CN103983801B - The flat aobvious pseudo-velocity vector symbol localization method of a kind of aircraft - Google Patents

Abstract

The flat aobvious pseudo-velocity symbol display method for calculating and locating of a kind of aircraft, belongs to airborne avionics system, it is characterised in that read the prediction inertia angle of attack of inertial navigation output_p, determine " shadow " symbol angle of pitch；Read the inertia sideslip angle beta of inertial navigation output_I, determine " shadow " symbol azimuth；Determine that " shadow " shows opportunity.Use the method aobvious pseudo-velocity symbol flat to aircraft to show and carry out location Calculation, accurately and reliably, can dynamically position with optimal attack angle frame and coordinate mutually, it is ensured that aircraft is along standard glide path landing.

Description

The flat aobvious pseudo-velocity vector symbol localization method of a kind of aircraft

Technical field

The invention belongs to airborne avionics system, particularly to the flat aobvious pseudo-velocity vector symbol location side of a kind of aircraft Method.

Background technology

Pseudo-velocity vector symbol (also referred to as " shadow ") display is on flat showing, and velocity symbol supports the use.Speed Degree vector symbol is driven by the inertia angle of attack and inertia yaw angle, if aerial crosswind is bigger during landing, the inertia of aircraft breaks away Angle also can be relatively big, and at this moment velocity symbol will be displaced to flat aobvious edge.And optimal attack angle frame shows in flat aobvious centre, So align optimal attack angle frame with velocity symbol extremely difficult.In order to solve this problem, velocity symbol is shown Within ± 2 °, but another one problem can be brought: pilot cannot learn the real velocity attitude of aircraft.To this end, introduce A kind of brand-new display symbol pseudo-velocity vector symbol, namely " shadow ", replaces velocity symbol with it, is flown Office staff provides aircraft real velocity attitude.

Summary of the invention

It is an object of the invention to: this invention provides a kind of pseudo-velocity vector symbol display method for calculating and locating, is used for During aircraft landing is glided, when bias current is bigger, (velocity symbol shows within ± 2 °, it is simple to alignment optimal attack angle Frame), provide aircraft real velocity attitude to pilot.Pseudo-velocity vector symbol is directed at landing point, aircraft can be controlled Flying to landing point, assisting in flying person successfully lands.

The technical scheme is that the flat aobvious pseudo-velocity symbol display method for calculating and locating of a kind of aircraft, its feature exists In, comprise the steps:

Step 1:

Read the prediction inertia angle of attack of inertial navigation output_p, determine " shadow " symbol angle of pitch, described " shadow according to formula (1) Son " putting down the pseudo-velocity vector symbol on showing for display:

E_L=-α_p (1)

Step 2:

Read the inertia sideslip angle beta of inertial navigation output_I, determine " shadow " symbol azimuth according to formula (2):

A_Z=β_I (2)

Step 3:

Determine " shadow " show opportunity:

1) when " not cutting partially ", when inertia sideslip angle beta_IShow during ＞ 2 °；

2) when " cutting partially ", when inertia sideslip angle beta_IShow during ＞ 1 °.

The invention have the advantage that use the method aobvious pseudo-velocity symbol flat to aircraft shows and carry out location Calculation, accurately Reliably, can dynamically position with optimal attack angle frame and coordinate mutually, it is ensured that aircraft is along standard glide path landing.

Accompanying drawing explanation

Fig. 1 is that " shadow " size defines schematic diagram

Fig. 2 is " shadow " symbol display schematic diagram on flat aobvious picture

Detailed description of the invention

Below by specific embodiment and combine accompanying drawing the present invention is described in further detail.

The first step: determine " shadow " symbol angle of pitch

If the prediction inertia angle of attack read from inertial navigation_P=3 °

Then " shadow " the symbol angle of pitch: E_L=-α_p=-3 °

Second step: determine " shadow " symbol azimuth

If the inertia sideslip angle beta read from inertial navigation_I=1 °

Then " shadow " symbol azimuth A_Z=1 °

3rd step: determine display opportunity

Due to β_I=1 °, now " shadow " does not shows.

When repeating above step, if the inertia sideslip angle beta read from inertial navigation_I=3 ° of β_I＞ 2 °, now display " shadow " Symbol.

Claims (1)

1. the flat aobvious pseudo-velocity symbol display method for calculating and locating of aircraft, it is characterised in that comprise the steps:

Step 1:

Read the prediction inertia angle of attack of inertial navigation output_p, determine that " shadow " symbol angle of pitch, described " shadow " are according to formula (1) Show at the pseudo-velocity vector symbol put down on aobvious:

$E_L={-}^{{\mathrm{\α}}_p}---\left(1\right)$

Step 2:

Read the inertia sideslip angle beta of inertial navigation output_I, determine " shadow " symbol azimuth according to formula (2):

A_Z=β_I (2)

Step 3:

Determine " shadow " show opportunity:

1) when " not cutting partially ", when inertia sideslip angle beta_IShow during ＞ 2 °；

2) when " cutting partially ", when inertia sideslip angle beta_IShow during ＞ 1 °.