CN104670521A - Transport aircraft inlet splash testing method - Google Patents
Transport aircraft inlet splash testing method Download PDFInfo
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Abstract
The invention relates to a transport aircraft inlet splash testing method for transport aircraft splash testing. According to the method, before a splash test, configuration of a test aircraft for test flight, various running statues of an engine and test aircraft glide speed point required by testing are determined according to the type of the test aircraft; materials and position of a test pool in a runway, coloring position of an aircraft body and selection of coloring materials, a video-recording method, test aircraft glide modes meeting the testing requirements and the like are determined; tests are performed one by one according to the test aircraft glide speed required by testing. The method has the advantages that splash testing is performed according to the airworthiness regulation for test aircraft, by studying, the configuration state of the test aircraft during splash testing, a building method of the test pool, coloring of the test aircraft for judging test results, a test video-recording technique, acquisition of test key data, final identification modes of data and the like are determined, and a standard set of methods and programs for transport aircraft splash testing is formed.
Description
Technical field
The present invention is used for airplane in transportation category water spray suppression test, be applicable to the water spray suppression test that civil aircraft carries out according to GJB243 " requirement of aviation gas turbine certification flight test " according to CCAR the 25th airplane in transportation category airworthiness standard or military transport class aircraft, for the clause airworthiness compliance of civil aircraft or the design typification of military aircraft provide foundation, the water spray suppression test of other types aircraft also can refer to this method to carry out.
Background technology
Airplane in transportation category water spray suppression test is one of the civil aircraft important tests that must carry out and get the Green Light during carrying out Airworthiness Certification.The civilian airplane in transportation category runed both at home and abroad at present, substantially all water spray suppression test is completed during certification, and by the approval of aiMonhiness authority, as airliners such as learjet45, FOKKER100 aircraft early stage abroad and current Airbus A380, Boeing747.The seaworthiness clause of many military transport class aircrafts also with reference to civilian airplane in transportation category during type design sizing requires to have carried out water spray suppression test, the A400M military transportation airplane of such as Air Passenger military aircraft company.External aircraft industry is through century-old development, have accumulated sturdy basic test technology, seaworthiness authorization to be taken a flight test or design typification is taken a flight test through the authorization of Multiple Type aircraft certification, particularly there are clearer and more definite test requirements document and strict successful criterion to airplane in transportation category water spray suppression test, if US Federal Aviation Administration FAA and European aviation office EASA has all formulated relevant airworthiness regulation and clause.China just started really to start independent development airplane in transportation category from last century Mo, therefore just at the early-stage in test routine method and seaworthiness authorization are taken a flight test, main the 25th formulation with reference to US Federal Aviation Administration of airplane in transportation category airworthiness regulation, referred to as CCAR-25.Therefore, the airplane in transportation category of China will enter European & American Market or the other countries that are foundation with FAA or EASA airworthiness standard, and the airplane in transportation category seaworthiness authorization that China develops voluntarily or design typification also need the requirement by FAA or EASA airworthiness regulation standard.
Although airplane in transportation category water spray suppression test is mentioned in the CCAR-25 of FAA, EASA and China, but be only limitted to seaworthiness clause and requirement, also do not inquire concrete implementation method and the documents and materials of technical scheme abroad at present, blank especially in China, so there is no can to follow according to the technical materials performed and test routine.Clause 25.1091(d according to CCAR-25-R4) (2): " aircraft must be designed to prevent the water of dangerous amount on other work-yard of runway, taxiway or airport or snow-broth from directly entering the inlet channel of driving engine or auxiliary power unit, and the position of inlet channel or protection must make the degree that it was taking off, and landed and sucking in taxiing procedures exotic reduce to minimum.", clause 25.1323(h) for the requirement of air speed indicating system: " arrangement of each air speed indicating system must prevent malfunctioning because moisture, dust or other foreign material invade as far as possible or produce gross error; " and clause 25.1325(b) performance of static-pressure system must be made by variations in flow or the requirement that is subject to the impact of moisture or other exotic minimum for the static aperture design design of aircraft static pressure system and position, the checking of clause accordance must be carried out by water spray suppression test.Carry out airplane in transportation category water spray suppression test, need to solve following problem:
A) determination of test condition, comprises the flight test vehicle coasting speed interval of flight test vehicle configuration, engine configuration state, test requirements document;
B) determine to test airport according to the configuration states of test requirements document, coasting speed interval;
C) according to the condition on flight test vehicle structure, dabble time and depth of water requirement and test airport, aquifer zones is built to simulate puddled runway;
D) slide race to terminate to determine fast and identification test aircraft splash area and degree afterwards;
E) video, image admission technology that process of the test dabbles is obtained, with the situation that dabbles of the whole process of the test of interpretation;
F) coasting speed that flight test vehicle entered, left experimental tank is accurately obtained;
G) according to the sliding race mode of the flight test vehicle configuration of test, engine condition, the flight test vehicle coasting speed determination test routine of test requirements document and method, flight test vehicle;
H) determination methods of test results.
