Patent ID: 9688416
Date: 2017-06-27
CPC Classifications: B64D,G01C,G01S

Claim:
1. An attitude integrity and display system, the system comprising: a primary inertial reference unit generating a primary attitude solution calculated at least in part as a function of inertial data from a first navigation-grade inertial sensor; a primary aircraft display system coupled to the primary inertial reference unit, wherein the primary aircraft display system displays the primary attitude solution; a hybrid reference unit comprising a first processor that generates a secondary attitude solution calculated at least in part as a function of inertial data received by the first processor from a second navigation-grade inertial sensor; a standby aircraft display system coupled to the hybrid reference unit, wherein the standby aircraft display system displays the secondary attitude solution; an attitude integrity system comprising a second processor that generates an attitude integrity (AI) solution calculated by one or more measurements provided to the second processor by an attitude solution data source, wherein the attitude solution data source provides data independent from the first navigation-grade inertial sensor and the second navigation-grade inertial sensor, wherein the attitude integrity solution is not displayed on either the primary aircraft display system or the standby aircraft display system; an attitude monitor comprising a third processor coupled to the attitude integrity system, wherein the attitude monitor includes a monitoring mode in which the attitude monitor compares the primary attitude solution against the secondary attitude solution; wherein when the primary attitude solution deviates from the secondary attitude solution by more than a predetermine threshold, the attitude monitor identifies either the primary attitude solution or the secondary attitude solution as a failed solution based on a determination of which of the primary attitude solution or the secondary attitude solution has a greatest deviation from the attitude integrity solution; and wherein the attitude monitor generates a warning on one or both of the primary or standby aircraft display system identifying the failed solution.