CN113428381A - Device and method for determining time period of catapult impact action of airplane suspension - Google Patents
Device and method for determining time period of catapult impact action of airplane suspension Download PDFInfo
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention relates to a device and a method for determining a time period of catapult impact action of an airplane suspension, belongs to the field of flight measurement, and solves the problems of complex measurement system and low measurement precision in the process of determining the time period of catapult impact action in the prior art. According to the method, an impact measuring sensor and an overload measuring sensor are arranged on a suspended object, and then a ground ejection test is carried out to obtain an impact signal curve and an overload signal curve; and determining an ejection impact starting time t1, a suspension object grounding time t3 and an ejection impact ending time t4 according to the two curves to finally obtain an ejection impact action time period [ t1, t4 ].
Description
Technical Field
The invention relates to the technical field of flight measurement, in particular to a device and a method for determining an action time period of ejection impact of an airplane suspension object.
Background
When the aircraft suspension is separated from the aircraft, the modes of ejection, guide rail launching, gravity launching and the like are generally adopted, wherein the ejection separation mode is widely used because the separation speed is relatively high, the power of the suspension is not needed, and the safety of the aircraft is high.
The aircraft suspension is subjected to the action of ejection impact in the ejection separation process, so that the ejection impact condition needs to be provided for verifying whether the aircraft suspension is resistant to the ejection impact environment. In order to accurately set the ejection impact condition, the ejection impact environment is measured in a ground ejection test, and the measurement result is shown in fig. 1.
In order to determine the action time period of the ejection impact, an ejection starting signal is led out from the ejection device, and a launching device-suspension separation signal is led out from the suspension; or a timing device is adopted to send out signals, timing signals are recorded by high-speed photography and impact measurement equipment at the same time, and the starting time and the ending time of ejection impact are judged according to the high-speed photography after the test.
In both methods, an additional device is required for determining the impact action time period, the system is relatively complex, and the test cost is increased.
In addition, in the existing process of determining the time period of the catapult impact action, due to the existence of measurement errors, impact signals caused by the fact that a suspended object touches the ground are often mistakenly taken as catapult impact signals, and the time period measurement accuracy is low.
Disclosure of Invention
In view of the foregoing analysis, embodiments of the present invention provide an apparatus and a method for determining an action time period of an aircraft suspension catapult impact, so as to solve the problems of complexity and low measurement accuracy of a measurement apparatus in the existing process for determining an action time period of an aircraft suspension catapult impact.
On one hand, the embodiment of the invention provides a method for determining an action time period of ejection impact of an airplane suspension object, which comprises the following steps:
arranging an impact measuring sensor and an overload measuring sensor on the suspension;
carrying out a ground ejection test, and obtaining a suspension impact signal and an overload signal to form an impact signal curve and an overload signal curve;
determining an ejection impact starting time t1, a suspension object grounding time t3 and an ejection impact ending time t4 based on the impact signal curve and the overload signal curve;
and determining the catapult impact action time period, namely [ t1, t4 ].
Further, the determining of the ejection impact start time t1 includes: the initial noise N1 is found in the impact signal curve, and the t1 is the time corresponding to the last impact signal before the catapult impact signal amplitude reaches m times the initial noise N1 for the first time.
Further, the determining a ground contact time t3 includes: finding out a characteristic segment conforming to the change-zero-change-shock attenuation in the overload signal curve, and taking the starting point of the time segment with the amplitude of zero as the aircraft-suspended object separation time t2 and the end point of the time segment with the amplitude of zero as the suspended object touchdown time t 3.
Further, the determining of the ejection impact end time t4 includes: and finding out the maximum impact amplitude Amax before the ground contact time t3 of the suspended object from the impact signal curve, wherein the time corresponding to the last impact signal with the amplitude p.Amax before t3 is the ejection impact end time t 4.
Further, the value of m is 1.3-2; the value of p is 8-13%.
