CN108238284A - A kind of aircraft Distal promoter tests system - Google Patents
A kind of aircraft Distal promoter tests system Download PDFInfo
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- CN108238284A CN108238284A CN201711482060.1A CN201711482060A CN108238284A CN 108238284 A CN108238284 A CN 108238284A CN 201711482060 A CN201711482060 A CN 201711482060A CN 108238284 A CN108238284 A CN 108238284A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The present invention relates to flight system testing field, more particularly to a kind of aircraft Distal promoter test system, including：Inertial navigation combinations of satellites system；Atmospheric engine system；Radio altimeter；Landing system；Topographic database, for providing scheduled terrain data；Warning system；Ground proximity warning computer, for structure simulation aircraft, build artificially generated terrain, the corresponding simulated flight of control simulation aircraft progress or simulation landing, the alert mode for judging simulation aircraft, and transmission and the corresponding alarm command of the alert mode or cancellation alarm command.The aircraft Distal promoter test system of the present invention, can carry out simulation test to ground proximity warning system, ensure performance higher, cost is lower.
Description
Technical field
The present invention relates to flight system testing field, more particularly to a kind of aircraft Distal promoter test system.
Background technology
Ground proximity warning system is one of important composition equipment of Flight Safety.It can be excessive according to decrease speed,
Near-earth rate is excessive；Wing flap when climbing that takes off or go around is transferred too small；It is highly too low；Aircraft into it is near when, glide path is deflected downwardly；
Situations such as wind shear, provides warning message for pilot.
Therefore, the security performance of ground proximity warning system and stability etc. are tested particularly important；But near-earth at present
The test of warning system is carried out on entity aircraft, and security performance ensures low and somewhat expensive.
Invention content
The object of the present invention is to provide a kind of aircraft Distal promoters to test system, can carry out mould to ground proximity warning system
Intend test.
The technical scheme is that：
A kind of aircraft Distal promoter tests system, including：
Inertial navigation combinations of satellites system, for providing roll attitude information, pitch attitude information and the course of aircraft to be measured
Information；
Atmospheric engine system, for providing pressure altitude, the air speed information during aircraft flight to be measured；
Radio altimeter, real event elevation information during for providing aircraft flight to be measured from the ground；
Landing system, for provide aircraft to be measured whether land and undercarriage whether the information of folding and unfolding；
Topographic database, for providing scheduled terrain data；
Warning system is alerted or is cancelled alarm for the alarm command according to reception and cancellation alarm command；
Ground proximity warning computer is used for：
The simulation aircraft that structure matches with the aircraft to be measured；
According to the data that the topographic database provides, structure carries out simulated flight or simulation for the simulation aircraft
Artificially generated terrain during landing；
The letter inputted according to the inertial navigation combinations of satellites system, atmospheric engine system, radio altimeter and landing system
Breath controls the simulation aircraft to carry out corresponding simulated flight or simulate to land；
Simulated flight is carried out according to the simulation aircraft or related data and predetermined alarm data and is made a reservation for when simulation is landed
Cancel alarm data to be compared, judge the alert mode of the simulation aircraft, and sent and the announcement to the warning system
The corresponding alarm command of police's pattern cancels alarm command.
Optionally, the ground proximity warning computer includes：
Gound-mapping algoritic module, for the data provided according to the topographic database, component flies for the simulation
Machine carries out artificially generated terrain when simulated flight or simulation landing；
Alert algoritic module, for simulated flight is carried out according to the simulation aircraft or when simulation is landed related data with it is pre-
Determine alarm data and predetermined alarm data of cancelling is compared, judge the alert mode of the simulation aircraft.
Optionally, the warning system includes alarm prompt lamp, language alarm device and display alarm device.
Optionally, the alert mode of the simulation aircraft includes：
Excessive fall rate alarm, the alarm of excessive near-earth rate fall height alarm, incorrect landing configuration announcement after taking off
It is alert and excessive less than glide path alarm.
Optionally, under the excessive fall rate alert mode, predetermined alarm data is radio altitude 475.3m, sinks
Speed 19.6m/s, it is radio altitude 224.7m, subsidence velocity 9m/s to make a reservation for cancel alarm data；
Under the excessive near-earth rate alert mode, predetermined alarm data is radio altitude 322.6m, crust deformation rate
22.7m/s makes a reservation for cancel alarm data as radio altitude 178, crust deformation rate 6.3m/s；
It is described take off after fall under height alert mode, predetermined alarm data be radio altitude 163.4m, make a reservation for cancel accuse
Alert data are radio altitude 180.1m；
Under the incorrect landing configuration alert mode, predetermined alarm data for undercarriage be in collapsed state, wirelessly
Electrical height 150.5m makes a reservation for cancel alarm data as radio altitude 49.6m, gear down；
It is described excessively less than under glide path alert mode, predetermined alarm data for simulation aircraft implement microwave landing approach,
Radio altitude is less than 300m, is deflected downwardly glide path center line more than 0.11385DDM, and it is radio to make a reservation for cancel alarm data
Highly it is less than 90m, is deflected downwardly glide path center line more than 0.1750DDM.