Only solve above several key issue, just can meet the requirement tested and carry out technically, technically have the method carrying out to office side demonstrating, water spray suppression test just can carry out, and just can obtain aiMonhiness authority or examination side to the accreditation of test figures validity.
Summary of the invention
Goal of the invention
Water spray suppression test is carried out in requirement according to flight test vehicle airworthiness regulation, by having determined the configuration states of flight test vehicle in water spray suppression test process, experimental tank building method, can judge that the flight test vehicle of test results is tinted, test video shoot technology, the acquisition methods of test critical data, and the last interpretation mode etc. of data, form method and the program of standard set airplane in transportation category water spray suppression test.
Technical scheme
Before water spray suppression test, first flight test vehicle configuration, the various mode of operations of driving engine, the flight test vehicle coasting speed point of test requirements document of taking a flight test to be determined according to corresponding type, that determines experimental tank on runway builds material, position, the position that body is tinted and material selection, video shoot method and meet the sliding race mode of flight test vehicle etc. of test requirements document, then successively tests according to the flight test vehicle coasting speed of test requirements document.
The concrete testing sequence of water spray suppression test is as follows:
Step 1 tests the new field of technical activity
1.1 flight test vehicle configurations are determined step by step
According to the seaworthiness clause of water spray suppression test and the manufacture claim of flight test vehicle, can determine the test weight W of flight test vehicle, center-of-gravity position, the flight test vehicle coasting speed interval of test requirements document is 0kn ~ V
r, V
rfor taking off of this type flight test vehicle lifts front-wheel coasting speed; the flap configuration of flight test vehicle is screens and the landing screens of taking off; engine condition is takeoff condition or landing state; the configuration simultaneously can sent according to this type flight test vehicle determines the power supply of the driving engine that can affect test results, bleed, firing unit configuration states; the state of thrust reverser under landing configuration; before test, weight, center of gravity allotment to be carried out to flight test vehicle, meet test requirements document; .
1.2 length and width determining experimental tank step by step
In the process of dabbling, require that the time of dabbling of different configuration is not less than 1 second, be all coasting speeds of satisfied test, the length L of experimental tank
cbe not less than V
r* 1 second, according to the landing gear structure of flight test vehicle, the width L of experimental tank
kbe not less than the main landing gear tire outer end distance L of flight test vehicle
l, consider the take-off deviation △ L of flight test vehicle simultaneously
k, experimental tank width L
k>=L
l+ △ L
k;
1.3 experimental tank position and building modes step by step
According to flight test vehicle coasting speed, the engine condition of test requirements document, calculate flight test vehicle by flight test vehicle performance and testing the head L needed for the flight test vehicle coasting speed accelerating to test requirements document under configuration states
jIAS, for meeting coasting speed and the engine condition requirement of flight test vehicle, the length of experimental tank distance runway one end is not less than L
jIAS, experimental tank is positioned at the L of the distance above-mentioned termination of runway
jIAS~ L
jIAS+ L
cplace.Meanwhile, according to raising with temperature during test with the wind, the impact of flight test vehicle acceleration distance is suitably revised experimental tank position; The dykes and dams material of experimental tank be have elasticity, toughness, can the material composition of strong bond on runway, guarantee can not to aircraft slide and pilot guidance impacts, and can the leakage of anti-sealing;
If this section of runway pavement exists the gradient, then adopt grid type layout, the size of grid calculates according to the runway gradient, and in each lattice, the depth of water in more than 90% region reaches seaworthiness clause and requires the degree of depth;
Before test, complete the construction of experimental tank at test zone;
1.4 flight test vehicles are tinted step by step
