Mode of controlling working capacity of airborne receiver indicator of satellite radio navigational system

IPC classes for russian patent Mode of controlling working capacity of airborne receiver indicator of satellite radio navigational system (RU 2254591):

G01S7/40 - Means for monitoring or calibrating

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FIELD: the proposed invention refers to radio navigation namely to modes of controlling working capacity of a receiver indicator (RI) of a satellite radio navigational system installed on the board of a flying vehicle.

SUBSTANCE: the mode is that the altitude H_RA of the flight of a flying vehicle is measured with the help of installed on it a radio altimeter (RA), the altitude h_r of an area above which a flying vehicle flies at the moment of the altitude measuring using for this purpose data about planned coordinates from the output of the receiver indicator of the satellite radio navigational system and digital map of an area, an absolute altitude H_a= H_RA +h_r, is calculated and compared with the altitude H_RI, taking from the output of the receiver indicator and a signal of its working capacity is formed if |H_a- H_RI| is smaller than the installed threshold Th.

EFFECT: using of the proposed mode allows in comparison with known modes to decrease the magnitude of the threshold Th. and buy this increase the reliability of RI control installed on a flying vehicle.

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The present invention relates to radio navigation systems, and specifically to methods of monitoring the health (integrity) of the receiver-indicators (PI) satellite navigation systems (SNS), and can be used to improve the reliability of monitoring the health of PIRNS installed on aircraft (LA) for various purposes.

Known [1], p.30-31, PI, adapted for receiving and processing navigation signals from satellites to determine the coordinates, direction and speed of moving objects, including LA, and ways to control their health (integrity) [1], s-457, which consists in comparing the information issued by the PI of at least one coordinate with information about this parameter, obtained by other navigation systems.

Instrument the implementation of this method is illustrated in the functional diagram in figure 1, which includes:

1 - receiver equipment-satellite radionavigation system (PI crns);

2 - the navigation system (NS);

3 is a block comparison (BS).

Information X_PItaken from the PI output 1, and information about the same coordinate Hae output NA 2 are received respectively in the first and second inputs of the BS 3 that generates a signal of health if the difference

where P is the allowable threshold, the characteristic is cherisse performance PI.

Obviously, to avoid the possibility of zabrakovanie workable PI acceptable threshold

where ΔX_PIthat ΔX_E- maximum measurement error of the same coordinates PI and NA, respectively.

From the expression (2), it follows that to improve the reliability of control ΔX_Eshould be minimal.

As shown in [1], s-457, main NA used to evaluate the health (integrity) PI, can be barbastella (BVS) and inertial navigation (ins) system, as well as radio navigation system long-range navigation (RSDN).

Shortcomings of the NS is a large error ΔX_Emeasurements of the navigation parameter.

For example, BVS allows to determine the altitude of LA with error ΔX_ABS=350 m [1], s and error RSDN can reach ΔX_ISDN=500 m [1], s.

These errors exceed the error of the determination of the height using PI. For example, PI-type Navis SN-3301 [1], s, provides the error coordinates is not more than 20 M.

When using BVS and RSDN to assess the performance of the PI thresholds should be selected

P_BVS=20+350=370 m, N_RSDN=20+500=520 m

Such a significant thresholds do not allow to identify the errors of measurement of coordinates of LA using PI, call the by various factors, including the impact of specially organized noise.

The aim of the invention is to increase the reliability of control and a decrease in the detected error PI SRNS.

This objective is achieved in that in the method of monitoring the reliability of output information of diamondcutter satellite radionavigation system based on a comparison of information obtained through diamondcutter satellite navigation system, with external information from other navigation device as a sensor of external information used by the radio altimeter, the output of which is increased by the height of the relief obtained using digital maps on the signals taken from the output of diamondcutter satellite navigation system.

The essence of the proposed method of monitoring the health of PI illustrated by figure 2, which includes:

1 - receiver equipment-satellite radionavigation system (PIRNS);

2 - digital maps (CSM);

3 - the radio (RV);

4 - block the formation of the absolute height (BFAV);

5 - unit comparison (BS).

