CN105644802B - Wing flap zero-bit self-adaptive identification method - Google Patents
Wing flap zero-bit self-adaptive identification method Download PDFInfo
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- CN105644802B CN105644802B CN201410707640.6A CN201410707640A CN105644802B CN 105644802 B CN105644802 B CN 105644802B CN 201410707640 A CN201410707640 A CN 201410707640A CN 105644802 B CN105644802 B CN 105644802B
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Abstract
The present invention provides a kind of wing flap zero-bit self-adaptive identification method for aircraft ground proximity warning system, the tap of flap position transducer first and flap position transducer the second tap output voltage is divided into several are interval by flap angle, by judging current flap position transducer the first tap output voltage and judging flap state with whether current the second tap output of flap position transducer voltage falls into above-mentioned interval.The present invention provides a kind of wing flap zero-bit self-adaptive identification method for the ground proximity warning system being assemblied on certain large transport airplane.When the type transporter is carrying out wing flap assembling; a kind of method of quick zero-bit self-adapting estimation is provided; provided safeguard so as to accurately obtain current aircraft flap state for ground proximity warning system, provide protection for the safe flight of aircraft, reduce security incident caused by non-artificial factor.
Description
Technical field
The present invention relates to a kind of wing flap zero-bit recognition methods in aircraft Distal promoter field, it is used to fly more particularly, to one kind
The wing flap zero-bit self-adaptive identification method of machine ground proximity warning system, is used particular for large transport airplane in zero adjustment.
Technical background
It is that landing state also right and wrong, it is necessary to obtain aircraft flap current state in aircraft ground proximity warning system algorithm
Land state, to carry out mode decision, and then ensures the flight safety of aircraft.It is according to the wing flap that takes off of flight airmanship regulation aircraft
15 °, landing wing flap is 30 °.Ordinary circumstance, which is got off the plane, can directly provide current state, i.e. landing state（1）Or non-landing shape
State（0）.As shown in figure 1, the type transporter provides corresponding two taps by flap position transducer（I.e. flap configuration is passed
The first tap of sensor BJ2, the second tap of flap position transducer BJ3）Voltage, ground proximity warning system is only entered by related algorithm
Row resolves and just can determine that current flap angle, and then judges current flap state.While the type aircraft flap position sensing
Utensil has uncertainty --- and 0 ° of same position, output tap position difference is larger, therefore wing flap is needed when working aboard
By machinery compared with zero, that is, the judgment standard of flap state angle is produced, wing flap zero-bit self-adaptive identification method can be quickly adaptive
The zero-bit of current aircraft should be recognized, and gives quick correction in time.
The content of the invention
There is provided a kind of wing flap zero-bit for aircraft ground proximity warning system is adaptive for deficiency of the prior art by the present invention
Answer recognition methods.
To achieve these goals, the present invention is achieved by the following technical solutions：One kind is used for aircraft Distal promoter
The wing flap zero-bit self-adaptive identification method of system, it is characterised in that sense the tap of flap position transducer first and flap configuration
Device the second tap output voltage is divided into several intervals by flap angle, by judging that current flap position transducer first is taken out
Head output voltage and wing flap shape is judged with whether current the second tap output of flap position transducer voltage falls into above-mentioned interval
State.
