Inertial measurement unit for spin-stabilized aerial vehicles, and method of providing guidance information using same

• US 8,156,806 B1
• Filed: 12/10/2008
• Issued: 04/17/2012
• Est. Priority Date: 12/10/2007
• Status: Expired due to Fees

• Current Assignee: Milli Sensor Systems & Actuators, Inc.
• Original Assignee: Milli Sensor Systems & Actuators, Inc.
• Inventors: Cardarelli, Donato
• Primary Examiner(s): Kwok, Helen C.
• Application Number:
  US12/332,275
• Time in Patent Office: 1,224 Days
• Field of Search: 735/040.2, 735/040.4, 735/040.3, 735/041.2, 735/041.3, 735/041.4, 735/10, 735/11, 735/141.6, 735/143.5
• US Class Current: 73/511
• CPC Class Codes: G01C 19/5776 Signal processing not specific to any of the devices covered by groups G01C19/5607 - G01C19/5719
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: G01P 15/18 in two or more dimensions

Abstract

An inertial measurement unit (IMU) for a spinning aerial vehicle that spins about a spin axis having a substrate defining a plane, the substrate fixed to the vehicle with the plane essentially orthogonal to the spin axis so that the substrate spins about the spin axis as the vehicle does, at least one generally planar gyroscope coupled to the substrate, the gyroscope defining a gyro input axis that is essentially parallel to the plane and generating a gyro output signal, at least one generally planar accelerometer coupled to the substrate, the accelerometer defining an accelerometer input axis that is essentially parallel to the plane and generating an accelerometer output signal, and a system for demodulating the gyro output signal with a phase-sensitive demodulation referenced to the accelerometer output signal. Also featured is a method of providing guidance information for a spinning aerial vehicle that spins about a spin axis using the described system.

Claims

1. A system for determining acceleration and rotation of a spinning aerial vehicle that spins about a spin axis, wherein the vehicle rotates about a pitch axis that is orthogonal to the spin axis and is orthogonal to the Earth'"'"'s gravity axis, and the vehicle also rotates about a yaw axis that is orthogonal to both the spin axis and the pitch axis, the system comprising:

(a) an inertial measurement unit (IMU) fixed to the vehicle and comprising;

(i) a first gyroscope having a first gyroscope input axis that is essentially orthogonal to the vehicle spin axis, the first gyroscope also having a first gyroscope output signal; and

(ii) a first accelerometer having a first accelerometer input axis that is essentially orthogonal to the vehicle spin axis and that is also essentially orthogonal to or essentially parallel to the first gyroscope input axis, wherein the first accelerometer generates a first accelerometer output signal that represents acceleration of the vehicle along the first accelerometer input axis;

(b) wherein the first gyroscope output signal and the first accelerometer output signal are each modulated by the vehicle spin and thus each possesses an AC component at the vehicle spin rate while the vehicle is spinning; and

(c) a phase-sensitive demodulation system that extracts the AC components of the first gyroscope output signal and the first accelerometer output signal, derives a reference signal from the AC component extracted from the first accelerometer output signal, and demodulates the AC component extracted from the first gyroscope output signal using the reference signal, to obtain a DC signal representing the rate of rotation of the vehicle about either the yaw axis or the pitch axis.

2. The system of claim 1 wherein the IMU further comprises:

(iii) a substrate defining a plane, the substrate fixed to the vehicle with the normal to the plane essentially parallel to the spin axis so that the substrate spins about the spin axis as the vehicle spins about the spin axis;

(iv) wherein the first gyroscope is a generally planar gyroscope coupled to the substrate, wherein the first gyroscope input axis is essentially parallel to the plane; and

(v) wherein the first accelerometer is a generally planar accelerometer coupled to the substrate, wherein the first accelerometer input axis is essentially parallel to the plane.

3. The system of claim 1 wherein the phase-sensitive demodulation system also phase shifts the reference signal by essentially ninety degrees, to create a phase-shifted reference signal.

4. The system of claim 3 wherein the phase-sensitive demodulation system also demodulates the AC component extracted from the first gyroscope output signal using the phase-shifted reference signal, to obtain a DC signal representing the rate of rotation of the vehicle about the other of the yaw axis and the pitch axis.

5. The system of claim 3 wherein the phase-sensitive demodulation system also demodulates the AC component extracted from the first accelerometer output signal using the reference signal, to obtain a DC signal representing the acceleration of the vehicle along either the yaw axis or the pitch axis.