Invention effect：
The aircraft Distal promoter test system of the present invention, can carry out simulation test to ground proximity warning system, ensure performance
Higher, cost are lower.
Description of the drawings
Fig. 1 is aircraft Distal promoter test system structure schematic diagram of the present invention.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of range.
1 aircraft Distal promoter of the present invention test system is described in further details below in conjunction with the accompanying drawings.
A kind of aircraft Distal promoter tests system, including inertial navigation combinations of satellites system 1, atmospheric engine system 2, radio altitude
Table 3, landing system 4, topographic database 5, warning system 6 and ground proximity warning computer 7.
Wherein, inertial navigation combinations of satellites system 1, atmospheric engine system 2, radio altimeter 3 and landing system 4 can bases
The correspondence system that selection is needed to be adapted with aircraft to be measured, details are not described herein again for concrete structure.
Inertial navigation combinations of satellites system 1 is used to provide roll attitude information, pitch attitude information and the course of aircraft to be measured
The information such as information；Pressure altitude, air speed information, flying speed when atmospheric engine system 2 is used to provide aircraft flight to be measured and
The information such as vertical speed；Real event elevation information when radio altimeter 3 is for providing aircraft flight to be measured from the ground；It lands and is
System 4 for provide aircraft to be measured whether land and undercarriage whether the information of folding and unfolding.
5 storage inside of topographic database is for providing scheduled terrain data, i.e., to be measured there are many suitable terrain data
The landform that aircraft needs fly.
Warning system 6 is used to be alerted or cancelled alarm according to the alarm command and cancellation alarm command of reception.It accuses
Alert system 6 can be to select in a manner of a variety of suitable alarms, such as phonic warning, display alarm etc. as needed, the present embodiment
In, preferably warning system 6 includes alarm prompt lamp 61, language alarm device 62 and display alarm device 63, so that alarm is brighter
Really.
Ground proximity warning computer 7 can select a variety of suitable computers as needed；Ground proximity warning computer 7 can be used
In the simulation aircraft that component and the aircraft to be measured match；Furthermore it is possible to 5 data are provided according to topographic database, structure
For simulating artificially generated terrain when aircraft carries out simulated flight or simulation landing；It further more, can be according to the inertial navigation satellite group
The relevant information that collaboration system 1, atmospheric engine system 2, radio altimeter 3 and landing system 4 input, controls the simulation aircraft
It carries out corresponding simulated flight or simulation is landed；Finally, can also simulated flight be carried out according to the simulation aircraft or simulated
Related data is compared with predetermined alarm data and predetermined alarm data of cancelling during land, judges the alarm mould of the simulation aircraft
Formula, and sent and the corresponding alarm command of the alert mode or cancellation alarm command to the warning system 6.
It should be noted that such as automobile is simulated and constructed by computer corresponding environment allows simulation
Automobile carries out skimulated motion, belongs to the technology of comparative maturity at present, no longer repeats herein how it specifically realizes.
The aircraft Distal promoter test system of the present invention, can carry out ground proximity warning system simulation test, before opposite
It needs to carry out for practical flight test, ensures performance higher, cost is lower.
Further, in aircraft Distal promoter test system of the invention, ground proximity warning computer 7 can include gound-mapping
Algoritic module 71 and alarm algoritic module 72.
Gound-mapping algoritic module 71 is mainly used for the data provided according to topographic database 5, and component is winged for simulating
Machine carries out artificially generated terrain when simulated flight or simulation landing.Alarm algoritic module 72 is used to be simulated according to simulation aircraft
Related data is compared with predetermined alarm data and predetermined alarm data of cancelling when flight or simulation are landed, and judges to simulate aircraft
Alert mode.
Further, in aircraft Distal promoter test system of the invention, the alert mode for simulating aircraft includes following 5 kinds of moulds
Formula：
Excessive fall rate alarm, the alarm of excessive near-earth rate fall height alarm, incorrect landing configuration announcement after taking off
It is alert, excessive to be alerted less than glide path.
