CN107776910B - Whole-machine-level fault hazard evaluation test flight method of airborne indication recording system - Google Patents
Whole-machine-level fault hazard evaluation test flight method of airborne indication recording system Download PDFInfo
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- CN107776910B CN107776910B CN201610727416.2A CN201610727416A CN107776910B CN 107776910 B CN107776910 B CN 107776910B CN 201610727416 A CN201610727416 A CN 201610727416A CN 107776910 B CN107776910 B CN 107776910B
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Abstract
The invention provides a complete machine level fault hazard evaluation test flight method of an airborne indication recording system, which is characterized by comprising the following steps of preparing before flight: calibrating a standby magnetic compass of the airplane, checking whether the indication precision of the standby magnetic compass is normal or not, and checking the display function and correctness of the integrated standby instrument; preparing a backup shielding piece on the airplane, wherein the shielding piece is made of a light-tight material and can completely cover the display screen of the airplane to be tested; the method comprises the steps of collecting and recording three types of video data of a front cabin scene of the airplane, an integrated standby instrument and a standby magnetic compass and flight state data of the whole-journey longitude, the latitude and the altitude of the airplane.
Description
Technical Field
The invention belongs to airworthiness approval test flight technology of an indication recording system of civil aircrafts and transport aircrafts, and particularly relates to a complete machine level fault hazard evaluation test flight method of the indication recording system.
Background
The indication recording system complete machine level fault hazard evaluation test flight is an important content of airworthiness approval of civil aircrafts and large-scale transport aircrafts, and means that the aircrafts are controlled to complete the whole processes of takeoff, climbing, cruising, descending, approach landing under the condition that all flight information display functions except standby flight information are completely lost, and a driver gives a fault level comment when flying under the fault condition.
The trial flight subjects have high execution risk, the information required by flight can only be controlled by means of standby equipment, the aircraft is difficult to control, and obvious workload is brought to safe flight and landing of a driver, so that the execution difficulty is high. At present, no relevant execution standard exists in China. There is no public guidance for the trial flight practice of the subject in foreign countries. In recent years, civil airliners and large-scale transport airplanes develop rapidly in China, and urgent needs are also obtained for the standardized maturity of the overall level fault hazard evaluation test flight of the indication recording system.
Disclosure of Invention
The purpose of the invention is:
the method is used for evaluating the overall level fault hazard of the civil aircraft and large-scale transport aircraft indication recording system and providing data support for the airworthiness approval of the system.
The technical scheme of the invention is as follows:
during take-off, climbing, cruising, descending and landing on approach, all flight information of the left and right PFD/MFD is not used, and only the flight information of the standby instrument (comprising the integrated standby instrument and the standby magnetic compass) is used for flying.
The first step is as follows: preparation before flight
a) Calibrating a standby magnetic compass of the airplane, checking whether the indication precision of the standby magnetic compass is normal or not, and checking the display function and correctness of the integrated standby instrument;
b) preparing a shielding sheet which is made of opaque material and completely covers the display screen of the tested airplane;
c) the method comprises the steps of collecting and recording three types of video data of a display screen of the front cabin airplane, an integrated standby instrument and a standby magnetic compass and flight state data of the airplane such as the whole-course longitude, the latitude, the altitude and the like.
The second step is that: pilot adaptability test flight with shielding single-side display screen
a) The shielding piece is used for shielding the display at the driving side, the shielding piece is firmly adhered to the display screen of the airplane, and the operation of other keys is not influenced;
b) the piloting operation plane finishes taking off according to given information indicated by the integrated standby instrument and the standby magnetic compass, and the copilot carries out real-time monitoring through a display screen on the other side;
c) after taking off, the pilot aircraft flies at a cruising altitude on a preset flight line, and the copilot carries out real-time monitoring through a display screen on the other side;
d) returning to a given airspace after the flight of the flight line, intercepting a blind landing signal by a forward-piloted control aircraft, and carrying out real-time monitoring on a copilot through a display screen on the other side;
e) landing visually after landing to a decision altitude according to the blind landing signal, closely monitoring the height and the position of the airplane by a landing guidance radar, guiding the airplane when deviating from a glide path or a course, and confirming the position of the airplane by a visual runway method;
f) removing the shielding piece after the airplane lands on the ground and enters a sliding stage;
g) and evaluating the test flight result.
The third step: test flight for display screens at two shielding sides
a) The shielding piece is used for shielding the displays on the two sides of the front/secondary driver, the shielding piece is firmly adhered to the display screen of the airplane, and the operation of other keys is not influenced;
b) the pilot operates the airplane to complete takeoff according to given information indicated by the integrated standby instrument and the standby magnetic compass;
c) after taking off, the pilot operates the airplane to fly at cruising altitude on a preset flight line;
d) returning to a given airspace after the flight of the flight path, and operating the aircraft by an aircraft crew to capture a blind landing signal;
e) landing visually after landing to a decision altitude according to the blind landing signal, closely monitoring the height and the position of the airplane by a landing guidance radar, guiding the airplane when deviating from a glide path or a course, and confirming the position of the airplane by a visual runway method;
f) removing the shielding piece after the airplane lands on the ground and enters a sliding stage;
g) and evaluating the test flight result.
The invention has the advantages that:
1. the method for evaluating and testing the damage of the complete machine level fault of the indicating and recording system is put forward for the first time in China, and the blank of the field in China is filled;
2. the method for shielding the display information by the shielding piece truly simulates the state of losing the main flight display information, and the shielding piece can be uncovered to quickly recover the flight information display when a dangerous case occurs, thereby greatly reducing the risk of test flight and increasing the feasibility of test flight.