Determine position of tinting, material, color; Tint position can comprise flight test vehicle pitot position, flight test vehicle inlet lip circumference, the inner temperature sensor region of inlet channel, flight test vehicle wing flap front edge area, environmental control system air inlet port regions, may affected cargo door, luggage compartment door region, APU air inlet port regions, different according to the structure of flight test vehicle, position of tinting can increase and decrease by demand; Material of tinting is that after non-corrosiveness, chance water, vestige is obvious, easy cleaned water-soluble liquid;
1.5 photography and vedio recordings step by step
According to the configuration of the position in water spray suppression test pond, flight test vehicle, the object of pick up camera shooting and object, arrange corresponding pick up camera; Wherein the 1st, the 3rd pick up camera lays respectively at the both sides of experimental tank, adopts wide angle cameras, takes all images from experimental tank entrance to outlet; 2nd and the 4th pick up camera lays respectively at experimental tank exit end side, adopts focal length pick up camera, takes the whole process video that dabbles; 5th pick up camera is arranged in main cabin, and after being positioned at the side window near engine inlet, shooting inlet lip dabbles video;
The shooting frame number of each pick up camera is not less than 24 frames/second, based on the restriction of the effect of taking, safety and condition, the position of pick up camera can suitably adjust, under can obtaining at the 1st, the 2nd, the 3rd, No. 4 pick up camera the condition judging the situation that dabbles, installation the 6th position for video camera can be selected in the other one end of runway, adopt focal length high-definition camera, the video that dabbles that shooting flight test vehicle heads on; The 7th pick up camera can be selected to be arranged on helicopter, to take a crane shot in the air the whole process that dabbles in the sliding front side of running of flight test vehicle, the helicopter installing the 7th pick up camera can in the equidirectional motion in front, side, experimental engine overhead, keeps as far as possible and coasting speed that flight test vehicle is same;
Before test, complete the installation and adjustment of pick up camera;
1.6 flight test vehicles enter and leave the coasting speed defining method of experimental tank step by step
Perpendicular on the direction of runway, the extended line of experimental tank entrance limit and Exit-edge is arranged the first digital high-speed photography A and the second digital high-speed video camera B, record the time that flight test vehicle entered and left experimental tank.Digital high-speed video camera and Airborne Testing System all adopt GPS time service, time lock, in the time that airborne testing extracting data first digital high-speed video camera A, the second digital high-speed video camera B record corresponding coasting speed value;
The 1.7 sliding race methods of fixed point constant speed meeting coasting speed, engine condition step by step
1.7.1 determine flight test vehicle coasting speed
The flight test vehicle coasting speed testing test requirements document first chooses about VNO.1=︱ V
r/ 2 ︱ values, other coasting speeds are followed successively by VNO.2, VNO.3 and are incremented to V
rif there is incongruent test results under the coasting speed of VNO.1, can reduce coasting speed and carry out, until test thinks that test results meets the demands, flight test vehicle two closes on the absolute value≤20kn of coasting speed difference;
1.7.2 determine that flight test vehicle plays sliding some distance
According to test coasting speed VNO.1, VNO.2, VNO.2 ..., V
r, design provide theoretical condition calculate different temperatures time under the flight test vehicle configuration, engine condition of test requirements document flight test vehicle acceleration distance L1, L2 ..., LR; Then selected two or three coasting speeds carry out simulating and slidingly run test, under determining the flight test vehicle configuration of this type flight test vehicle test requirements document, engine condition, and the bias △ L that when accelerating to this coasting speed, the gentle wind speed in field affects ground run distance,
During landing configuration, driving engine accelerates at maximum rating, the engine condition needed for motivation to test is received and dispatched under certain coasting speed of flight test vehicle coasting speed being greater than test requirements document, aircraft carries out deceleration, when engine condition and coasting speed reach the coasting speed of test requirements document, this distance is flight test vehicle landing state and plays sliding some distance LZ.
Flight test vehicle add ski-running run section to mark successively to the direction leaving experimental tank entrance each the sliding some L1 that respectively dabble, L2 ..., LR, LZ corresponding rise slip 1, rise slip 2 ..., rise slip V
r, rise slip LZ;
During test, according to the wind speed of test area and field Wen Qi slip L1, L2 ..., LR, LZ increase or reduce △ L.