Further, the impact measurement sensor is arranged at a position with good rigidity of the suspension, and the measurement direction is X, Y, Z direction; the overload measuring sensor is arranged at the position of the center of mass of the suspended object, and the measuring direction is X, Y, Z, or the measuring direction is measured in all three directions.
Further, the measuring range of the impact measuring sensor is +/-500 g; the overload measuring sensor is a capacitance type or piezoresistive overload sensor with zero-frequency measuring capacity, and the measuring range is +/-50 g; the frequency ranges of the two sensors are 10 Hz-2000 HZ.
Further, the ejection impact starting time t1 is taken as t1- Δ t, the ejection impact ending time t4 is taken as (t3+ t4)/2, and the Δ t is 10-50 ms.
In another aspect, the present application further provides an aircraft suspension object ejection impact action time period determination device, which includes the following components:
the impact measuring sensor and the overload measuring sensor are both arranged on the suspension object and are respectively used for measuring an impact signal and an overload signal of the suspension object;
the data acquisition unit is connected with the impact measurement sensor and the overload measurement sensor and is used for acquiring impact signals and overload signals of a suspended object in the ground ejection test process to form an impact signal curve and an overload signal curve;
and the data processing unit is connected with the data acquisition unit and determines an impact action time period based on the impact signal curve and the overload signal curve.
Further, the data processing unit includes:
the impact signal starting time determining module is used for finding an initial noise N1 in an impact signal curve, and outputting a time corresponding to the last impact signal before the amplitude of the ejection impact signal reaches m times of the initial noise N1 for the first time as an impact signal starting time t 1;
the suspension touchdown time determining module is used for finding out a characteristic segment which accords with change-zero-change-oscillation attenuation in the overload signal curve, outputting a time segment starting point with zero amplitude as an airplane-suspension separation time t2, and outputting a time segment ending point with zero amplitude as a suspension touchdown time t 3;
the impact signal end time determining module is used for finding out the maximum impact amplitude Amax before the suspension object landing time t3 in the impact signal curve, and outputting the time corresponding to the last impact signal with the amplitude p.Amax before t3 as the ejection impact end time t 4;
the ejection impact action time period determining module is used for determining that the ejection impact action time period is [ t1, t4 ];
the value of m is 1.3-2; the value of p is 8-13%.
Compared with the prior art, the invention can realize at least one of the following beneficial effects:
1. this application is through installing impact measurement sensor and overload measurement sensor on the suspender, and direct measurement suspender impact signal and ejection signal in launching impact test form impact signal curve and launch signal curve to confirm the impact action time quantum of launching according to two curves, compare in the measuring device among the prior art, this application measuring device is simple easily operated.
2. According to the method, the ejection impact starting time t1, the airplane-suspended object separation time t2, the suspended object touchdown time t3 and the ejection impact ending time t4 can be determined through an impact signal curve and an overload signal curve, after the suspended object touchdown time t3 is determined, the time corresponding to the maximum impact amplitude Amax before the suspended object touchdown time t3 and the last impact signal with the amplitude p.Amax before t3 in the impact signal curve needs to be found as the ejection impact ending time t4, and as the suspended object touchdown time t3 is determined and t4 is a certain required time before t3, the impact caused by the touching of the suspended object can be prevented from being judged as ejection impact mistakenly, and the measurement accuracy of the ejection impact action time period can be improved.
In the invention, the technical schemes can be combined with each other to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.
Fig. 1 is a flowchart of a method for determining a period of time of an impact of ejection;
FIG. 2 is a schematic diagram of a catapult impact signal curve;
FIG. 3 is a graph illustrating an overload signal;
FIG. 4 is a graph of an enlarged signal at the initial stage of a ballistic impact;
FIG. 5 is an enlarged view of an impact signal curve before the ground contact moment of the suspended object;
fig. 6 is a schematic view of a projectile impact action time period determination device.
Detailed Description
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate preferred embodiments of the invention and together with the description, serve to explain the principles of the invention and not to limit the scope of the invention.