Correspondingly, under excessive fall rate alert mode, predetermined alarm data is radio altitude 475.3m, lower settling velocity
19.6m/s is spent, is alerted at this time；Predetermined alarm data of cancelling is radio altitude 224.7m, subsidence velocity 9m/s, is taken at this time
Disappear alarm.
Under excessive near-earth rate alert mode, predetermined alarm data is radio altitude 322.6m, crust deformation rate
22.7m/s is alerted at this time；Predetermined alarm data of cancelling takes at this time for radio altitude 178, crust deformation rate 6.3m/s
Disappear alarm.
Fall after take off under height alert mode, predetermined alarm data is radio altitude 163.4m, is alerted at this time；
Predetermined alarm data of cancelling is radio altitude 180.1m, cancels alarm at this time.
Under incorrect landing configuration alert mode, predetermined alarm data is in collapsed state, radio for undercarriage
Height 150.5m, alerts at this time；It is predetermined cancel alarm data for radio altitude 49.6m, gear down, cancel at this time
Alarm.
In the case where being excessively less than glide path alert mode, predetermined alarm data implements microwave landing approach, nothing for simulation aircraft
Line electrical height is less than 300m, is deflected downwardly glide path center line more than 0.11385DDM, alerts at this time；It is predetermined to cancel alarm number
According to being less than 90m for radio altitude, being deflected downwardly glide path center line more than 0.1750DDM, cancel alarm at this time.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (5)
1. a kind of aircraft Distal promoter tests system, which is characterized in that including：
Inertial navigation combinations of satellites system (1), for providing roll attitude information, pitch attitude information and the heading device of aircraft to be measured
Breath；
Atmospheric engine system (2), for providing pressure altitude, the air speed information during aircraft flight to be measured；
Radio altimeter (3), real event elevation information during for providing aircraft flight to be measured from the ground；
Landing system (4), for provide aircraft to be measured whether land and undercarriage whether the information of folding and unfolding；
Topographic database (5), for providing scheduled terrain data；
Warning system (6) is alerted or is cancelled alarm for the alarm command according to reception and cancellation alarm command；
Ground proximity warning computer (7), is used for：
The simulation aircraft that structure matches with the aircraft to be measured；
The data of (5) are provided according to the topographic database, structure carries out simulated flight or simulation for the simulation aircraft
Artificially generated terrain during landing；
According to the inertial navigation combinations of satellites system (1), atmospheric engine system (2), radio altimeter (3) and landing system (4)
The information of input controls the simulation aircraft to carry out corresponding simulated flight or simulation landing；
Related data and predetermined alarm data and predetermined cancellation when being landed according to the simulation aircraft progress simulated flight or simulation
Alarm data is compared, and judges the alert mode of the simulation aircraft, and is sent and the alarm to the warning system (6)
The corresponding alarm command of pattern cancels alarm command.
2. aircraft Distal promoter according to claim 1 tests system, which is characterized in that the ground proximity warning computer
(7) include：
Gound-mapping algoritic module (71), for the data provided according to the topographic database (5), component is used for the simulation
Aircraft carries out artificially generated terrain when simulated flight or simulation landing；
Alert algoritic module (72), for simulated flight is carried out according to the simulation aircraft or when simulation is landed related data with it is pre-
Determine alarm data and predetermined alarm data of cancelling is compared, judge the alert mode of the simulation aircraft.
3. aircraft Distal promoter according to claim 2 tests system, which is characterized in that the warning system (6) includes
Alarm prompt lamp (61), language alarm device (62) and display alarm device (63).
4. aircraft Distal promoter according to claim 2 tests system, which is characterized in that the alarm mould of the simulation aircraft
Formula includes：
The alarm of excessive fall rate, the alarm of excessive near-earth rate, fall after taking off height alarm, the alarm of incorrect landing configuration with
And it is excessively alerted less than glide path.
5. aircraft Distal promoter according to claim 4 tests system, which is characterized in that the excessive fall rate alarm
Under pattern, predetermined alarm data is radio altitude 475.3m, subsidence velocity 19.6m/s, and it is wireless to make a reservation for cancel alarm data
Electrical height 224.7m, subsidence velocity 9m/s；
Under the excessive near-earth rate alert mode, predetermined alarm data is radio altitude 322.6m, crust deformation rate
22.7m/s makes a reservation for cancel alarm data as radio altitude 178, crust deformation rate 6.3m/s；
It is described take off after fall under height alert mode, predetermined alarm data be radio altitude 163.4m, make a reservation for cancel alarm number
According to for radio altitude 180.1m；
Under the incorrect landing configuration alert mode, predetermined alarm data is in collapsed state, radio height for undercarriage
150.5m is spent, makes a reservation for cancel alarm data as radio altitude 49.6m, gear down；
It is described excessively less than under glide path alert mode, predetermined alarm data implements microwave landing approach, wireless for simulation aircraft
Electrical height is less than 300m, is deflected downwardly glide path center line more than 0.11385DDM, and it is radio altitude to make a reservation for cancel alarm data
Less than 90m, glide path center line is deflected downwardly more than 0.1750DDM.