Step 2 test session
After every dead work puts in place, just can test.Testing sequence is as follows:
Wind speed Vwind, wind direction Dwind, the field temperature T0 of 2.1 record proving grounds step by step;
2.2 pairs of experimental tank water fillings measuring step by step, guarantee that the depth of water of experimental tank area 90% is not less than the depth of water requirement of seaworthiness clause;
2.3 engineerings to navigate front inspection to flight test vehicle step by step, confirm that each system is normal;
The 2.4 pairs of flight test vehicles are tinted according to 1.4 positions of tinting determined step by step step by step, and in a certain order, shooting angle takes pictures to flight test vehicle position of tinting, and carry out mark, confirms the position state of tinting before water spray suppression test;
2.5 flight test vehicles have slided into slip 1 step by step, stop and stop.Arrange the screens that flight test vehicle wing flap is test requirements document, engine test state, releasing of brake flight test vehicle adds ski-running and runs, and passes through experimental tank with coasting speed VNO.1; The each pick up camera step by step described in 1.5 and the digital high-speed video camera journey record step by step described in 1.6 is adopted to dabble image;
The mode of operation of aviator, each system of engineering staff's monitoring test aircraft of taking a flight test in 2.6 processs of the test step by step, abnormal if there is system works, stop test, pending fault proceeds the test of this coasting speed point after getting rid of, if fault can not be discharged or this fault effects to flight safety, then termination test;
2.7 flight test vehicles leave normal interruption after experimental tank step by step, slide back to aircraft gate, stop;
Step by step 2.8 with step by step 2.4 order, shooting angle shooting flight test vehicle to tint the photo at position, mark;
Whether each system of 2.9 engineering checkout test aircraft is normal step by step;
If step by step 2.10 step by step 2.9 check normal, according to 2.1 ~ step by step 2.9 tests carrying out coasting speed VNO.2 step by step; If 2.9 checkout test airframe damages or discovery fault, get rid of or do not affect test results and safety, proceeding test step by step, otherwise, termination test;
After 2.11 all test poinies terminate step by step, test before and after photo of tinting, video, engine operating parameter, digital high-speed camera record enter and leave the data information of experimental tank time as analytical test result.By analyzing, determine that the inlet channel flooded condition of this type flight test vehicle under different coasting speed, water inlet critical coasting speed the most serious or critical coasting speed are interval; That determines airspeed system in process of the test indicates whether to there is fluctuation, and whether the pitot-static pressure pipeline water accumulator of static-pressure system exists ponding.
Step by step 2.12 about 2.11 critical coasting speeds determined step by step or critical coasting speed interval reduce coasting speed and be spaced apart 10kn, even 5kn, according to 2.1 ~ step by step 2.11 repeated trials step by step, until can judge that the most serious situation that dabbles and corresponding critical coasting speed or critical coasting speed are interval.
Technique effect
The present invention accurately can determine the critical coasting speed that dabbles of flight test vehicle easily, identifies position and the degree of dabbling, meets the requirement of seaworthiness clause to water spray suppression test, forms method and the program of airplane in transportation category water spray suppression test.The test flight data data obtained can judge and verify the accordance of airplane in transportation category water spray suppression test result and clause, provides enough foundations of taking a flight test for obtaining type certificate or obtaining setting sizing.
Advantage of the present invention is:
The method of that a) formulated complete set, that there is practical operability airplane in transportation category water spray suppression test and program;
B) determine building of experimental tank and want summation approach, material requirements;
C) determine the coloring method of flight test vehicle, dabble position and degree can be identified easily;
D) video camera requirement, the method for arranging of pick up camera, the technique for taking of image is determined;
E) indirectly obtain by image processing techniques the coasting speed difficulty that flight test vehicle entered, left experimental tank;
The sliding race method of the fixed point constant speed f) determined, obtains a difficult problem for the coasting speed of test requirements document under solving the aircraft configuration state of certain experimental tank position, certain test requirements document engine condition, certain test requirements document; Decrease test number, shorten test and account for field time, improve efficiency; Reduce the operation requirements in aviator's process of the test simultaneously, improve the safety of test;
G) the method can demonstrate the result of water spray suppression test intuitively, the data obtained by test method, image and video data, can the result that dabbles of intuitive judgment inlet channel, the accordance of certification testing aircraft and seaworthiness clause;
H) flight test vehicle that this test method also can be used for other types carries out the reference of water spray suppression test, and test results can be the development of flight test vehicle meter and provides and answer Attention question, avoids occurring subversive design problem, accelerates the Development Schedule of flight test vehicle.
Accompanying drawing explanation
Fig. 1 is the diagram of circuit of flight test vehicle water spray suppression test
Fig. 2 is camera arrangements schematic diagram
Detailed description of the invention
For aircraft water spray suppression test, the concrete testing sequence of test is as follows:
1 test new field of technical activity
1.1 test configurations are determined
According to the seaworthiness clause of water spray suppression test and the manufacture claim of flight test vehicle, and the dabble form of design to flight test vehicle tire, what determine flight test vehicle is be with take-off weight and maximum landing weight most, front center of gravity, coasting speed interval is 0kn ~ 140kn, during takeoff condition, flight test vehicle flap configuration is screens of taking off, engine takeoff state, during landing state, flight test vehicle wing flap is landing screens, driving engine idling rating, the power supply of the configuration determination driving engine simultaneously can sent according to flight test vehicle, bleed, firing unit configuration, under landing configuration, thrust reverser is for opening and not open mode.