Example 1
The invention discloses a method for determining an action time period of ejection impact of an airplane suspension object, which comprises the following steps of:
s1, arranging an impact measuring sensor and an overload measuring sensor on the suspension;
specifically, the impact measurement sensor is generally arranged at a position with better rigidity of a suspension, and the measurement direction is X, Y, Z direction; the overload measuring sensor is arranged at the position of the center of mass of the suspension object, and the measuring direction can be either X, Y, Z direction or three directions.
Specifically, the impact measurement sensor can be a 354C02 type three-axis acceleration sensor of PCB company, and the measuring range is +/-500 g;
the overload measuring sensor is a capacitive or piezoresistive overload sensor with zero-frequency measuring capacity, and can be a 3713 series triaxial acceleration sensor of a PCB company, and the measuring range is +/-50 g;
the frequency ranges of the two sensors are 10-2000 HZ.
S2, carrying out ground ejection test, and obtaining a suspension impact signal and an overload signal to form an impact signal curve and an overload signal curve;
the ground ejection test is to use an airborne ejection device to perform ejection test on a suspended object on the ground under the state that the airplane does not take off.
Before testing, installing an impact measuring sensor and an overload measuring sensor on a suspension object, and connecting each sensor to a data acquisition unit through a cable; the data acquisition unit and the data processing unit are arranged on the ground at a position which is dozens of meters away from the suspended object; the data acquisition unit and the data processing unit can be two independent components, and data transmission is carried out between the data acquisition unit and the data processing unit through a network cable; or the data acquisition unit and the data processing unit are integrated in one computer. And the data acquisition unit transmits the acquired impact signal and the acquired overload signal to the data processing unit. After the measuring device is connected, the ground ejection test can be started.
Specifically, an airborne ejection device is adopted to eject the suspension, impact data and overload data are collected in the ejection process, and the suspension stops collecting after falling to the ground.
The data acquisition unit comprises an impact measurement acquisition channel and an overload measurement acquisition channel; the impact measurement acquisition channel and the overload measurement acquisition channel both comprise a sampling circuit, a low-pass filter circuit and a normalization processing module;
specifically, for an impact measurement acquisition channel, the sampling rate of a sampling circuit is greater than 10 kHZ; the filtering frequency of the low-pass filtering circuit is 2-5 kHz;
for the overload measurement channel, the sampling frequency of the sampling circuit is more than 500Hz, and the filtering frequency of the low-pass filtering circuit is 100-200 Hz;
the specific structures of the sampling circuit and the low-pass filter circuit are not limited, and all the sampling circuits and the low-pass filter circuits meeting the requirements are within the protection scope of the application.
In order to facilitate subsequent data processing, normalization processing modules are arranged in the impact measurement channel and the overload measurement channel, normalization processing is carried out on data after sampling and filtering, and finally obtained impact signal curves and overload signal curves are data after normalization. As shown in fig. 2 and 3, the ejection impact signal curve and the overload signal curve are shown respectively.
S3, determining an ejection impact starting time t1, a suspension object grounding time t3 and an ejection impact ending time t4 based on the impact signal curve and the overload signal curve;
s31, determining the ejection impact starting time t 1;
the determining of the ejection impact starting time t1 includes: the initial noise N1 is found in the impact signal curve, and the t1 is the time corresponding to the last impact signal before the catapult impact signal amplitude reaches m times the initial noise N1 for the first time.
The value of m is 1.3-2;
preferably, the value of m is 1.5.
Specifically, an initial noise N1 of the ejection impact signal is determined, fig. 4 is an impact signal curve at the initial stage of the ejection impact, that is, an enlarged view of an impact signal curve circled by an elliptical coil in fig. 2, and a maximum value of an absolute value of the ejection impact signal in a time period from 0s to 0.3s is found therefrom to be 0.004577, that is, N1, and a time corresponding to a last impact signal before the ejection impact signal reaches the first 1.5 times of N1 is 0.48s, which is an ejection impact start time, and is recorded as t 1.
