CN108100298A - A kind of test method for aircraft terrain awareness warning system - Google Patents
A kind of test method for aircraft terrain awareness warning system Download PDFInfo
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- CN108100298A CN108100298A CN201711239952.9A CN201711239952A CN108100298A CN 108100298 A CN108100298 A CN 108100298A CN 201711239952 A CN201711239952 A CN 201711239952A CN 108100298 A CN108100298 A CN 108100298A
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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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- Aviation & Aerospace Engineering (AREA)
- Alarm Systems (AREA)
- Emergency Alarm Devices (AREA)
- Traffic Control Systems (AREA)
Abstract
The present invention relates to flight system testing field, more particularly to a kind of test method for aircraft terrain awareness warning system, including radio altitude sensor, atmospheric engine sensor, flap position transducer, alarm indicator and voice alarm；Test method following steps：Above-mentioned device is attached by bus；One integrated data converter is set, and passes through bus and is connected respectively with radio altitude sensor, atmospheric engine sensor and flap position transducer；Aircraft terrain awareness warning system is connected to flight simulator, carries out test flight；Successively to rate of descent, close to landform rate, take off after rate of descent, non-landing type hit under ground, opposite glide path rate, the anticollision of forward sight landform partially and decline and test too early.The test method for aircraft terrain awareness warning system of the present invention, can test aircraft terrain awareness warning system, ensure performance higher, and cost is lower.
Description
Technical field
The present invention relates to flight system testing fields, more particularly to a kind of survey for aircraft terrain awareness warning system
Method for testing.
Background technology
In many aircraft accidents of modern Aviation, caused by being not due to the aircrafts such as power failure reasons itself,
But in the case of controllable, ground or the accident that falls into the sea are hit due to lacking to the perception of landform.For such accident, lead to
Frequently referred to controllably hit (CFIT) accident.
In order to overcome the above problem, there is aircraft landform hint and caveat system (TAWS)；Which increase forward sight landform
Function is advanced by the pre-warning time of system significantly, to pilot's more reaction time, so as to be effectively prevented from controllably hitting ground thing
Therefore generation.But the test of aircraft terrain awareness warning system at present is carried out on entity aircraft, security performance is protected
Hinder low and somewhat expensive.
The content of the invention
The object of the present invention is to provide a kind of test methods for aircraft terrain awareness warning system.
The technical scheme is that：
A kind of test method for aircraft terrain awareness warning system, in the aircraft terrain awareness warning system
Including radio altitude sensor, atmospheric engine sensor, flap position transducer, alarm indicator and voice alarm, bag
Include following steps：
Step 1: the radio altitude sensor, the atmospheric engine sensor, the flap configuration are passed by bus
Sensor, the alarm indicator and the voice alarm are attached；
Step 2: set an integrated data converter, and pass through bus respectively with the radio altitude sensor, institute
State atmospheric engine sensor and flap position transducer connection；
Step 3: the aircraft terrain awareness warning system is connected to flight simulator, test flight is carried out；
Step 4: successively to rate of descent, close to landform rate, take off after rate of descent, non-landing type hit ground, opposite glide path
Inclined rate, the anticollision of forward sight landform and decline are tested too early down.
Optionally, when the rate of descent is tested, the air speed of 3000ft/min is inputted by the integrated data converter
Value so that the flight simulator simulates the state of flight under the conditions of the air speed value, and the alarm indicator flicker, described at this time
Voice alarm is prompted, and represents that rate of descent is excessive.
Optionally, in the rate close to landform, input 500ft-1000ft's by the integrated data converter
Height value so that the flight simulator simulates the state of flight under the conditions of the height value, at this time the alarm indicator flicker,
The voice alarm prompting, represents excessive close to landform rate.
Optionally, after described take off during rate of descent, the height value of 700ft is inputted by the integrated data converter,
So that the flight simulator simulates the state of flight under the conditions of the height value, and the alarm indicator flicker at this time, institute's predicate
Sound alarm device is prompted, and rate of descent is excessive after expression is taken off.
Optionally, when the non-landing type is tested with hitting, the height of 200m is inputted by the integrated data converter
Value so that the flight simulator simulates the state of flight under the conditions of the height value, and the alarm indicator flicker, described at this time
Voice alarm is prompted, and expression hits ground.
Optionally, inputted down respectively by the integrated data converter during rate test partially under the opposite glide path
Slideway 1.3dot and 2dot so that the flight simulator simulates the state of flight under the conditions of the glide path, at this time the alarm
Indicator light flickers, the voice alarm prompting, represents that rate partially is too small under opposite glide path.
Optionally, in the forward sight landform anticollision, the height value of 300ft is inputted by the integrated data converter,
So that the flight simulator simulates the state of flight under the conditions of the height value, and the alarm indicator flicker at this time, institute's predicate
Sound alarm device is prompted, and expression will hit mountain.
