CN113607128B - Low-precision lifting method for radio altimeter - Google Patents
Low-precision lifting method for radio altimeter Download PDFInfo
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- CN113607128B CN113607128B CN202110868184.3A CN202110868184A CN113607128B CN 113607128 B CN113607128 B CN 113607128B CN 202110868184 A CN202110868184 A CN 202110868184A CN 113607128 B CN113607128 B CN 113607128B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C5/00—Measuring height; Measuring distances transverse to line of sight; Levelling between separated points; Surveyors' levels
- G01C5/005—Measuring height; Measuring distances transverse to line of sight; Levelling between separated points; Surveyors' levels altimeters for aircraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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Abstract
A low-precision lifting method for a radio altimeter mainly comprises seven steps of judging that a low-altitude error after an altimeter is installed is large, detecting and confirming whether zero position error delta 0 on the altimeter is qualified or not, testing whether the low-altitude error delta 1 on the altimeter is qualified or not, calibrating zero points of the altimeter, readjusting the error of the altimeter and confirming that the performance of the altimeter is qualified, judging whether system low-altitude error delta 2 on the altimeter is qualified or not, ending if the system low-altitude error delta 2 is qualified, and returning to the steps of detecting and confirming that the altimeter is normal in operation if the system low-altitude error delta 2 is not qualified. According to the method, the low altitude error of the altitude meter after installation can be increased from 1-3 m to less than 0.6m, the performance of the equipment is obviously improved, the low altitude precision of the altitude meter is improved, and the taking-off and landing and ground-attached flight safety of the helicopter are improved.
Description
Technical Field
The invention belongs to the technical field of helicopter altimeter measurement, relates to an altimeter precision improving method, and particularly relates to a radio altimeter low-precision improving method.
Background
The radio altimeter (hereinafter referred to as altimeter) assembled by the helicopter of the helicopter series of the helicopter is developed on the basis of the altimeter assembled by the helicopter of the dolphin produced by the imitation method in a retrofit way, is used for measuring the true altitude of the carrier relative to the terrain over which the carrier flies, can carry out the altitude early warning, and is an important navigation device working by adopting the frequency modulation continuous wave constant difference frequency principle. The height measured by the altimeter is displayed by an integrated display system (hereinafter referred to as "integrated display"). The low altitude precision of the altimeter directly relates to the taking off and landing of the helicopter and the ground-attached flight safety at night, in low visibility or in mountain areas. At present, special equipment and a test method matched with a underwriting unit are mainly adopted to debug and detect the dislocation performance of the altimeter, and the altimeter is installed for use after being qualified.
However, the special equipment and the test method matched with the existing underwriting unit are adopted to debug and detect the qualified altimeter, and after the helicopter is installed, the problem that the low altitude precision is obviously insufficient exists is solved, specifically, the helicopter takes off and has a height of approximately 2 meters or even 3 meters from the ground, but the displayed height of the system is still 0 meter, which is very unfavorable for the taking-off and landing of the helicopter and the safety of ground-attached flight.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, the present invention is directed to providing a method for improving the low accuracy of a radio altimeter, which is used for solving the problem that the low accuracy of the radio altimeter in the prior art is insufficient, so that the helicopter is not beneficial to take-off and landing flight safety.
To achieve the above and other related objects, the present invention provides a method for improving the low accuracy of a radio altimeter, comprising the steps of:
step one: when the helicopter flies, judging that the low altitude error after the altitude meter is installed is large;
step two: in the stop state of the helicopter, detecting and confirming that the altimeter works normally;
step three: in the stop state of the helicopter, testing whether zero error delta 0 on the altimeter is qualified or not, if so, performing a step seven, and if not, performing a step four;
step four: pushing the helicopter to enable the position of the helicopter, where the altimeter receiving and transmitting antenna is installed, to be arranged above the sinking platform, then testing whether the low altitude error delta 1 on the altimeter is qualified or not, if so, performing the step six, and if not, performing the step five;
step five: calibrating a zero point of the altimeter in a stop state of the helicopter;
step six: readjusting the error of the altimeter and confirming that the performance of the altimeter is qualified;
step seven: and (3) placing the position of the helicopter, on which the altimeter receiving and transmitting antenna is mounted, above the sinking platform, judging whether the system low altitude error delta 2 on the altimeter is qualified or not, if so, ending, and if not, returning to the step (II) again.