S32, determining the ground contact time t3 of the hanging object;
the pendant touchdown time t3 includes: finding out a characteristic segment conforming to the change-zero-change-shock attenuation in the overload signal curve, and taking the starting point of the time segment with the amplitude of zero as the aircraft-suspended object separation time t2 and the end point of the time segment with the amplitude of zero as the suspended object touchdown time t 3.
Specifically, according to the physical process of the ejection impact, it can be determined that the overload signal on the suspension object should continuously change in the action process of the ejection impact, and after the suspension object is separated from the airplane, the overload signal is a constant value zero due to the loss of the action of the ejection force, and when the suspension object touches the ground, the overload signal on the suspension object changes due to the action force applied to the suspension object by the ground, and the suspension object may have the characteristic of oscillation attenuation. The overload signal is as shown in fig. 3, a characteristic segment conforming to change-zero-change-oscillation attenuation is searched in an overload signal curve, the starting point (0.79s) of the time segment with zero is taken as the separation moment of the airplane and the suspension object and is marked as t2, and the end point (i.e. the turning point from zero to change) (0.95s) of the time segment with the amplitude of 0 is taken as the contact moment of the suspension object and is marked as t 3;
it should be noted that the curve segment with zero amplitude in the above characteristic segment is relative to other curve segments with larger amplitude fluctuation in the overload signal curve, and in practice, the curve segment with zero amplitude refers to the curve segment with only background noise and no actual overload signal due to the inevitable background noise in the measurement.
S33, determining the ejection impact end time t 4;
the determining of the ejection impact end time t4 includes: and finding out the maximum impact amplitude Amax before the ground contact time t3 of the suspended object from the impact signal curve, wherein the time corresponding to the last impact signal with the amplitude p.Amax before t3 is the ejection impact end time t 4.
The value of p is 8-13%.
Preferably, p is 10%.
FIG. 5 is an enlarged view of the shock signature curve of FIG. 2 prior to suspension touchdown (0.95 s); as can be found from fig. 5, the absolute value of the maximum impact amplitude before the grounding time of the suspended object is 0.5961, which is recorded as Amax, the value of 10% Amax reached by the last impact signal before t3 is 0.06033, and the corresponding time is 0.6776s, which is the ending time of the ejection impact, which is recorded as t 4;
and S4, determining the catapult impact action time period, namely [ t1, t4 ].
Specifically, for the impact signal curve shown in fig. 2, the impact action time period is obtained as [0.48s, 0.6776s ].
The purpose of determining the catapult impact action time period is to facilitate the follow-up analysis of catapult impact signals, so that in order to perform the follow-up impact signal analysis at different positions, a plurality of impact measurement sensors can be installed during the test, so that a plurality of impact signal curves can be obtained, and the measured impact signal curves are slightly different due to different installation positions of each sensor, so that the catapult action time period determining method can be applied to the impact signal curves with the differences, preferably, the catapult impact starting time t1 is t1- Δ t, the catapult impact ending time t4 is (t3+ t4)/2, and the Δ t is 10-50 ms; by the arrangement, the determined ejection impact action time period can be suitable for impact signal curves corresponding to all the sensors, and the ejection impact action time period is obtained without repeatedly executing each impact signal curve, so that the data processing efficiency is improved.
Specifically, the ejection impact starting time is 10ms to 50ms before t1, the ending time is (t4+ t3)/2, and the ejection impact analysis time period is [0.47s, 0.8138s ] after the above values are substituted.
Example 2
Another embodiment of the present invention provides an aircraft suspension ejection impact duration determination apparatus, as shown in fig. 6, including the following components: the device comprises an impact measurement sensor, an overload measurement sensor, a data acquisition unit and a data processing unit.
