DE4243273A1 - Device for swinging a missile, with two gyros - Google Patents

Device for swinging a missile, with two gyros

Info

Publication number
DE4243273A1
DE4243273A1 DE19924243273 DE4243273A DE4243273A1 DE 4243273 A1 DE4243273 A1 DE 4243273A1 DE 19924243273 DE19924243273 DE 19924243273 DE 4243273 A DE4243273 A DE 4243273A DE 4243273 A1 DE4243273 A1 DE 4243273A1
Authority
DE
Germany
Prior art keywords
gyros
rotation
angular momentum
gyroscope
gyroscopes
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
DE19924243273
Other languages
German (de)
Inventor
Thomas Dipl Ing Eckardt
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.)
Rockwell Collins Deutschland GmbH
Original Assignee
Rockwell Collins Deutschland GmbH
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
Priority to DE4236116 priority Critical
Application filed by Rockwell Collins Deutschland GmbH filed Critical Rockwell Collins Deutschland GmbH
Priority to DE19924243273 priority patent/DE4243273A1/en
Priority claimed from PCT/DE1993/000963 external-priority patent/WO1994010036A1/en
Publication of DE4243273A1 publication Critical patent/DE4243273A1/en
Ceased legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/28Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24Guiding or controlling apparatus, e.g. for attitude control

Abstract

The orientation of flying objects, in particular satellites, must be stabilised in space. For that purpose, gyroscope devices are used with swivellable gyroscopes in a cardan frame or with gyroscopes fixed in three different directions with adjustable speeds of rotation. These constructions are costly, heavy and prone to failure in certain circumstances. The disclosed device requires only two gyroscopes (1, 2) which may be suspended with a limited cardan mobility, whose axes of rotation coincide in the initial stage and which rotate in opposite directions. By tilting at least one gyroscope and modifying the speed of rotation, any desired resulting torque-vector (Hg) and any desired rotation of the satellite may be achieved.

Description

The invention relates to a device according to the preamble of claim 1.

Most of the spacecraft currently in use (mostly satellites) have to find their orientation in the Space to be stabilized. Often the fact becomes used that the total swirl of a body by amount and Direction is constant as long as no external torques occur act on this body.

Many satellites use this to take advantage of this but not having to rotate the satellite, at least one gyro installed, in which the total twist of the Satellite is stored.

By installing swiveling rotors, e.g. B. in a gimbal, it is possible to change the speed of rotors without to pan the satellite; because by vectorial addition the resulting swirl vector (angular momentum) results is still fixed in space, but its relative to the satellite Location has changed. It is thus possible to use the satellite in the Swivel space without the need for external torque. Gimbals are additional, heavy, failure-prone mechanisms that are also hardly jerk-free are to be swiveled (noiselessly).  

When installing at least two gyros, their fixed Axes of rotation are not parallel to each other, it is possible to pan the satellite by turning the speed of the Gyro is changed. With previous solutions to problems, which make it possible to put a satellite into any one Rotating the direction of space is at least three gyros provided, each a fixed axis of rotation, but one have variable speed. The axes of rotation of at least three of these gyros not parallel to each other. How described above can be done by vectorial addition the angular momentum any according to amount and direction Generate swirl vector. However, since each gyro is in a different one Orientation must be installed is the necessary Construction very complex and heavy. This arrangement calls in the English "skewed arrangement". One feature such a known arrangement is that Acceleration and deceleration energy are used must, and it can happen that one of the gyros must be brought to zero speed. Then surrender Problems restarting due to static friction. Furthermore interferes with what occurs at low speeds Noise spectrum (structure-borne noise) to a particular extent.

One could solve this problem by magnetically mounted gyroscopes encounter, but only in a limited angular range can be pivoted. This limitation is unfortunate because to an increasing extent an extreme silence of even stronger ones tiltable gyros is required, but currently only with magnetically mounted gyros that seems only reachable can be tilted to a limited extent.

The invention with the features of claim 1 or 2 has the advantage of having fewer than three gyros gets along, so that a less complex and less heavy construction results. Despite the  desired usability of magnetically mounted gyros with their restrictions regarding the swivel range Swiveling a missile in any spatial direction. Furthermore, the device according to the invention does not set ahead that the gyro speed is close to zero is steered down where it is also with magnetic bearings Gyroscopes can still give deficits with the smoothness.

By using two gyros with opposite Direction of rotation, at least one of which can be swiveled to a limited extent a resulting angular momentum vector is generated. By Swing at least one of these gyros and (!) Suitable selected speeds, the resulting angular momentum vector in any spatial direction relative to the top attachment (e.g. satellite body). Since the Total angular momentum vector of a body, as initially described, but is fixed in space, the satellite can thus be in be swiveled in every direction.

Three gyros are preferably used, which are in the same Orientation (at least in its starting position) arranged are and can be pivoted about two pivot axes, the orthogonal to each other and to (common in the starting position) Axis of rotation are arranged. Usually only two of them three gyros in operation. The third becomes only if one fails the other gyro used.

The following gyro combinations are possible:

  • - There is no gyroscope and another around two swivel axes pivotable, which are not parallel to each other and to the in Starting position run common direction of the axes of rotation.
  • - Two gyros are each around at least one swivel axis pivotable, with at least two of the pivot axes and the  common direction of the axes of rotation not parallel to each other run.
  • - By adding one or more additional gyros redundancy can be achieved.

The preferred embodiments are in the subclaims specified.

Based on the drawing is a preferred embodiment described the invention.

