Converter for converting a load factor command into a longitudinal attitude deviation instruction
AssigneeThales
InventorMarc Riedinger
Life of this patent
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Abstract
The invention relates to flight control systems for aircraft, which have large control loops delivering load factor commands and which are applied to flight controls more suited to the following by the pilot of a longitudinal attitude deviation instruction than to the following of a load factor instructions. It consists of a small control loop generating a deviation indicator displayed by the flight director on the PFD screen, with a converter for converting a controlled load factor into a longitudinal attitude deviation instruction comprising a bandpass filter allowing the integration for the calculation of the longitudinal attitude deviation instruction value in the piloting frequency span only.
Claims9
A converter, for aircraft, for converting a load factor command Nzc into a longitudinal attitude deviation instruction Δθc comprising a longitudinal attitude deviation generator circuit with:
- a variable-gain integrator applying the flight mechanics relation linking the load factor Nzc to the longitudinal attitude deviation Δθc:
- Δ
-
-
- θ
- c
- =
- α
- TAS
- ·
- ∫
- (
- N
- zc
- +
- τ
- γ
- ·
- ⅆ
- N
- zc
- ⅆ
- t
- )
-
- ⅆ
- t
- α=180/π being a coefficient for converting radians into degrees,
- τγ the aircraft's trajectory constant, and
- TAS the true air speed of the aircraft considered, and
- a high-pass filter restoring in the long term, to a constant value, the longitudinal attitude deviation instruction value provided by the integrator.
Dependencies are inferred from the claim text.