In any of the above schemes, preferably, in the first step, the method for determining that the low altitude error after the altitude meter is installed is: when the helicopter flies, the unit leaves the ground to a certain height through visual observation of the helicopter, but the radio height displayed by the comprehensive display is still 0m, and the low height error after the altitude meter is installed can be judged to be large.
In any of the above schemes, preferably, in the second step, the method for detecting and confirming that the altimeter works normally comprises the following steps: in the stop state of the helicopter, the ground is electrified to check that the altimeter works normally and the self-checking is qualified; meanwhile, the whole working condition of the altimeter in flight is known to be normal to the unit.
In any of the above schemes, preferably, in the third step, the method for testing whether the zero error on the altimeter is qualified is as follows: in the stop state of the helicopter, when the ground is electrified, the height value of the altimeter is measured, wherein the height value is zero error delta 0 of the altimeter on the helicopter, and if delta 0 is more than 0.6m, the altimeter is unqualified; if the absolute delta 0 is less than or equal to 0.6m, the product is qualified.
In any of the above schemes, preferably, in the fourth step, the method for testing whether the low altitude error on the altimeter is acceptable is as follows: pushing the helicopter, placing the position of the helicopter where the altimeter receiving and transmitting antenna is installed above the sinking platform, powering on the altimeter and the comprehensive display system, measuring the altitude value beta of the altimeter, calculating the low altitude error delta 1 of the altimeter on the helicopter, wherein the calculation formula is as follows,
δ1＝β－γ，
wherein, gamma is the depth of the sinking platform,
then, judging whether the low height error delta 1 on the height meter is qualified or not, wherein the specific judging method is that,
if |δ1| > 0.6m, the test piece is failed,
if the I delta 1I is less than or equal to 0.6m, the product is qualified.
In any of the above schemes, preferably, in the fifth step, the method for calibrating the zero point of the altimeter is as follows: and in the shutdown state of the helicopter, the high-frequency cable plug at the transceiver end of the altimeter is detached and connected to the vector network analyzer, the vector network analyzer is used for testing the actual residual installation height on the altimeter, a new 0-meter delay line is manufactured according to the actual residual installation height, and the new 0-meter delay line is used for calibrating the modulation period of the altimeter, so that the modulation period of the altimeter is equal to the theoretical modulation period value corresponding to zero height.
In any of the above schemes, preferably, in the step six, the method for readjusting the error of the altimeter and confirming that the performance of the altimeter is acceptable comprises the following steps: the error adjusting circuit parameters in the altimeter height output circuit are adjusted, so that the height measurement error of the altimeter not only meets the requirement of low height precision, but also meets the precision of the whole height measurement range, and the overall performance is qualified.
In any of the above schemes, preferably, in the seventh step, the method for judging whether the system low altitude error on the altimeter is qualified is as follows: the position of the helicopter for installing the altimeter receiving and transmitting antenna is arranged above the sinking platform, the altimeter and the comprehensive display system are electrified, the radio altitude alpha displayed by the comprehensive display is read, the system low altitude error delta 2 on the altimeter is calculated, the calculation formula is that,
δ2＝α－γ，
then judging whether the system low height error delta 2 on the height meter is qualified or not, wherein the specific judging method is that,
if |δ2| > 1m, the product is unqualified,
if the I delta 2I is less than 1m, the product is qualified.
In any of the above schemes, preferably, the sinking platform is a rectangular pit formed by opening downwards in the air space beside the apron, the depth of the rectangular pit is gamma, two cement piers are arranged on the upper edge of one side of the sinking platform pushing helicopter, and a step-shaped step is formed from top to bottom on the other side of the sinking platform pushing helicopter.
As described above, the low-precision improvement method of the radio altimeter of the present invention has the following beneficial effects: by the method, the low altitude error of the altitude meter after installation can be increased from 1-3 m to less than 0.6m, the performance of the equipment is obviously improved, and the low altitude precision of the altitude meter is improved, so that the take-off and landing and ground-attached flight safety of the helicopter is improved.
Drawings
Fig. 1 shows a schematic flow chart of the invention.
Fig. 2 shows a cross-sectional view of a submerged platform.
Description of element reference numerals
1-rectangular pit, 2-cement pier and 3-step.
Detailed Description
Further advantages and effects of the present invention will become apparent to those skilled in the art from the disclosure of the present invention, which is described by the following specific examples.