Communication between blocks correspond to the one presented in figure 2.

Signal processing health PI as follows:

- set the threshold P=ΔN_PIΔ H_and,

where Δ N_PIand ΔN_and- the maximum permissible error of PIRNS and PB+DCW, respectively;

using PB 3 LA measure the relative flight altitude H₀;

using PORNS 1 determine the altitude H_PIand his plan coordinates Y and Z, coming respectively 1 input BS 5, the first and second inputs SMC 2;

according to the Y and Z determine the relative height of the terrain h_pover which the measured height H₀;

- calculate the absolute height

H_a=H₀+h_pand enter her in the BC 5;

- calculate the difference

Δ=(H_and-N_PI);

- compare the difference Δ threshold P and form the signal health, And if less than the threshold P.

The advantage of the proposed method is more accurate measurements of H_andthat allows to reduce the threshold value P, and thus improve the reliability of the PI control.

We will show the possibility of reducing the threshold P.

Error σ_ndetermine the absolute height H_andaircraft flight in this method of performance monitoring can be calculated as

where σ_SMC- the standard error of the SMC;

σ_RV- accuracy radio.

As shown in [2], p.47-48,

where σ_To- error primary mapping, σ_To=2-3 m;

σ_dn- accuracy sampling field-dependent sampling

(W) and the degree of ruggedness of the surface.

According to the schedule given in [2], 48, for moderate terrain σ_dn<1.5 m when W=250 m

In this case,

Error σ_RVdepends on the type of radio altimeter. When using, for example, PB small and large heights of a-035 [3].

σ_RV=±(0,5+0,N) m

If, for example, the flight to LA is at a height H=2000 m, σ_RV=11,5 m

Then

or 3σ_N=36 m

This error is much less than the errors of the air force and RSDN and allows you to set the threshold P=20+36=56 m, which is much less than using the air force and RSDN.

Such a small threshold of P allows to identify less PI errors and thereby improve the completeness of the control.

The advantage of this method is the fact that it allows us to estimate and error positioning, especially when flying over rough terrain.

When significant errors PI determine Y and Z of the SMC will retrieve other information about the height of the terrain, and |N_and-N_PI| exceeds the threshold P.

The realization of the situation this way will not require a significant increase in volume and mass. PB installed on virtually all types of AIRCRAFT, the unit of comparison may be performed on a single programmable logic chip type ARM [4], and SMC necessary to store information about the topography of the land area 200×200 km, can be performed on a single chip type LH 28 F 032 SUND [5].

Literature

1. Global satellite navigation system GLONASS. 2nd edition, corrected. Edited Kharisov, VN, Perov A.I., Boldin VA - M: IPGR, 1999, p.30-31, 385, 455-457.

2. I. N. Beloglazov. and others. The basics of navigation by means of geophysical fields. - M.: Nauka, 1985, p.47-48.

3. Product A-035. The user guide. UPKB "Item", 1985. p.35.

4. WWW. ALTERA. com.

5. SYFRP ELASH Merory LH28F032 8 NO.. Brochure of the firm of SHARP, 2002.

Method of monitoring the health of the onboard diamondcutter satellite navigation systems, namely, that measure the relative height NRV flight of the aircraft with installed on it radio altimeter, determine the relative height of the terrain h_pover which is the aircraft at the time of measuring the height NRV using data on planned coordinates of the aircraft obtained from the output of diamondcutter satellite navigation system, and the height of the terrain h_pobtained with the aid of the updated digital maps on signals, remove from the output of diamondcutter satellite navigation system, calculate the absolute height of the aircraft On=NRV+h_pto compare it with the relative height of the aircraft Cui taken from the output of diamondcutter satellite navigation system, and form the signal of his health, if |On-NPI| is less than the set threshold P=ΔCui+Δwhere ΔCui Δ - maximum permissible error of diamondcutter satellite navigation system, radio altimeter and a digital terrain map.