Advanced tactical line replaceable unit alignment system
US-9205517-B1 · Dec 8, 2015 · US
Inertial measurement system for an aircraft
US10415995B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10415995-B2 |
| Application number | US-201615737660-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jun 14, 2016 |
| Priority date | Jun 23, 2015 |
| Publication date | Sep 17, 2019 |
| Grant date | Sep 17, 2019 |
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Abstract
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An inertial measurement system for aircraft, the system comprising at least one processor unit connected to at least two inertial units, namely at least one inertial unit of a first type having at least three angular sensors and three linear sensors aligned on three substantially distinct sensing axes, and an inertial unit of a second type comprising at least four angular sensors and four linear sensors aligned on four substantially distinct sensing axes. The system is arranged to calculate one piece of inertial data from the six sensors of the inertial unit of the first type and four pieces of inertial data from four distinct combinations of three angular sensors and three linear sensors selected from the sensors of the inertial unit of the second type, and the processor unit is arranged to compare the four pieces of inertial data from the measurements of the inertial unit of the second type with one another so as to determine whether the inertial unit of the second type has failed.
First claim
Opening claim text (preview).
The invention claimed is: 1. An inertial measurement system for aircraft, the system comprising at least one processor unit connected to at least two inertial units, namely at least one inertial unit of a first type having at least three angular sensors and three linear sensors aligned on three substantially distinct sensing axes, and an inertial unit of a second type comprising at least four angular sensors and four linear sensors aligned on four substantially distinct sensing axes, the system being arranged to calculate one piece of inertial data from the six sensors of the inertial unit of the first type and four pieces of inertial data from four distinct combinations of three angular sensors and three linear sensors selected from the sensors of the inertial unit of the second type, and the processor unit being arranged to compare the four pieces of inertial data from the measurements of the inertial unit of the second type with one another so as to determine whether the inertial unit of the second type has failed and the processor unit is arranged to calculate a difference between the pieces of inertial data derived from the measurements of the inertial unit of the first type and any one of the pieces of inertial data derived from the inertial unit of the second type and to issue an alert when the difference is greater than a predetermined value. 2. The system according to claim 1 , the four pieces of inertial data from the measurements of the inertial unit of the second type are calculated by means of the same algorithm. 3. The system according to claim 1 , wherein the inertial unit of the second type includes a first control circuit for controlling a first set of sensors comprising three angular sensors and three linear sensors, and a second control circuit for controlling a second set of sensors comprising the fourth angular sensor and the fourth linear sensor. 4. The system according to claim 1 , wherein the sensing axes of the sensors of the inertial unit of the second type comprise three axes coinciding with three canonical axes together with an axis arranged on a trisector of these three axes. 5. The system according to claim 1 , wherein the sensing axes of the sensors of the inertial unit of the second type are aligned on diagonals of a cube.
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Classifications
- G01C25/005Primary
initial alignment, calibration or starting-up of inertial devices · CPC title
by integrating acceleration or speed, i.e. inertial navigation · CPC title
Mechanical, construction or arrangement details of inertial navigation systems · CPC title
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- What does patent US10415995B2 cover?
- An inertial measurement system for aircraft, the system comprising at least one processor unit connected to at least two inertial units, namely at least one inertial unit of a first type having at least three angular sensors and three linear sensors aligned on three substantially distinct sensing axes, and an inertial unit of a second type comprising at least four angular sensors and four linea…
- Who is the assignee on this patent?
- Safran Electronics & Defense
- What technology area does this patent fall under?
- Primary CPC classification G01C25/005. Mapped technology areas include Physics.
- When was this patent published?
- Publication date Tue Sep 17 2019 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).