Detailed Description
The following takes the evaluation of the fault hazard of the whole level of an indication recording system of a civil passenger plane as an example, and the implementation mode of the invention is further explained:
a) before taking off, the prepared black opaque paper is adhered to the left and right PFD/MFD frames by using a double faced adhesive tape, so that the left and right PFD/MFD are completely shielded, and the operation of other keys is not influenced;
b) the pilot piloted plane finishes takeoff according to the information such as the attitude, the airspeed, the magnetic heading and the like indicated by the integrated standby instrument and the standby magnetic compass;
c) after the carrier takes off, listening to the command of a commander to fly straight to the XX waypoint and climbing to the height Hp30000ft (cruise altitude);
d) after the aircraft reaches the XX route point, listening to the command of a commander to return and descend;
e) a pilot drives the airplane to arrive above the local area, follows the command of a commander and operates the airplane to intercept a blind landing signal of the local area;
f) the method comprises the following steps that visual landing is carried out after the aircraft descends to a decision altitude according to the blind landing indication of the local field, in the period, the local landing guiding radar closely monitors the height and the position of the aircraft carrier, necessary guiding is carried out on the aircraft carrier when the aircraft carrier deviates from a glide path or a course, and meanwhile, a pilot can confirm the position of the aircraft carrier by a method of visual runway; the decision altitude is the altitude at which the aircraft can fly back when approaching.
g) Removing the shielding paper after the carrier falls to the ground and enters a sliding stage;
h) and evaluating the test flight result.
Claims (1)
1. A complete machine level fault hazard evaluation test flight method of an airborne indication recording system is characterized by comprising the steps of preparing before flight:
calibrating a standby magnetic compass of the airplane, checking whether the indication precision of the standby magnetic compass is normal or not, and checking the display function and correctness of the integrated standby instrument;
preparing a standby shielding sheet on the airplane, wherein the shielding sheet is made of a light-tight material and can completely cover the display screen of the airplane to be tested;
collecting and recording three types of video data of a front cabin scene of the airplane, an integrated standby instrument and a standby magnetic compass and flight state data of the whole-course longitude, the latitude and the altitude of the airplane;
the method further comprises the step of shielding pilot adaptability test flight of the single-side display screen:
only the display screen at the driving side is shielded by using the shielding piece, the shielding piece is firmly adhered to the display screen of the airplane, and the operation of other keys is not influenced;
the piloting operation plane finishes taking off according to given information indicated by the integrated standby instrument and the standby magnetic compass, and the copilot carries out real-time monitoring through a display screen on the other side;
after taking off, the pilot aircraft flies at a cruising altitude on a preset flight line, and the copilot carries out real-time monitoring through a display screen on the other side;
returning to a given airspace after the flight of the flight line, intercepting a blind landing signal by a forward-piloted control aircraft, and carrying out real-time monitoring on a copilot through a display screen on the other side;
landing visually after landing to a decision altitude according to the blind landing signal, closely monitoring the height and the position of the airplane by a landing guidance radar, guiding the airplane when deviating from a glide path or a course, and confirming the position of the airplane by a visual runway method;
removing the shielding piece after the airplane lands on the ground and enters a sliding stage;
evaluating the test flight result;
the method further comprises the step of blocking the display screens on the two sides for trial flight:
the shielding sheets are used for shielding the display screens at the two sides of the pilot/copilot, the shielding sheets are firmly adhered to the display screen of the airplane, and the operation of other keys is not influenced;
the pilot operates the airplane to complete takeoff according to given information indicated by the integrated standby instrument and the standby magnetic compass;
after taking off, the pilot operates the airplane to fly at cruising altitude on a preset flight line;
returning to a given airspace after the flight of the flight path, and operating the aircraft by an aircraft crew to capture a blind landing signal;
landing visually after landing to a decision altitude according to the blind landing signal, closely monitoring the height and the position of the airplane by a landing guidance radar, guiding the airplane when deviating from a glide path or a course, and confirming the position of the airplane by a visual runway method;
removing the shielding piece after the airplane lands on the ground and enters a sliding stage;
and evaluating the test flight result.
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| CN201610727416.2A CN107776910B (en) | 2016-08-25 | 2016-08-25 | Whole-machine-level fault hazard evaluation test flight method of airborne indication recording system |
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| CN201610727416.2A CN107776910B (en) | 2016-08-25 | 2016-08-25 | Whole-machine-level fault hazard evaluation test flight method of airborne indication recording system |
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| CN107776910B true CN107776910B (en) | 2020-11-13 |
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| CN102050226A (en) * | 2009-10-30 | 2011-05-11 | 航天科工惯性技术有限公司 | Aviation emergency instrument, and system initial alignment method and combined navigation algorithm thereof |
| FR2978585B1 (en) * | 2011-07-26 | 2013-08-16 | Airbus Operations Sas | METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING A FLIGHT PARAMETER VECTOR OF AN AIRCRAFT, AND METHOD AND ASSEMBLY FOR DETECTING FAILURE AFFECTING SUCH A VECTOR |
| CN102514718B (en) * | 2011-12-01 | 2014-07-02 | 中国科学院西安光学精密机械研究所 | Landing aid method for auxiliary aircraft |
| GB2514109B (en) * | 2013-05-13 | 2015-07-08 | Ge Aviat Systems Ltd | Method for diagnosing a speed brake system fault |
| CN103693204A (en) * | 2013-12-19 | 2014-04-02 | 哈尔滨飞机工业集团有限责任公司 | Control crosslinking method of attitude and heading systems and flight control system |
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