A real-time calculation method of comprehensive system error in rnp

A real-time calculation and integrated system technology, applied in the field of aviation navigation, can solve problems that affect normal flight, do not distinguish the horizontal or vertical component of TSE, and the true value of the calculation result is conservative.

Active Publication Date: 2015-11-25
BEIHANG UNIV
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Problems solved by technology

Although this scalar summation method can obtain real-time TSE, however, this method does not distinguish the horizontal or vertical components of TSE, so when the direction of FTE is different from that of NSE, the scalar sum will be greater than the vector sum, resulting in calculation results that are closer to the real value. Conservative
When the calculated value is compared with the threshold value of the RNP specification, it is likely to cause false alarms, thereby affecting normal flight

Method used

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  • A real-time calculation method of comprehensive system error in rnp
  • A real-time calculation method of comprehensive system error in rnp
  • A real-time calculation method of comprehensive system error in rnp

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Embodiment Construction

[0021] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0022] The TSE real-time calculation method in a kind of RNP of the present invention, method flow chart is as follows image 3 As shown, it specifically includes the following steps:

[0023] Step 1: Calculate the navigation error probability ellipse through the navigation equation.

[0024] Establish the satellite navigation nonlinear observation equation:

[0025] ρ π = | | p π ENU - p r ENU | | + C b - - - ( 1 )

[0026] where: ρ π is the pseudorange of the πth visible satellite, is the position of the satellite in the ENU coor...

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Abstract

The invention discloses a real-time error calculating method of an integrated system in an RNP (Required Navigation Performance). The real-time error calculating method specifically comprises the following steps: 1, figuring out a navigation error probable ellipse through using a navigation equation; 2, rotating the navigation error probable ellipse into a positive ellipse by using a coordinate system rotation algorithm; 3, solving an exterior tangent curve parameter of the positive ellipse, wherein a curve adopted by the invention adopts an exterior tangent straight line (a line tangent ellipse method) and an exterior tangent circle (a circle tangent ellipse method); 4, calculating a real-time TSE (Total System Error) by using the exterior tangent curve parameter; 5, comparing the real-time TSE with an RNP standard threshold to output an alarm result. The real-time error calculating method of the integrated system in the RNP, provided by the invention, is relatively small in calculation cost and can be used for relatively accurately performing a TSE estimation, and is suitable for real-time TSE calculation in the RNP.

Description

technical field [0001] The invention belongs to the field of aviation navigation, and specifically refers to a real-time calculation method of comprehensive system errors in RNP. Background technique [0002] Aeronautical applications place extremely high demands on the level of safety and other performance indicators that need to be met. In terms of navigation, RNP (RequiredNavigationPerformance, required navigation performance) has clear regulations on these performance indicators. It mainly includes four performance indicators, namely accuracy, integrity, continuity and availability. Among them, the improvement of accuracy and real-time alarm play an important role in ensuring the flight safety of RNP. like figure 1 As shown, the accuracy in RNP means that in a certain airspace or route, the airborne navigation system should ensure that the aircraft deviates from the expected track with a probability of more than 95% and does not exceed a certain specification threshold...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C21/20
Inventor 张军李锐付立
Owner BEIHANG UNIV
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