Please refer to fig. 1-2. It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for illustration purposes only and should not be construed as limiting the invention to the extent that it can be practiced, since modifications, changes in the proportions, or otherwise, used in the practice of the invention, are not intended to be critical to the essential characteristics of the invention, but are otherwise, required to achieve the objective and effect taught by the invention. Also, the terms such as "upper," "lower," "left," "right," "middle," and "a" and the like recited in the present specification are merely for descriptive purposes and are not intended to limit the scope of the invention, but are intended to provide relative positional changes or modifications without materially altering the technical context in which the invention may be practiced.
Referring to fig. 1 to 2, in order to overcome the defect of low altitude precision after an altitude meter installation in the prior art, which is very unfavorable for taking off and landing of a helicopter and ground-attached flight safety, the invention provides a low altitude precision lifting method of a radio altitude meter, which is used for realizing the aim of lifting the low altitude precision after the altitude meter installation by carrying out quantitative test on zero position errors and low altitude errors of the state of the altitude meter installation, calibrating zero positions of the altitude meter and readjusting the errors of the altitude meter on the basis of performance of the altitude performance. The method comprises the following specific processes:
step one: when the helicopter flies, judging that the low altitude error after the altitude meter is installed is large;
specifically, when the helicopter flies, the unit senses obvious errors between the flying height of the helicopter and the radio height displayed by the comprehensive display through visual comparison, and the main appearance is that the helicopter has lifted off the ground more than 1-2 m or even 3m, but the radio height displayed by the comprehensive display is still 0m, and then the low-height error after the altitude meter is installed is judged to be large.
The difference between the flight height of the unit visual comparison helicopter and the height displayed by the comprehensive display is larger than about 1m, and the low-altitude error of the installed altimeter can be judged to be large.
Step two: in the stop state of the helicopter, detecting and confirming that the altimeter works normally;
in a helicopter stopping state, the ground electrifying checking altimeter works normally, namely the radio height displayed by the comprehensive display is 0m, and the self-checking is qualified; meanwhile, the whole working condition of the altimeter in flight is known to be normal to the unit.
Step three: in the stop state of the helicopter, testing whether zero error delta 0 on the altimeter is qualified or not;
specifically, in the state of stopping the helicopter, when the ground is electrified, a high-precision digital voltmeter is used for monitoring the actual output height voltage signal of the altimeter on line, a specific height value is converted through a height conversion relation, the height value is zero position error delta 0 of the altimeter on the helicopter, and then whether the zero position error delta 0 of the altimeter on the helicopter is qualified or not is judged, and the judging method is as follows:
if the I delta 0I is more than 0.6m, the product is unqualified;
if the absolute delta 0 is less than or equal to 0.6m, the product is qualified.
If the zero error delta 0 on the altimeter is not qualified, testing whether the low altitude error delta 1 on the altimeter is qualified or not;
if the zero error delta 0 on the altimeter is qualified, judging whether the system low altitude error delta 2 on the altimeter is qualified or not.
Step four: testing whether the low altitude error delta 1 on the altimeter is qualified or not;
specifically, the helicopter is pushed, the position of the helicopter, on which the altimeter receiving and transmitting antenna is installed, is arranged above the sinking platform, the altimeter and the comprehensive display system are electrified, the high-precision digital voltmeter is used for monitoring the actual output altitude voltage signal of the altimeter on line, a specific altitude value beta is converted through the altitude conversion relation, then the converted altitude value beta is used for calculating the low altitude error delta 1 of the altimeter on the helicopter, the calculation formula is that,
δ1＝β－γ，
wherein, gamma is the depth of the sinking platform,
then, judging whether the low height error delta 1 on the height meter is qualified or not, wherein the specific judging method is that,
if |δ1| > 0.6m, the test piece is failed,
if the I delta 1I is less than or equal to 0.6m, the product is qualified.
If the low altitude error delta 1 on the altimeter machine is not qualified, calibrating the zero point of the altimeter;
and if the low height error delta 1 on the altimeter machine is qualified, readjusting the error of the altimeter and confirming that the performance of the altimeter is qualified.
Step five: calibrating a zero point of the altimeter in a stop state of the helicopter;
the method comprises the following steps: and in the shutdown state of the helicopter, the high-frequency cable plug at the transceiver end of the altimeter is detached and connected to the vector network analyzer, the actual residual installation height on the altimeter is tested by using the group delay function of the vector network analyzer, a new 0-meter delay line is manufactured according to the actual residual installation height, and the modulation period of the altimeter is calibrated by using the new 0-meter delay line, so that the modulation period of the altimeter is equal to the theoretical modulation period value corresponding to zero height.