6. The system of claim 5 wherein the phase-sensitive demodulation system also demodulates the AC component extracted from the first accelerometer output signal using the phase-shifted reference signal, to obtain a DC signal representing the acceleration of the vehicle along the other of the yaw axis and the pitch axis.

7. The system of claim 3 wherein the IMU further comprises:

(iii) a Z gyroscope having a Z gyroscope input axis that is essentially parallel to the spin axis, and having a Z gyroscope output signal that is related to rotation rate about the spin axis; and

(iv) a Z accelerometer having a Z accelerometer input axis that is essentially parallel to the spin axis, and having a Z accelerometer output signal that is related to acceleration along the spin axis.

8. The system of claim 1 wherein the IMU further comprises:

(iii) a second gyroscope having a second gyroscope input axis that is essentially orthogonal to both the vehicle spin axis and the first gyroscope input axis, and having a second gyroscope output signal that is related to the rotation rate about the second gyroscope input axis; and

(iv) a second accelerometer having a second accelerometer input axis that is essentially orthogonal to both the vehicle spin axis and the first accelerometer input axis, and having a second accelerometer output signal that is related to the acceleration along the second accelerometer input axis.

9. The system of claim 2 wherein the first accelerometer senses the component of the Earth'"'"'s gravity parallel to the plane of the substrate that is also parallel to the first accelerometer input axis.

10. The system of claim 2 wherein the first accelerometer output signal is at a maximum when the first accelerometer input axis is aligned with the component of the Earth'"'"'s gravity that is parallel to the plane of the substrate.

12. The system of claim 3 wherein the reference signal and the phase-shifted reference signal have the same amplitude.

13. The system of claim 1 wherein the first gyroscope and the first accelerometer are each single degree of freedom devices.

14. The system of claim 7 wherein the first gyroscope, the first accelerometer, the Z gyroscope and the Z accelerometer are each single degree of freedom devices.

15. The system of claim 8 wherein the first gyroscope, the first accelerometer, the second gyroscope and the second accelerometer are each single degree of freedom devices.

11. A system for determining acceleration and rotation of a spinning aerial vehicle that spins about a spin axis, wherein the vehicle rotates about a pitch axis that is orthogonal to the spin axis and is orthogonal to the Earth'"'"'s gravity axis, and the vehicle also rotates about a yaw axis that is orthogonal to both the spin axis and the pitch axis, the system comprising:

(a) an inertial measurement unit (IMU) fixed to the vehicle and comprising;

(i) a substrate defining a plane, the substrate fixed to the vehicle with the normal to the plane essentially parallel to the spin axis so that the substrate spins about the spin axis as the vehicle spins about the spin axis;

(ii) a generally planar gyroscope coupled to the substrate, the gyroscope having a gyroscope input axis that is essentially parallel to the plane and essentially orthogonal to the vehicle spin axis, the gyroscope also having a gyroscope output signal;

(iii) a generally planar accelerometer coupled to the substrate, the accelerometer having an accelerometer input axis that is essentially parallel to the plane, essentially orthogonal to the vehicle spin axis, and essentially orthogonal to or essentially parallel to the gyroscope input axis, wherein the accelerometer generates an accelerometer output signal that represents acceleration of the vehicle along the accelerometer input axis;

(b) wherein the gyroscope output signal and the accelerometer output signal are each modulated by the vehicle spin and thus each possesses an AC component at the vehicle spin rate while the vehicle is spinning; and

(c) a phase-sensitive demodulation system that;

(i) extracts the AC component of the gyroscope output signal and the accelerometer output signal;

(ii) derives a reference signal from the AC component extracted from the accelerometer output signal;

(iii) phase shifts the reference signal by essentially ninety degrees, to create a phase-shifted reference signal;

(iv) demodulates the AC component extracted from the gyroscope output signal using the reference signal, to obtain a DC signal representing the rate of rotation of the vehicle about either the yaw axis or the pitch axis;

(v) demodulates the AC component extracted from the gyroscope output signal using the phase-shifted reference signal, to obtain a DC signal representing the rate of rotation of the vehicle about the other of the yaw axis and the pitch axis;

(vi) demodulates the AC component extracted from the accelerometer output signal using the reference signal, to obtain a DC signal representing the acceleration of the vehicle along either the yaw axis or the pitch axis; and

(vii) demodulates the AC component extracted from the accelerometer output signal using the phase-shifted reference signal, to obtain a DC signal representing the acceleration of the vehicle along the other of the yaw axis and the pitch axis.