1.2 length and width determining experimental tank
Experimental tank length is L
cbe not less than V
r* 1 second, L
c>=140kn*1 second=72m, determine experimental tank length L
c=100 meters, aircraft main landing gear tire outer end distance L
l=5.7m, allows flight test vehicle to depart from 1.1m, finally determines experimental tank width L
k=8m.
1.3 experimental tank position and building modes
Calculate according to aeroplane performance, at the acceleration distance L on test airport when aircraft maximum take-off weight, engine takeoff state, field temperature 30 DEG C
jIASfor 1540m, select L
jIAS=1550m.Because face, road, experimental tank region exists the gradient, experimental tank adopts grid type layout.
Before test, complete experimental tank construction at test zone, and carried out revealing checking.
1.4 flight test vehicles are tinted
To around airplane intake lip circumference, the left and right leading edge of a wing, left and right pitot, back cargo hold door position tints.Selected Switzerland's Clariant redness to tint material, this material does not have corrosive property to airframe, be easy to cleaning, and the chromatic zones of body divides obviously.
1.5 photography and vedio recording
Camera arrangements as shown in Figure 2,1. number, 3. number wide angle cameras is adopted, be positioned at the left and right sides, pond, 2. number, 4. number pick up camera adopts focal length pick up camera, be positioned at experimental tank exporter side, 5. number employing field camera, taken through the position near inlet lip by human users, 7. position for video camera is on helicopter, moves in the same way when the sliding race of flight test vehicle.Based on security consideration, 6. number pick up camera is not set.Before test, complete the installation and adjustment of pick up camera.
1.6 flight test vehicles enter and leave the coasting speed defining method of experimental tank
Digital high-speed photography A and digital high-speed video camera B is positioned at the entrance of experimental tank, exit position perpendicular on the direction of runway, and record aircraft enters and leave the time in pond moment.
1.7 employing fixed points, constant speed method carry out sliding race test
Test speed is defined as takeoff configuration 70kn, 90kn, 110kn, 130kn, V
r, landing configuration is 100kn, 120kn.Calculate according to aeroplane performance, during its midfield temperature 30 °, the ground run distance of calm condition 90kn is 250m.
Before test, flight test vehicle add ski-running run section to mark successively to the direction leaving experimental tank entrance each coasting speed that dabbles corresponding rise slip 1, slip 2 ..., rise slip V
rwith a slip L
z.
2 test sessions
After every dead work puts in place, just can test.Testing sequence is as follows:
Wind speed Vwind, wind direction Dwind, the field temperature T0 of 2.1 record proving grounds;
2.2 pairs of experimental tank water fillings are also measured, and the depth of water of experimental tank area 90% is not less than 12.7mm, meet the depth of water requirement of seaworthiness clause;
2.3 engineerings to navigate front inspection to flight test vehicle, confirm that each system is normal;
Tint, according to pitot, the leading edge of a wing, inlet lip, back cargo hold door order Taking Pictures recording in 2.4 pairs of flight test vehicles position of tinting;
2.5 flight test vehicles slide into a slip of test speed 70kn, stop and stop.Arrange flight test vehicle wing flap for screens of taking off, engine condition is for taking off, and after driving engine working stability, releasing of brake flight test vehicle adds ski-running and runs; Digital high-speed video camera and each seat in the plane pick up camera whole process record the image that dabbles; To take a flight test engineering staff's implementing monitoring driving engine and each system operational parameters of aircraft;
2.6 aircraft slide back to aircraft gate, stop;
2.7 according to 2.4 order taken pictures and record in position of tinting;
Whether 2.8 engineering checkout test aircraft outward appearances, each system of flight test vehicle be normal;
The each system of 2.9 aircraft is normal, and the program according to 2.1 ~ 2.8 carries out the test of coasting speed 90kn;
After the water spray suppression test of 2.10 takeoff configuration completes, the program according to 2.1 ~ 2.8 carries out the test of landing configuration.