Step six: readjusting the error of the altimeter and confirming that the performance of the altimeter is qualified;
the method comprises the following steps: the error adjusting circuit parameters in the altimeter height output circuit are adjusted, so that the height measurement error of the altimeter not only meets the requirement of low height precision, but also meets the precision of the whole height measurement range, and the overall performance is qualified.
Step seven: judging whether a system low altitude error delta 2 on the altimeter is qualified or not;
specifically, the position of the helicopter for installing the altimeter receiving and transmitting antenna is arranged above a sinking platform, the altimeter and a comprehensive display system are electrified, the radio height alpha displayed by the comprehensive display is read, the system low height error delta 2 on the altimeter is calculated, the calculation formula is as follows,
δ2＝α－γ，
then judging whether the system low height error delta 2 on the height meter is qualified or not, wherein the specific judging method is that,
if |δ2| > 1m, the product is unqualified,
if the I delta 2I is less than 1m, the product is qualified.
If the system low altitude error delta 2 on the altimeter is not qualified, returning to the second step for corresponding adjustment;
if the system low height error delta 2 on the altimeter is qualified, ending, wherein the adjusted system low height error is small.
As a further description of the above embodiments, the altimeter includes a transceiver 1 piece, a feedhorn 2 piece, a transmitting cable 1 piece, and a receiving cable 1 piece.
The altitude signal output by the altimeter is direct current voltage proportional to the measured altitude.
The summary is converted by high precision a/D and software processing, showing the radio altitude.
The design height measurement error of the altimeter in the working range of 0-30 m is as follows: 0.6m or 3%H, and the others.
The altimeter measures the true altitude, i.e., the vertical distance of the carrier from the air to the ground directly below. For a helicopter, the minimum height of the measurement output of the altimeter is 0m when the helicopter is in a ground state, so that the minimum display value of the radio height is set to be 0m in the comprehensive design.
As a further description of the above embodiment, in the third step, in the shutdown state of the helicopter, the altimeter and the comprehensive display system are powered on, the high-precision digital voltmeter is used to monitor the actual output altitude voltage signal of the altimeter on line, the specific altitude value is converted through the altitude conversion relationship, and then the zero error of the installed state of the altimeter is obtained by subtracting 0m from the altitude value. Therefore, the specific altitude value converted by the altitude conversion relation is the zero position error delta 0 of the altimeter on the machine.
As a further description of the above embodiment, in the third and fourth steps, the conversion relationship between the altitude voltage signal actually output by the altimeter and the altitude is: height (m) =height voltage (V)/0.0164;
the selection requirements for the high-precision digital voltmeter are as follows: the measurement accuracy is higher than the comprehensive A/D conversion accuracy (more than or equal to 14 bits), and the input impedance is large enough (far larger than the rated load value of the altimeter) to avoid influencing the system error.
As a further description of the above embodiment, in the fourth step, because of the specificity of the 0m point, for the linear altimeter, to accurately quantify the systematic error, an error test of a low altitude point is added. In order to be basically the same as the real flight state, ensure the precision and stability of the test, facilitate the test operation and reduce the test flight cost, the invention provides a test facility method which comprises the following steps: according to the directivity of the altimeter transceiver (horn) antenna, a sinking platform is built beside the apron, and the sectional view of the sinking platform is shown in fig. 2.
The sinking type platform is characterized in that a rectangular pit 1 is formed downwards in the air space beside the parking apron, the depth of the rectangular pit 1 is gamma, and the rectangular pit 1 and the ground on two sides of the top form the sinking type platform together. Two cement piers 2 are arranged on a platform at one side of the rectangular pit 1, and a step 3 in a stepped shape is formed at the other side of the rectangular pit 1.
The depth of the sinking platform is gamma, the height of the cement pier 2 is 150mm, but the sinking platform is not limited to 150mm, and the sinking platform can be correspondingly adjusted according to the use requirement. The cement pier 2 is used for limiting the pushing position of the helicopter and ensuring the safety when the helicopter is pushed.
The step-shaped step 3 is mainly used for facilitating staff to descend into the rectangular pit 1 to clean the surplus materials.
The helicopter is pushed to the upper edge of the sinking platform, and the wheel is positioned outside the cement pier 2, so that the tail beam part for installing the altimeter antenna is positioned right above the rectangular pit 1, and the height is equivalent to the height for the helicopter to fly flatly by the depth gamma of the sinking platform. The depth gamma of the sinking platform=the altimeter system shows the theoretical value +0.1m when the height gauge is changed from 1m to 2m, so that the low-height error of the altimeter can be tested to be no more than 0.6m.