According to a particular embodiment of the invention, the wing flap zero-bit self-adaptive identification method, comprises the following steps：
Step 1: the tap of flap position transducer first and flap position transducer the second tap output voltage are remembered respectively
For A, B, flap angle is divided into N+1 angle by scale, while by the tap of flap position transducer first under above-mentioned angle
Output voltage note A [0] ~ A [N], the output voltage of the tap of flap position transducer second is designated as B [0] ~ B [N] ,+27V voltages
Value is designated as C [0], is designated as D [0] wing flap；
Step 2: setting flap position transducer the first tap output voltage and the tap output of flap position transducer second
The judgement of voltage is interval, first determine whether flap position transducer the first tap output voltage A A [0] ~ A [N] whether monotonic increase
Or monotone decreasing, then judge that A [0] ~ A [N] is monotonic increase or monotone decreasing again in this way, wing flap is set if monotonic increase
Position sensor the first tap output voltage judges interval for each interval and A [N] and C [0] interval between A [0] ~ A [N]；
Flap position transducer the first tap output voltage is set if monotone decreasing and judges interval for each interval between A [0] ~ A [N]
And A [N] and D [0] is interval；As A [0] ~ A [N] be not monotonic increase or monotone decreasing, then find Long-term change trend point A [P] and
B [P], judges that A [0] ~ A [P] is monotonic increase or monotone decreasing, if monotonic increase, sets flap position transducer first
Tap output voltage judges interval for each interval and A [P] and C [0] interval between A [0] ~ A [P]；If monotone decreasing, set
Determine flap position transducer the first tap output voltage and judge interval for each interval and A [P] and D [0] between A [0] ~ A [P]
Interval, the judgement of same setting flap position transducer the second tap output voltage is interval；
Step 3: collection wing flap supply voltage, judges whether wing flap sensor has electricity, no electricity is then defaulted as wing flap and packed up；
If there is electricity, by the voltage X of the current tap of flap position transducer first, the voltage of the tap of current flap position transducer second
Y is carried out by step 4；
Step 4: being tested according to the judgement interval set in step 2, current flap position transducer first is judged
The voltage X of tap judges interval with the presence or absence of the first tap output of flap position transducer voltage, and current flap configuration is passed
The voltage Y of the tap of sensor second judges interval interior with the presence or absence of the second tap output of flap position transducer voltage, such as two
Person exists and is present in same group of judgement interval, then it is that 1, i.e. wing flap land to show flap state, otherwise shows wing flap shape
State is 0, i.e. wing flap is packed up.
The present invention provides a kind of wing flap zero-bit self-adapting estimation for the ground proximity warning system being assemblied on certain large transport airplane
Method.When the type transporter is carrying out wing flap assembling there is provided a kind of method of quick zero-bit self-adapting estimation, so as to be near
Ground warning system accurately obtains current aircraft flap state and provided safeguard, and provides protection for the safe flight of aircraft, reduces inhuman
For security incident caused by factor.
Brief description of the drawings
Fig. 1 is the schematic diagram of the flap position transducer of the present invention.
Fig. 2 is the FB(flow block) of wing flap school zero of the invention.
Embodiment
The invention provides a kind of wing flap zero-bit self-adaptive identification method for aircraft ground proximity warning system, including it is following
Step：
Step one, the tap of flap position transducer first and flap position transducer the second tap output voltage are remembered respectively
For A, B, flap angle is divided into 20 °, 25 °, 30 °, 35 °, 38 ° by scale, while flap configuration under above-mentioned angle is sensed
The output voltage of the tap of device first is designated as A [0], A [1], A [2], A [3], A [4], the output of the tap of flap position transducer second
Voltage is designated as B [0], B [1], B [2], B [3], B [4], and 27V magnitudes of voltage are designated as C [0], D [0] are designated as, in wing flap school zero wing flap
Before, magnitude of voltage under above-mentioned correspondence flap angle is recorded into Distal promoter signal boxcar, and creates data link table.
Step 2：Judge A, B A [0] ~ A [4] and B [0] ~ B [4] whether monotonic increase or monotone decreasing, if change
Trend is identical, then without operation.If it is not the same, then note Long-term change trend interval A [X] is AP, continuation judges that AP is after being first incremented by
Successively decrease still first to successively decrease and be incremented by afterwards.If the former, then by AP interval extensions to C [0]；If the latter converts trend, then by AP
Interval extension is to D [0].B is equally operated.Because A [0] ~ A [4] maximum voltage is not more than+27V, therefore it is incremented by the ban
When, it is by interval extension to C [0], i.e., to be incremented by A [0] ~ C [0]；When successively decreasing in the ban, by interval extension to D [0], i.e., A [0] ~
D [0] successively decreases.
