Quasi-inertial attitude reference platform

• US 4,136,844 A
• Filed: 03/15/1976
• Issued: 01/30/1979
• Est. Priority Date: 03/15/1976
• Status: Expired due to Term

• Current Assignee: Hughes Missile Systems Company
• Original Assignee: General Dynamics Corporation
• Inventors: Maudal, Inge
• Primary Examiner(s): Engle, Samuel W.
• Assistant Examiner(s): Webb, Thomas H.
• Application Number:
  US05/667,240
• Time in Patent Office: 1,051 Days
• Field of Search: 244/3.2, 244/165
• US Class Current: 244/3.2
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/369 using gyroscopes as attitude sensors
• CPC Class Codes: F41G 7/36 using inertial references
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems

Abstract

An inertial guidance system including a true space stable platform is provided while retaining a simple two-degree-of-freedom gimbal system. An added third degree of freedom is provided by motions of the support itself which maintains desired platform orientation. The output of a third axis instrument is used to maneuver the frame itself about the axis of the frame which most nearly will null any rotation about the platform roll or longitudinal axis. A rotational rate gyroscope is positioned on the space stable platform, and actuates the movement of the frame about the longitudinal or roll axis directly from the reading of the rotational movement along the roll axis of the platform.

Claims

1. A space-stable reference platform system comprising:

a frame rotatable about at least one axis;

a platform having three orthogonal axes;

sensing means for sensing rotational movement of the platform about all of said orthogonal axes, said sensing means being positioned on said platform;

inner and outer gimbals for mounting the platform for movement relative to the frame such that the platform is capable of two-degrees-of-freedom axial rotation about first and second orthogonal axes, the outer gimbal being pivotably mounted on the frame, the inner gimbal including the platform being pivotably mounted to the outer gimbal;

first means responsive to said sensing means for rotating said gimbals relative to the frame in order to maintain the platform aligned in space with respect to said first and second axes; and

second means responsive to said sensing means for rotating said frame in order to maintain the platform aligned in space with respect to the third orthogonal axis.

2. The system of claim 1 wherein the sensing means comprises three gyroscopes orthogonally mounted on the platform.

3. The system of claim 1 wherein the second means responsive to the sensing means includes electrical circuitry responsive to voltage potential signals proportional to angular rates of said three axes generated by said sensing means.

4. The system of claim 3 wherein the electrical circuitry includes an integrator for integrating the signal from the sensing means to provide an indication of angular deviation of the platform relative to said third axis.

5. The system of claim 1 wherein the second means is operable to rotate the frame about a longitudinal axis, wherein the outer gimbal is so mounted as to be pivotable about a pivot axis orthogonal to the longitudinal axis of the frame, an wherein the inner gimbal is so mounted as to be pivotable about an axis orthogonal to both the longitudinal axis of the frame and the pivot axis of the outer gimbal.

7. The system of claim 5 wherein the sensing means includes a gyroscope aligned to sense rotation of the platform relative to the longitudinal axis of the frame and coupled to provide a corresponding signal to said second means.

8. The system of claim 3 wherein the electrical circuitry comprises means for performing functions indicated in the following equations:

space="preserve" listing-type="equation">ω

.sub.a = (cosα

cosβ

) ω

.sub.x + (sinα

cosβ

) ω

.sub.y - sinβ

(ω

.sub.z + α

)

space="preserve" listing-type="equation">ω

.sub.b = (-sinα

) ω

.sub.x + (cosα

) ω

.sub.y + β

space="preserve" listing-type="equation">ω

.sub.c = (cosα

sinβ

) ω

.sub.x + (sinα

cosβ

) ω

.sub.y + cosβ

(ω

.sub.z + α

)

wherein ω

_x, ω

_y and ω

_z are respectively rotation rates of the frame;

ω

_a, ω

_b and ω

_c are respectively rotation rates of the platform;

α

is the angle of the outer gimbal relative to the frame;

β

is the angle of the inner gimbal relative to the outer gimbal;

α and

β

are gimbal rates of the outer and inner gimbals respectively; and

further including

means for forcing each of the values ω

_a, ω

_b and ω

_c to equal zero.

9. The system of claim 8 wherein the means for forcing ω

_a to equal zero comprises control means for varying ω

_x.

10. The system of claim 9 wherein the control means further comprises a roll control mechanism attached to the frame.

6. A space-stable reference platform system for controlling the movement of a platform movably positioned within a rotatable frame capable of forced movement through space, comprising:

a frame having a longitudinal axis about which said frame is capable of rolling;

a platform mounted within said frame, said platform having three orthogonal axes;

a plurality of gimbals aligned respectively in only two of said axes for mounting said platform to said frame whereby said platform is capable of two-degrees-of-freedom rotation about two gimbal axes;

sensing means positioned on said platform for sensing rotational movement about all of said orthogonal axes;

first means responsive to said sensing means for rotating said gimbals to compensate for said rotational movement about said two platform axes; and

second means responsive to said sensing means for rotating said frame to compensate for rotational movement of the platform about said third axis.