Priority Applications (1)
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| CN201711482060.1A CN108238284A (en) | 2017-12-29 | 2017-12-29 | A kind of aircraft Distal promoter tests system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711482060.1A CN108238284A (en) | 2017-12-29 | 2017-12-29 | A kind of aircraft Distal promoter tests system |
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Cited By (9)
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| CN109144079A (en) * | 2018-08-22 | 2019-01-04 | 中国民航大学 | A kind of amphibious aircraft landing configuration control system based on integrated avionics |
| CN109896046A (en) * | 2017-12-11 | 2019-06-18 | 上海航空电器有限公司 | A kind of forward sight prediction alarm function test method of enhanced ground proximity warning system (EGPWS) |
| CN111123966A (en) * | 2019-12-26 | 2020-05-08 | 陕西宝成航空仪表有限责任公司 | Method for judging flight phase based on airborne ground proximity warning system |
| CN111308455A (en) * | 2020-03-18 | 2020-06-19 | 中国商用飞机有限责任公司 | Method and system for determining the ground clearance of an aircraft |
| CN111435572A (en) * | 2019-01-12 | 2020-07-21 | 上海航空电器有限公司 | Multi-purpose ground proximity warning system simulation demonstration platform structure based on terrain database |
| CN111311968B (en) * | 2020-03-30 | 2021-06-04 | 中国人民解放军陆军航空兵学院陆军航空兵研究所 | Ground proximity warning method and device for helicopter |
| CN112927564A (en) * | 2021-03-08 | 2021-06-08 | 中国电子科技集团公司第二十研究所 | Radio altitude abnormity detection and reconstruction method in ground proximity alarm system |
| CN113568437A (en) * | 2021-09-27 | 2021-10-29 | 西安羚控电子科技有限公司 | Air-drop system and air-drop control method for large and medium-sized fixed wing unmanned aerial vehicle |
| CN113792382A (en) * | 2021-09-10 | 2021-12-14 | 中国航空工业集团公司西安飞行自动控制研究所 | Multi-task mode ground proximity warning method based on machine learning |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109896046A (en) * | 2017-12-11 | 2019-06-18 | 上海航空电器有限公司 | A kind of forward sight prediction alarm function test method of enhanced ground proximity warning system (EGPWS) |
| CN109896046B (en) * | 2017-12-11 | 2023-06-30 | 上海航空电器有限公司 | EGPWS forward-looking prediction alarm function test method |
| CN109144079A (en) * | 2018-08-22 | 2019-01-04 | 中国民航大学 | A kind of amphibious aircraft landing configuration control system based on integrated avionics |
| CN111435572A (en) * | 2019-01-12 | 2020-07-21 | 上海航空电器有限公司 | Multi-purpose ground proximity warning system simulation demonstration platform structure based on terrain database |
| CN111123966A (en) * | 2019-12-26 | 2020-05-08 | 陕西宝成航空仪表有限责任公司 | Method for judging flight phase based on airborne ground proximity warning system |
| CN111308455A (en) * | 2020-03-18 | 2020-06-19 | 中国商用飞机有限责任公司 | Method and system for determining the ground clearance of an aircraft |
| CN111308455B (en) * | 2020-03-18 | 2022-04-19 | 中国商用飞机有限责任公司 | Method and system for determining the ground clearance of an aircraft |
| CN111311968B (en) * | 2020-03-30 | 2021-06-04 | 中国人民解放军陆军航空兵学院陆军航空兵研究所 | Ground proximity warning method and device for helicopter |
| CN112927564A (en) * | 2021-03-08 | 2021-06-08 | 中国电子科技集团公司第二十研究所 | Radio altitude abnormity detection and reconstruction method in ground proximity alarm system |
| CN113792382A (en) * | 2021-09-10 | 2021-12-14 | 中国航空工业集团公司西安飞行自动控制研究所 | Multi-task mode ground proximity warning method based on machine learning |
| CN113568437A (en) * | 2021-09-27 | 2021-10-29 | 西安羚控电子科技有限公司 | Air-drop system and air-drop control method for large and medium-sized fixed wing unmanned aerial vehicle |
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Application publication date: 20180703 |