The impact measuring sensor and the overload measuring sensor are both arranged on the suspension object and are respectively used for measuring an impact signal and an overload signal of the suspension object;
the impact measurement sensor is generally arranged at a position with better rigidity, and the measurement direction is X, Y, Z direction; the overload measuring sensor is arranged at the position of the center of mass of the suspension object, and the measuring direction can be either X, Y, Z direction or three directions.
Specifically, the impact measurement sensor can be a 354C02 type three-axis acceleration sensor of PCB company, and the measuring range is +/-500 g;
the overload measuring sensor is a capacitive or piezoresistive overload sensor with zero-frequency measuring capacity, and can be a 3713 series triaxial acceleration sensor of a PCB company, and the measuring range is +/-50 g;
the frequency ranges of the two sensors are 10-2000 HZ.
The data acquisition unit is connected with the impact measurement sensor and the overload measurement sensor through cables and is used for acquiring impact signals and overload signals of a suspended object in the ground ejection test process to form an impact signal curve and an overload signal curve;
the data acquisition unit comprises an impact measurement acquisition channel and an overload measurement acquisition channel; the impact measurement acquisition channel and the overload measurement acquisition channel both comprise a sampling circuit, a low-pass filter circuit and a normalization processing module;
specifically, for an impact measurement acquisition channel, the sampling rate of a sampling circuit is greater than 10 kHZ; the filtering frequency of the low-pass filtering circuit is 2-5 kHz;
for the overload measurement channel, the sampling frequency of the sampling circuit is more than 500Hz, and the filtering frequency of the low-pass filtering circuit is 100-200 Hz;
the specific structures of the sampling circuit and the low-pass filter circuit are not limited, and all the sampling circuits and the low-pass filter circuits meeting the requirements are within the protection scope of the application.
In order to facilitate subsequent data processing, normalization processing modules are arranged in the impact measurement channel and the overload measurement channel, normalization processing is carried out on data after sampling and filtering, and finally obtained impact signal curves and overload signal curves are data after normalization.
And the data processing unit is connected with the data acquisition unit and determines an impact action time period based on the impact signal curve and the overload signal curve.
The data acquisition unit and the data processing unit are arranged on the ground at a position which is dozens of meters away from the suspended object; the data acquisition unit and the data processing unit can be two independent components, and data transmission is carried out between the data acquisition unit and the data processing unit through a network cable; or the data acquisition unit and the data processing unit are integrated in one computer.
The data processing unit includes:
and the impact signal starting time determining module is used for finding the initial noise N1 in the impact signal curve, and the t1 is the time corresponding to the last impact signal before the catapult impact signal amplitude reaches m times of the initial noise N1 for the first time.
The suspension touchdown time determining module is used for finding out a characteristic segment which accords with change-zero-change-oscillation attenuation in the overload signal curve, outputting a time segment starting point with zero amplitude as an airplane-suspension separation time t2, and outputting a time segment ending point with zero amplitude as a suspension touchdown time t 3;
the impact signal end time determining module is used for finding out the maximum impact amplitude Amax before the suspension object landing time t3 in the impact signal curve, and outputting the time corresponding to the last impact signal with the amplitude p.Amax before t3 as the ejection impact end time t 4;
the ejection impact action time period determining module is used for determining that the ejection impact action time period is [ t1, t4 ];
the value of m is 1.3-2; the value of p is 8-13%.
Those skilled in the art will appreciate that all or part of the flow of the method implementing the above embodiments may be implemented by a computer program, which is stored in a computer readable storage medium, to instruct related hardware. The computer readable storage medium is a magnetic disk, an optical disk, a read-only memory or a random access memory.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (10)
1. A method for determining an action time period of ejection impact of an airplane suspension object is characterized by comprising the following steps:
arranging an impact measuring sensor and an overload measuring sensor on the suspension;
carrying out a ground ejection test, and obtaining a suspension impact signal and an overload signal to form an impact signal curve and an overload signal curve;
determining an ejection impact starting time t1, a suspension object grounding time t3 and an ejection impact ending time t4 based on the impact signal curve and the overload signal curve;
and determining the catapult impact action time period, namely [ t1, t4 ].