Step 3：Wing flap school zero starts, and wing flap supply voltage is gathered first, judges whether wing flap sensor has electricity, no electricity
Wing flap is then defaulted as to pack up；If there is electricity, by the voltage of the first tap of current flap configuration voltage signal flap position transducer
（X）, the tap of flap position transducer second voltage（Y）Carried out by step 4；
Step 4：Tested according to the flap angle order of division, and sequentially will be designated as i, i=0,1,2,3,4,5, it is suitable
Whether sequence searches A in A [i] and A [i+1]（If A [i] is that Long-term change trend is interval, interval extension is carried out according to step 2）Between,
And record in the presence of interval i values；If there are two groups of A [i] to meet condition with A [i+1], carried out according to step 5；If there is a kind of A
[i] and A [i+1] meet condition, then are carried out according to step 6；If not meeting the interval of condition, carried out according to step 8.
Step 5：Verify Y value whether between corresponding B groups（The B [i] corresponding to two groups of i values found in step 4）,
And record qualified one group of i value, it is designated as Z（Similar processing below）, into step 7；If it is not satisfied, then entering
Step 8.
Step 6：Verify Y value whether between corresponding B groups（The B [i] corresponding to one group of i value found in step 4）；
If meeting, i values are recorded, into step 7；Enter step 8 if not meeting.
Step 7：Z is compared with 1, so that it is determined that whether flap configuration angle is more than 25 °：If Z>1, then show the flap
Wing state is 1（I.e. wing flap is put down）；If Z<1, then it is 0 to show flap state（I.e. wing flap is packed up）.
Step 8：It is 0 to show flap state（I.e. wing flap is packed up）.
Step 9：Zero-bit end of identification.
The following is the specific embodiment of the present invention.
101st, system electrification collects BJ_2 electricity corresponding with BJ_3 ends when flap state is 20 °, 25 °, 30 °, 35 °, 38 °
Press as+12V ,+15V ,+18V ,+21V, 22.8V, be respectively labeled as A [0] ~ A [4], B [0] ~ B [4], and set up the current aircraft flap
Wing slip condition database；
102nd, system operation, the voltage of the tap of flap position transducer first collected（X）, flap position transducer
The voltage of two taps（Y）Respectively+16.8V and+22V, into 103；
103rd, above-mentioned voltage X, Y gathered in real time and current aircraft flap state data are compared, due to current X and
Y is respectively that+16.8V ,+22V, i.e. wing flap are to have voltage output state, therefore enters 104；
104th, by the voltage of the tap of flap position transducer first（X）Comparing is carried out with A [0] ~ A [4] successively,, now、, judge whether, return 104 is unsatisfactory for, until meeting,
Now, record now, into 105；
105th, judge whether, meet condition, therefore enter 106；
106th, judge whether, the condition of being unsatisfactory for, therefore order are learnt according to condition, into 107；
107th, judge whether, i.e.,, now, therefore, i.e.,, now, i.e.,
, carry out computing, into 108；
108th, judge whether, the condition that meets then return 108 by processing computings obtain finalWhen, now, into 109；
109th, judge whether, calculate and obtain, into 110；
110th, wing flap is put down, and display is state " 1 ", and enters 111；
111st, system testing terminates.
