trajectory at said instant. A second preferred embodiment of the present invention will be described below, with reference to FIG. 2 of the drawings, which represents a meteorite that moves in the direction of the axis 21 with a rotation represented by 22. The force pairs 23 constitute the other element necessary for the implementation of the invention.

In the present case, 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.

Finally, and now referring to fig. 3 of the drawings, a missile or rocket 31 which incorporates a third preferred embodiment of the invention is schematically represented.

To direct the trajectory of said rocket or missile 31, an angular momentum in the direction is provided

SUBSTITUTE SHEET RULE 26) of the trajectory by rotating part of the fuselage or of a cylindrical part 32 coupled thereto and capable of rotating around its axis of symmetry. According to the new direction to which it is to be oriented, a pair of forces will be provided by operating the thrusters 33 in pairs not located in the same circular section and so that their jets act in the same direction and opposite directions. By controlling the intensity of the angular momentum and the pairs of forces, the trajectory of the rocket is determined.

As those skilled in the art can verify, a system and method have been described above in which modifications and alterations can be made without departing from the spirit or scope of the present invention, as defined in the appended claims. .

SUBSTITUTE SHEET RULE 26

Claims

CLAIMS 1. A system to modify and control the trajectory of a mill that moves through space, characterized in that it comprises: a) 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 b) second means capable of providing pairs of forces of different intensity and duration, whose results are perpendicular to the directions defined in a).

2. A system according to claim 1, characterized in that said device is manned.

3. A system according to claim 1, characterized in that said ingenuity is remote control.

4. A system according to claim 1, characterized in that said ingenuity is autonomous.

5. A method to modify and control the trajectory of a mill that moves through space, characterized in that the operations of:

1) provide an appropriate angular momentum in the direction of the path to be changed;

2) once the angular momentum is stabilized, provide a pair of forces with component perpendicular to the angular momentum, so that said ingenuity begins a change in its trajectory; Y

3) interrupt said operation 2), from which moment said ingenuity will follow a rectilinear path defined by the direction of its speed.

6. A method according to claim 5, characterized in that the radius of variation of the trajectory can be controlled at any time by acting on

SUBSTITUTE SHEET RULE 26 three parameters, namely the ship's travel speed, said angular momentum and said torque.

7. A method according to claim 6, characterized in that said device is manned.

8. A method according to claim 6, characterized in that said ingenuity is remote control.

9. A method according to claim 6, characterized in that said ingenuity is autonomous.

10. A method to modify the trajectory of an inert body that travels through space, characterized by:

1) take advantage of the natural rotation of the body around one or more axes; 2) provide, simultaneously, a pair of forces with component perpendicular to the angular momentum, from which moment a change in the trajectory of said inert body will begin; Y

3) interrupt said operation 2), from which moment the said inert body will follow a rectilinear path defined by the direction of its velocity.

11. A method according to claim 10, characterized in that the radius of variation of the trajectory will be determined at each moment by the speed of movement of said inert body, by its own angular momentum and by said pair of forces.

12. A system to modify and control the trajectory of rockets, missiles or other types of directed or remote control devices that execute an aerial trajectory from its launch until they reach their objective characterized by:

REGL SUBSTITUTE SHEET a) first means capable of providing angular moments to the mill in the direction of the axis that determines the direction of travel; and b) second means capable of providing a pair of forces of different intensity and duration whose result is perpendicular to the direction of travel.

13. A method to modify and control the trajectory of rockets, missiles or other types of directed or remote control devices that execute an aerial trajectory from its launch until they reach their objective characterized by operations of:

1) provide the appropriate angular momentum in the direction of the path to be changed;

2) once the angular momentum is stabilized, provide a pair of forces with component perpendicular to the angular momentum, so that the ingenuity will initiate a modification of its trajectory; Y

3) interrupt said second operation 2), from which moment said ingenuity will follow a rectilinear path defined by the direction of its velocity.

14. A method according to claim 13, characterized in that the radius of variation of the trajectory can be controlled at any time by acting on three parameters, namely the speed of movement of the device, said angular momentum and said pair of forces.

SUBSTITUTE SHEET RULE 26