And in a state that the position of the helicopter, on which the altimeter receiving and transmitting antenna is mounted, is arranged above the sinking platform, powering on the altimeter and the comprehensive display system, monitoring the actual output altitude voltage signal of the altimeter on line by using a high-precision digital voltmeter, converting a specific altitude value through an altitude conversion relation, and subtracting the depth gamma of the sinking platform from the altitude value to obtain a low altitude error of the installation state of the altimeter.
As a further description of the above embodiment, in the fifth step, there is a problem that the height gauge generally has a large error in height after installation, which means that the designed remaining installation height is not consistent with the actual remaining installation height on the helicopter. According to the working mode of the frequency modulation continuous wave constant difference frequency altimeter, the output in the whole height measurement (0-600 m) range is linear, only two adjustment potentiometers are designed in a height output circuit, one adjustment potentiometer is used for adjusting one slope at a zero point, and the error adjustment principle of determining one straight line at two points is adopted, so that the adjustable quantity near 0m is very small, and the problems that the whole technical performance is ensured and the low height error is reduced can not be solved if only the development technical data and the adjustment process of a development unit are used.
Thus, this embodiment first measures the actual remaining mounting height of the altimeter on the helicopter: in the stop state of the helicopter, the high-frequency cable plug at the transceiver end of the altimeter is detached and connected to the vector network analyzer, and the group time of the vector network analyzer is usedGroup delay tau (mu s) corresponding to the actual remaining mounting height on the altimeter is tested by the delay function, and the actual remaining mounting height H on the altimeter is calculated by using the group delay tau corresponding to the actual remaining mounting height on the altimeter 0 (m) the calculation method is as follows:
H 0 ＝3×10 8 τ/2。
according to the actual remaining mounting height H 0 The corresponding group delay tau parameter creates a new "0 m" delay line.
And then performing zero calibration of the altimeter, and calibrating the modulation period of the altimeter by using the newly manufactured 0-meter delay line to ensure that the modulation period of the altimeter is equal to the theoretical modulation period corresponding to zero height.
As a further description of the above embodiment, in the sixth step, after the zero calibration of the altimeter is completed, two height error adjustment potentiometers in the altimeter height output circuit are adjusted, and the fixed resistor of the branch where the potentiometers are located is properly selected to make up for the deficiency of the adjustment amount of the potentiometers; and firstly adjusting the 0m error, then adjusting the low height error, and then checking that the 0m error is qualified, otherwise, adjusting the errors in sequence again until the height point errors meet the technical requirements.
In summary, the method can improve the low altitude error of the altitude meter from 1-3 m to not more than 0.6m, obviously improve the performance of the equipment, and improve the low altitude precision of the altitude meter, thereby improving the take-off and landing and ground-attached flight safety of the helicopter. Therefore, the invention effectively overcomes various defects in the prior art and has high industrial utilization value.
The above embodiments are merely illustrative of the principles of the present invention and its effectiveness, and are not intended to limit the invention. Modifications and variations may be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the invention. Accordingly, it is intended that all equivalent modifications and variations of the invention be covered by the claims, which are within the ordinary skill of the art, be within the spirit and scope of the present disclosure.
Claims (9)
1. A method for low precision elevation of a radio altimeter, the method comprising the steps of:
step one: when the helicopter flies, determining a low altitude error after the altitude meter is installed according to the actual flying altitude and the radio altitude;
step two: in the stop state of the helicopter, detecting and confirming that the altimeter works normally;
step three: in the stop state of the helicopter, testing whether zero error delta 0 on the altimeter is qualified or not, if so, performing a step seven, and if not, performing a step four;
step four: pushing the helicopter to enable the position of the helicopter, where the altimeter receiving and transmitting antenna is installed, to be arranged above the sinking platform, then testing whether the low altitude error delta 1 on the altimeter is qualified or not, if so, performing the step six, and if not, performing the step five;
wherein, δ1 is: powering on the altimeter and the comprehensive display system, measuring the altitude value beta of the altimeter, and calculating the altitude error between the altitude value beta and the sinking platform;
step five: calibrating a zero point of the altimeter in a stop state of the helicopter;
step six: readjusting the error of the altimeter and confirming that the performance of the altimeter is qualified;
step seven: the position of the helicopter, on which the altimeter receiving and transmitting antenna is arranged, is arranged above the sinking platform, whether the system low altitude error delta 2 on the altimeter is qualified or not is judged, if the system low altitude error delta 2 is qualified, the process is finished, and if the system low altitude error delta 2 is not qualified, the process returns to the step two again;
wherein, δ2 is: and electrifying the altimeter and the comprehensive display system, measuring the altitude value alpha of the altimeter, and calculating the altitude error between the altitude value alpha and the sinking platform.
2. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the first step, the method for judging the low height error after the height gauge is installed comprises the following steps: when the helicopter flies, the unit leaves the ground by visual observation, but the radio height displayed by the comprehensive display is still 0m, so that the low height error after the altitude meter installation is judged to be large.
3. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the second step, the method for detecting and confirming the normal operation of the altimeter comprises the following steps: in the stop state of the helicopter, the ground is electrified to check that the altimeter works normally and the self-checking is qualified; meanwhile, the whole working condition of the altimeter in flight is known to be normal to the unit.
4. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the third step, the method for testing whether the zero error on the altimeter is qualified is as follows: in the stop state of the helicopter, when the ground is electrified, the height value of the altimeter is measured, wherein the height value is zero error delta 0 of the altimeter on the helicopter, and if delta 0 is more than 0.6m, the altimeter is unqualified; if the absolute delta 0 is less than or equal to 0.6m, the product is qualified.
5. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the fourth step, the method for testing whether the low height error on the altimeter is qualified is as follows: pushing the helicopter, placing the position of the helicopter where the altimeter receiving and transmitting antenna is installed above the sinking platform, powering on the altimeter and the comprehensive display system, measuring the altitude value beta of the altimeter, calculating the low altitude error delta 1 of the altimeter on the helicopter, wherein the calculation formula is as follows,
δ1＝β－γ，
wherein, gamma is the depth of the sinking platform,
then, judging whether the low height error delta 1 on the height meter is qualified or not, wherein the specific judging method is that,
if |δ1| > 0.6m, the test piece is failed,
if the I delta 1I is less than or equal to 0.6m, the product is qualified.
6. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the fifth step, the method for calibrating the zero point of the altimeter comprises the following steps: and in the shutdown state of the helicopter, the high-frequency cable plug at the transceiver end of the altimeter is detached and connected to the vector network analyzer, the vector network analyzer is used for testing the actual residual installation height on the altimeter, a new 0-meter delay line is manufactured according to the actual residual installation height, and the new 0-meter delay line is used for calibrating the modulation period of the altimeter, so that the modulation period of the altimeter is equal to the theoretical modulation period value corresponding to zero height.
7. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the sixth step, the method for readjusting the error of the altimeter and confirming the qualified performance of the altimeter comprises the following steps: the error adjusting circuit parameters in the altimeter height output circuit are adjusted, so that the height measurement error of the altimeter not only meets the requirement of low height precision, but also meets the precision of the whole height measurement range, and the overall performance is qualified.
8. The radio altimeter low precision lifting method according to claim 1, characterized in that: in the seventh step, the method for judging whether the system low-altitude error on the altimeter is qualified comprises the following steps: the position of the helicopter for installing the altimeter receiving and transmitting antenna is arranged above the sinking platform, the altimeter and the comprehensive display system are electrified, the radio altitude alpha displayed by the comprehensive display is read, the system low altitude error delta 2 on the altimeter is calculated, the calculation formula is that,
δ2＝α－γ，
then judging whether the system low height error delta 2 on the height meter is qualified or not, wherein the specific judging method is that,
if |δ2| > 1m, the product is unqualified,
if the I delta 2I is less than 1m, the product is qualified.
9. The radio altimeter low precision lifting method according to claim 1, characterized in that: the sinking platform is characterized in that a rectangular pit (1) is formed in the space beside the parking apron downwards, the depth of the rectangular pit (1) is gamma, two cement piers (2) are arranged on the upper edge of one side of the sinking platform pushing helicopter, and a step-shaped step (3) is formed on the other side of the sinking platform from top to bottom.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0557592A1 (en) * | 1992-02-26 | 1993-09-01 | TELDIX GmbH | Device for calibrating a measuring device |
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2021
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| EP0557592A1 (en) * | 1992-02-26 | 1993-09-01 | TELDIX GmbH | Device for calibrating a measuring device |
| CN102591355A (en) * | 2012-02-24 | 2012-07-18 | 山东电力研究院 | Method for detecting safe power-line-cruising distance of UAV (unmanned aerial vehicle) |
| CN105093193A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Helicopter height measurement system airborne detecting method |
| CN105547328A (en) * | 2015-12-14 | 2016-05-04 | 中航通飞华南飞机工业有限公司 | Radio altimeter indicator detection system and detection method |
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