The drawing shows two rotors 1 and 2 , which can be suspended with limited gimbal mobility. The gyros rotate in opposite directions and generate moments H 1 and H 2 , from which a total moment H g results. In the starting position, not shown, the two moments (angular momentum vectors) H 1 and H 2 can add up to zero or largely compensate each other. By swiveling the gyroscope 1 and 2 and thus the vectors H 1 and H 2 and changing the speed, that is to say changing the amounts of the vectors, the total torque, that is to say the total angular momentum vector H g , can be steered in any desired direction. For this purpose, at least one of the two gyroscopes is tilted and accelerated or decelerated. As a result, the missile, in particular satellite, in which the gyros are located, can be aligned in any desired direction in space, namely by the vector of the total moment H g of the satellite, which is stored in gyros 1 , 2 , with respect to the coordinate system of the satellite is tilted. This means that the satellite can be tilted in any direction without degrading the noise properties, because the gyroscopes can be magnetically supported because they only have to be tilted in a limited range and they do not have to work at low speeds if the total angular momentum vector H g should assume small values.

Redundancy can be achieved by means of a further gyroscope 3 , which can be suspended with limited gimbal mobility, and which can therefore be magnetically mounted, ie the gyroscope 3 takes its place if one of the gyros 1 , 2 fails.

Claims (7)

1. Device for pivoting a missile, with two gyros ( 1 , 2 ), at least one of which can be pivoted relative to the other, characterized in that the gyros ( 1 , 2 ) can be controlled by pivoting and adjusting the speed of at least one of the gyros in each case are that their angular momentum vectors at least partially compensate each other.
2. Device for pivoting a missile, with two rotors ( 1 , 2 ), at least one of which is pivotable relative to the other, characterized in that the pivotability allows the axes of rotation of the rotors ( 1 , 2 ) to be parallel to one another, and that the angular momentum of at least one gyro can be controlled in such a way that the angular momentum vectors of both gyroscopes ( 1 , 2 ) run in opposite directions, but are equal to one another or almost the same size.
3. Device according to claim 1 or 2, characterized in that the axes of rotation of the gyros ( 1 , 2 ) can be aligned with each other.
4. Device according to one of the preceding claims, characterized in that only one ( 1 ) of the gyroscope ( 1 , 2 ) can be pivoted about two pivot axes which are not parallel to one another or to the direction which the axis of rotation of the gyroscope ( 1 ) assumes , if the two angular momentum vectors add up to zero.
5. Device according to one of claims 1 to 3, characterized in that the gyros ( 1 , 2 ) are each pivotable about at least one pivot axis, with at least two of the pivot axes and that direction not parallel to one another which occupies the axis of rotation of a gyroscope, when the two angular momentum vectors add up to zero.
6. Device according to one of the preceding claims, characterized in that a redundancy gyro ( 3 ) is provided.
7. Device according to one of the preceding claims, characterized in that at least one gyro ( 1 , 2 , 3 ) is magnetically mounted.
DE19924243273 1992-10-27 1992-12-21 Device for swinging a missile, with two gyros Ceased DE4243273A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE4236116 1992-10-27
DE19924243273 DE4243273A1 (en) 1992-10-27 1992-12-21 Device for swinging a missile, with two gyros

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19924243273 DE4243273A1 (en) 1992-10-27 1992-12-21 Device for swinging a missile, with two gyros
PCT/DE1993/000963 WO1994010036A1 (en) 1992-10-27 1993-10-12 Device with two gyroscopes for swivelling a flying object

Publications (1)

Publication Number Publication Date
DE4243273A1 true DE4243273A1 (en) 1994-04-28

Family

ID=6471381

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19924243273 Ceased DE4243273A1 (en) 1992-10-27 1992-12-21 Device for swinging a missile, with two gyros

Country Status (1)

Country Link
DE (1) DE4243273A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003042632A1 (en) * 2001-10-17 2003-05-22 Ingeniería Diseño Y Análisis, S.L. Gyroscopic actuator

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2423808A1 (en) * 1978-04-18 1979-11-16 Matra Attitude control of space vehicle - utilises kinetic moments from rotating wheels also used to store energy
DE4026624A1 (en) * 1989-08-30 1991-03-07 Teldix Gmbh Satellite orientation arrangement of flywheel and rotary motor - regulates speed so as to damp oscillations and prevent over-stress of e.g. solar panels
EP0424937A2 (en) * 1989-10-26 1991-05-02 Hughes Aircraft Company Apparatus for compensating for disturbing torques acting on a stabilized spacecraft or the like, with momentum wheel means

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2423808A1 (en) * 1978-04-18 1979-11-16 Matra Attitude control of space vehicle - utilises kinetic moments from rotating wheels also used to store energy
DE4026624A1 (en) * 1989-08-30 1991-03-07 Teldix Gmbh Satellite orientation arrangement of flywheel and rotary motor - regulates speed so as to damp oscillations and prevent over-stress of e.g. solar panels
EP0424937A2 (en) * 1989-10-26 1991-05-02 Hughes Aircraft Company Apparatus for compensating for disturbing torques acting on a stabilized spacecraft or the like, with momentum wheel means

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003042632A1 (en) * 2001-10-17 2003-05-22 Ingeniería Diseño Y Análisis, S.L. Gyroscopic actuator
ES2188404A1 (en) * 2001-10-17 2003-06-16 Ingenieria Diseno Y Analisis S Gyroscopic actuator

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Legal Events

Date Code Title Description
OP8 Request for examination as to paragraph 44 patent law
8131 Rejection