2. The method for determining an action time period of an aircraft suspension object catapulting impact according to claim 1, wherein said determining an initiation time t1 of the catapulting impact comprises: the initial noise N1 is found in the impact signal curve, and the t1 is the time corresponding to the last impact signal before the catapult impact signal amplitude reaches m times the initial noise N1 for the first time.
3. The method for determining an aircraft suspension ejection impact time period as claimed in claim 2, wherein said determining a suspension touchdown time t3 comprises: finding out a characteristic segment conforming to the change-zero-change-shock attenuation in the overload signal curve, and taking the starting point of the time segment with the amplitude of zero as the aircraft-suspended object separation time t2 and the end point of the time segment with the amplitude of zero as the suspended object touchdown time t 3.
4. The method for determining an action time period of an aircraft suspension object ejection impact according to claim 3, wherein said determining an end time t4 of the ejection impact comprises: and finding out the maximum impact amplitude Amax before the ground contact time t3 of the suspended object from the impact signal curve, wherein the time corresponding to the last impact signal with the amplitude p.Amax before t3 is the ejection impact end time t 4.
5. The method for determining the time period of the catapult impact action of the aircraft hangar as claimed in claim 4, wherein the value of m is 1.3-2; the value of p is 8-13%.
6. The method for determining the time period for which an aircraft suspension object catapult impact acts on according to any one of claims 1 to 5, wherein the impact measurement sensor is arranged at a position where the suspension object is relatively rigid, and the measurement direction is X, Y, Z; the overload measuring sensor is arranged at the position of the center of mass of the suspended object, and the measuring direction is X, Y, Z, or the measuring direction is measured in all three directions.
7. The method for determining an aircraft suspension ejection impact time period according to any one of claims 1 to 5, wherein the impact measurement sensor has a range of ± 500 g; the overload measuring sensor is a capacitance type or piezoresistive overload sensor with zero-frequency measuring capacity, and the measuring range is +/-50 g; the frequency ranges of the two sensors are 10 Hz-2000 HZ.
8. The aircraft suspension projectile impact duration determination method as claimed in any one of claims 1 to 5, wherein said projectile impact start time t1 is taken as t1- Δ t, said projectile impact end time t4 is taken as (t3+ t4)/2, and said Δ t is taken as 10-50 ms.
9. An aircraft suspension object ejection impact action time period determination device is characterized by comprising the following components:
the impact measuring sensor and the overload measuring sensor are both arranged on the suspension object and are respectively used for measuring an impact signal and an overload signal of the suspension object;
the data acquisition unit is connected with the impact measurement sensor and the overload measurement sensor and is used for acquiring impact signals and overload signals of a suspended object in the ground ejection test process to form an impact signal curve and an overload signal curve;
and the data processing unit is connected with the data acquisition unit and determines an impact action time period based on the impact signal curve and the overload signal curve.
10. The aircraft suspension object ejection impact duration determination apparatus as claimed in claim 9, wherein said data processing unit comprises:
the impact signal starting time determining module is used for finding an initial noise N1 in an impact signal curve, and outputting a time corresponding to the last impact signal before the amplitude of the ejection impact signal reaches m times of the initial noise N1 for the first time as an impact signal starting time t 1;
the suspension touchdown time determining module is used for finding out a characteristic segment which accords with change-zero-change-oscillation attenuation in the overload signal curve, outputting a time segment starting point with zero amplitude as an airplane-suspension separation time t2, and outputting a time segment ending point with zero amplitude as a suspension touchdown time t 3;
the impact signal end time determining module is used for finding out the maximum impact amplitude Amax before the suspension object landing time t3 in the impact signal curve, and outputting the time corresponding to the last impact signal with the amplitude p.Amax before t3 as the ejection impact end time t 4;
the ejection impact action time period determining module is used for determining that the ejection impact action time period is [ t1, t4 ];
the value of m is 1.3-2; the value of p is 8-13%.
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