Optionally, when the decline is too early, pass through the integrated data converter and distinguish transmission range airport 10nm, height
Spend 3 ° of 1500ft and gliding angle so that the flight simulator simulates the state of flight under the conditions of the state value, described at this time
Alarm indicator flickers, and the voice alarm prompting, it is too early to represent to decline.
Invention effect：
The test method for aircraft terrain awareness warning system of the present invention can be prompted and alerted to aircraft landform
System is tested, and ensures performance higher, and cost is lower.
Description of the drawings
Fig. 1 is flow chart of the present invention for the test method of aircraft terrain awareness warning system.
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 there is same or like element.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, belong to the scope of protection of the 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 scope.
1 pair of test method for aircraft terrain awareness warning system of the invention is done further in detail below in conjunction with the accompanying drawings
It describes in detail bright.
A kind of test method for aircraft terrain awareness warning system；Wherein, aircraft terrain awareness warning system
Belong to existing structure, be to be tested, test is installed in actual airplane after passing through and uses.In addition, aircraft landform is prompted
With generally included in warning system radio altitude sensor, atmospheric engine sensor, flap position transducer, alarm indicator with
And voice alarm.
The test method for aircraft terrain awareness warning system of the present invention may include steps of：
Step 1: using each component connection mode being currently known, by bus and by radio altitude sensor, air
Machine sensor, flap position transducer, alarm indicator and voice alarm are attached.
Step 2: set an integrated data converter, and pass through bus respectively with radio altitude sensor, atmospheric engine
Sensor and flap position transducer connection.
Step 3: aircraft terrain awareness warning system is connected to flight simulator, test flight is carried out；Wherein, fly
The simulator for the kinds of experiments room being currently known may be employed in row simulator.
Step 4: successively to rate of descent, close to landform rate, take off after rate of descent, non-landing type hit ground, opposite glide path
Inclined rate, the anticollision of forward sight landform and decline are tested too early down.
Specifically, when rate of descent is tested, the air speed value of 3000ft/min is inputted by integrated data converter so that fly
Row simulator simulates the state of flight under the conditions of the air speed value, and alarm indicator flickers at this time, voice alarm prompting, under expression
Drop rate is excessive, so as to illustrate that rate of descent alarm function is normal；Opposite test of starting from scratch, this method are more convenient convenient.
When close to landform rate, the height value of 500ft-1000ft is inputted by integrated data converter so that flight
Simulator simulates the state of flight under the conditions of the height value, and alarm indicator flickers at this time, and voice alarm prompting represents close
Landform rate is excessive.
After take off during rate of descent, the height value of 700ft is inputted by integrated data converter so that flight simulator mould
Intend the state of flight under the conditions of the height value, alarm indicator flickers at this time, voice alarm prompting, rate of descent after expression is taken off
It is excessive.
When non-landing type is tested with hitting, the height value of 200m is inputted by integrated data converter so that flight simulation
Device simulates the state of flight under the conditions of the height value, and alarm indicator flickers at this time, and voice alarm prompting, expression hits ground.
Under opposite glide path during inclined rate test, it is (less than normal that glide path 1.3dot is inputted by integrated data converter respectively
State) and 2dot (state bigger than normal) so that flight simulator simulates the state of flight under the conditions of the glide path, at this time alarm instruction
Lamp flickers, voice alarm prompting, represents that rate partially is too small or excessive under opposite glide path.
In forward sight landform anticollision, the height value of 300ft is inputted by integrated data converter so that flight simulator mould
Intend the state of flight under the conditions of the height value, alarm indicator flickers at this time, and voice alarm prompting, expression will hit mountain.
When declining too early, by integrated data converter distinguish transmission range airport 10nm, height 1500ft and under
Sliding 3 ° of angle so that flight simulator simulates the state of flight (towards aerodrome flight) under the conditions of the state value, at this time alarm indicator
Flicker, voice alarm prompting, it is too early to represent to decline.
The test method for aircraft terrain awareness warning system of the present invention can be prompted and alerted to aircraft landform
System is tested, and ensures performance higher, and cost is lower.
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 (8)
1. a kind of test method for aircraft terrain awareness warning system, wrapped in the aircraft terrain awareness warning system
Radio altitude sensor, atmospheric engine sensor, flap position transducer, alarm indicator and voice alarm are included, it is special
Sign is, includes the following steps：
Step 1: the radio altitude sensor, the atmospheric engine sensor, the flap configuration are sensed by bus
Device, the alarm indicator and the voice alarm are attached；
Step 2: set an integrated data converter, and pass through bus respectively with the radio altitude sensor, described big
Mechanism of qi sensor and flap position transducer connection；
Step 3: the aircraft terrain awareness warning system is connected to flight simulator, test flight is carried out；
Step 4: successively to rate of descent, close to landform rate, take off after rate of descent, non-landing type hit under ground, opposite glide path partially
Rate, the anticollision of forward sight landform and decline are tested too early.
2. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
When stating rate of descent test, the air speed value of 3000ft/min is inputted by the integrated data converter so that the flight simulation
Device simulates the state of flight under the conditions of the air speed value, at this time the alarm indicator flicker, and the voice alarm prompting represents
Rate of descent is excessive.
3. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
When stating close to landform rate, the height value of 500ft-1000ft is inputted by the integrated data converter so that the flight
Simulator simulates the state of flight under the conditions of the height value, at this time the alarm indicator flicker, the voice alarm prompting,
It represents excessive close to landform rate.
4. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
When stating rate of descent after taking off, the height value of 700ft is inputted by the integrated data converter so that the flight simulator mould
Intend the state of flight under the conditions of the height value, at this time the alarm indicator flicker, the voice alarm prompting represents to take off
Rate of descent is excessive afterwards.
5. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
When stating non-landing type and testing with hitting, pass through the height value that the integrated data converter inputs 200m so that the flight simulation
Device simulates the state of flight under the conditions of the height value, at this time the alarm indicator flicker, and the voice alarm prompting represents
Hit ground.
6. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
When stating inclined rate test under opposite glide path, glide path 1.3dot and 2dot are inputted by the integrated data converter respectively, made
The flight simulator simulates state of flight under the conditions of the glide path, the alarm indicator flicker at this time, the voice
Alarm device is prompted, and represents that rate partially is too small under opposite glide path.
7. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
When stating forward sight landform anticollision, the height value of 300ft is inputted by the integrated data converter so that the flight simulator mould
Intend the state of flight under the conditions of the height value, at this time the alarm indicator flicker, the voice alarm prompting, expression will
Hit mountain.
8. the test method according to claim 1 for aircraft terrain awareness warning system, which is characterized in that in institute
It states when declining too early, passes through the integrated data converter and distinguish transmission range airport 10nm, height 1500ft and gliding angle
3 ° so that the flight simulator simulates the state of flight under the conditions of the state value, and the alarm indicator flicker, described at this time
Voice alarm is prompted, and it is too early to represent to decline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711239952.9A CN108100298A (en) | 2017-11-30 | 2017-11-30 | A kind of test method for aircraft terrain awareness warning system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711239952.9A CN108100298A (en) | 2017-11-30 | 2017-11-30 | A kind of test method for aircraft terrain awareness warning system |
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| Publication Number | Publication Date |
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| CN108100298A true CN108100298A (en) | 2018-06-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711239952.9A Pending CN108100298A (en) | 2017-11-30 | 2017-11-30 | A kind of test method for aircraft terrain awareness warning system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112027107A (en) * | 2019-06-04 | 2020-12-04 | 丰鸟航空科技有限公司 | Unmanned aerial vehicle avoidance test system, method and device, terminal equipment and storage medium |
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| US20070069944A1 (en) * | 2005-09-29 | 2007-03-29 | Buell Robert K | Simulated radar system and methods |
| CN104992587A (en) * | 2015-07-06 | 2015-10-21 | 南京航空航天大学 | Analog simulation system |
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| CN105513305A (en) * | 2015-11-26 | 2016-04-20 | 南京莱斯信息技术股份有限公司 | TAWS module simulation test platform |
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Patent Citations (5)
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| US20070069944A1 (en) * | 2005-09-29 | 2007-03-29 | Buell Robert K | Simulated radar system and methods |
| CN104992587A (en) * | 2015-07-06 | 2015-10-21 | 南京航空航天大学 | Analog simulation system |
| CN105513305A (en) * | 2015-11-26 | 2016-04-20 | 南京莱斯信息技术股份有限公司 | TAWS module simulation test platform |
| CN105427379A (en) * | 2015-12-02 | 2016-03-23 | 上海航空电器有限公司 | Flight visual simulation system for testing ground proximity warning system |
| CN205621313U (en) * | 2016-03-29 | 2016-10-05 | 西京学院 | Aerial anticollision of aircraft and integrated system who closely reports an emergency and asks for help or increased vigilance |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112027107A (en) * | 2019-06-04 | 2020-12-04 | 丰鸟航空科技有限公司 | Unmanned aerial vehicle avoidance test system, method and device, terminal equipment and storage medium |
| CN112027107B (en) * | 2019-06-04 | 2022-03-11 | 丰鸟航空科技有限公司 | Unmanned aerial vehicle avoidance test system, method and device, terminal equipment and storage medium |
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Application publication date: 20180601 |
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