Claims (1)
1. wing flap zero-bit self-adaptive identification method, includes, by the tap of flap position transducer first and flap position transducer
Second tap output voltage is divided into several intervals by flap angle, by judging the current tap of flap position transducer first
Output voltage and flap state is judged with whether current the second tap output of flap position transducer voltage falls into above-mentioned interval,
Characterized in that, this method further comprises the steps：
Step 1: by the tap of flap position transducer first and flap position transducer the second tap output voltage be designated as respectively A,
B, N+1 angle is divided into by flap angle by scale, at the same by under above-mentioned angle the tap of flap position transducer first it is defeated
Go out voltage note A [0] ~ A [N], the output voltage of the tap of flap position transducer second is designated as B [0] ~ B [N] ,+27V magnitudes of voltage note
For C [0], it is designated as D [0] wing flap；
Step 2: setting flap position transducer the first tap output voltage and flap position transducer the second tap output voltage
Judgement it is interval, first determine whether flap position transducer the first tap output voltage A A [0] ~ A [N] whether monotonic increase or
Monotone decreasing, then judges that A [0] ~ A [N] is monotonic increase or monotone decreasing, flap configuration is set if monotonic increase again in this way
Sensor the first tap output voltage judges interval for each interval and A [N] and C [0] interval between A [0] ~ A [N]；Such as list
Tune successively decrease then setting flap position transducer the first tap output voltage judge it is interval for each interval between A [0] ~ A [N] and
A [N] and D [0] is interval；Such as A [0] ~ A [N] is not monotonic increase or monotone decreasing, then finds Long-term change trend point A [P] and B
[P], judges that A [0] ~ A [P] is monotonic increase or monotone decreasing, if monotonic increase, and setting flap position transducer first is taken out
Head output voltage judges interval for each interval and A [P] and C [0] interval between A [0] ~ A [P]；If monotone decreasing, set
Flap position transducer the first tap output voltage judges interval for each interval and A [P] and D [0] area between A [0] ~ A [P]
Between, the judgement of same setting flap position transducer the second tap output voltage is interval；
Step 3: collection wing flap supply voltage, judges whether wing flap sensor has electricity, no electricity is then defaulted as wing flap and packed up；If having
Electricity, then the voltage Y by the voltage X of the current tap of flap position transducer first, the tap of current flap position transducer second press
Step 4 is carried out；
Step 4: being tested according to the judgement interval set in step 2, the current tap of flap position transducer first is judged
Voltage X judge interval, current flap position transducer with the presence or absence of the first tap output of flap position transducer voltage
The voltage Y of second tap is judged in interval with the presence or absence of the second tap output of flap position transducer voltage, as both
In the presence of and be present in same group of judgement it is interval in, then it is 1 show flap state, i.e. wing flap landing, otherwise shows that flap state is
0, i.e. wing flap are packed up.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410707640.6A CN105644802B (en) | 2014-11-28 | 2014-11-28 | Wing flap zero-bit self-adaptive identification method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410707640.6A CN105644802B (en) | 2014-11-28 | 2014-11-28 | Wing flap zero-bit self-adaptive identification method |
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| CN105644802A CN105644802A (en) | 2016-06-08 |
| CN105644802B true CN105644802B (en) | 2017-08-25 |
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| CN110667885B (en) * | 2019-09-25 | 2023-02-10 | 西北工业大学 | Reliability test method for airplane flap slat movement mechanism |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101799689A (en) * | 2010-04-08 | 2010-08-11 | 中国电子科技集团公司第三十八研究所 | Dual-redundancy steering engine controller |
| CN102706271A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Redundancy device for angle position sensors of control plane of steering engine and control method for device |
| CN203053397U (en) * | 2012-11-16 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Tab position meter tester |
| CN104097790A (en) * | 2014-07-28 | 2014-10-15 | 贵州航天风华精密设备有限公司 | Debug method of control mechanism of spacecraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007190985A (en) * | 2006-01-18 | 2007-08-02 | Honda Motor Co Ltd | Steering device for vehicle |
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- 2014-11-28 CN CN201410707640.6A patent/CN105644802B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101799689A (en) * | 2010-04-08 | 2010-08-11 | 中国电子科技集团公司第三十八研究所 | Dual-redundancy steering engine controller |
| CN102706271A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Redundancy device for angle position sensors of control plane of steering engine and control method for device |
| CN203053397U (en) * | 2012-11-16 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Tab position meter tester |
| CN104097790A (en) * | 2014-07-28 | 2014-10-15 | 贵州航天风华精密设备有限公司 | Debug method of control mechanism of spacecraft |
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