Claims (1)
1. airplane in transportation category inlet channel water spray suppression test method, is characterized in that:
Before water spray suppression test, first flight test vehicle configuration, the various mode of operations of driving engine, the flight test vehicle coasting speed point of test requirements document of taking a flight test to be determined according to corresponding type, that determines experimental tank on runway builds material, position, the position that body is tinted and material selection, video shoot method and meet the sliding race mode of flight test vehicle etc. of test requirements document, then successively tests according to the flight test vehicle coasting speed of test requirements document; Concrete testing sequence is as follows:
Step 1 tests the new field of technical activity
1.1 flight test vehicle configurations are determined step by step
According to the seaworthiness clause of water spray suppression test and the manufacture claim of flight test vehicle, determine the test weight W of flight test vehicle, center-of-gravity position; The flight test vehicle coasting speed interval of test requirements document is 0kn ~ V
r,, V
rfor taking off of this type flight test vehicle lifts front-wheel coasting speed, the flap configuration of flight test vehicle is screens and the landing screens of taking off, and engine condition is takeoff condition or landing state; The configuration simultaneously can sent according to this type flight test vehicle determines the power supply of the driving engine that can affect test results, bleed, firing unit configuration states, the state of thrust reverser under landing configuration;
Before test, weight, center of gravity allotment to be carried out to flight test vehicle, meet test requirements document;
1.2 length and width determining experimental tank step by step
In the process of dabbling, require that the time of dabbling of different configuration is not less than 1 second, be all coasting speeds of satisfied test, the length L of experimental tank
cbe not less than V
r* 1 second, according to the landing gear structure of flight test vehicle, the width L of experimental tank
kbe not less than the main landing gear tire outer end distance L of flight test vehicle
l, consider the take-off deviation △ L of flight test vehicle simultaneously
k, experimental tank width L
k>=L
l+ △ L
k;
1.3 experimental tank position and building modes step by step
According to flight test vehicle coasting speed, the engine condition of test requirements document, calculate flight test vehicle by flight test vehicle performance and testing the head L needed for the flight test vehicle coasting speed accelerating to test requirements document under configuration states
jIAS, for meeting coasting speed and the engine condition requirement of flight test vehicle, the length of experimental tank distance runway one end is not less than L
jIAS, experimental tank is positioned at the L of the distance above-mentioned termination of runway
jIAS~ L
jIAS+ L
cplace; Meanwhile, according to raising with temperature during test with the wind, the impact of flight test vehicle acceleration distance is suitably revised experimental tank position; The dykes and dams material of experimental tank be have elasticity, toughness, can the material composition of strong bond on runway, guarantee can not to aircraft slide and pilot guidance impacts, and can the leakage of anti-sealing;
If this section of runway pavement exists the gradient, then adopt grid type layout, the size of grid calculates according to the runway gradient, and in each lattice, the depth of water in more than 90% region reaches seaworthiness clause and requires the degree of depth;
Before test, complete the construction of experimental tank at test zone;
1.4 flight test vehicles are tinted step by step
Determine position of tinting, material, color; Tint position comprise flight test vehicle pitot position, flight test vehicle inlet lip circumference, the inner temperature sensor region of inlet channel, flight test vehicle wing flap front edge area, environmental control system air inlet port regions, may affected cargo door and luggage compartment door region, APU air inlet port regions, different according to the structure of flight test vehicle, position of tinting can increase and decrease by demand; Material of tinting is that after non-corrosiveness, chance water, vestige is obvious, easy cleaned water-soluble liquid;
1.5 photography and vedio recordings step by step
According to the configuration of the position in water spray suppression test pond, flight test vehicle, the object of pick up camera shooting and object, arrange corresponding pick up camera; Wherein the 1st, the 3rd pick up camera lays respectively at the both sides of experimental tank, adopts wide angle cameras, takes all images from experimental tank entrance to outlet; 2nd and the 4th pick up camera lays respectively at experimental tank exit end side, adopts focal length pick up camera, takes the whole process video that dabbles; 5th pick up camera is arranged in main cabin, and after being positioned at the side window near engine inlet, shooting inlet lip dabbles video;
The shooting frame number of each pick up camera is not less than 24 frames/second, based on the restriction of the effect of taking, safety and condition, the position of pick up camera can suitably adjust, under can obtaining at the 1st, the 2nd, the 3rd, No. 4 pick up camera the condition judging the situation that dabbles, installation the 6th position for video camera can be selected in the other one end of runway, adopt focal length high-definition camera, the video that dabbles that shooting flight test vehicle heads on; The 7th pick up camera can be selected to be arranged on helicopter, to take a crane shot in the air the whole process that dabbles in the sliding front side of running of flight test vehicle, the helicopter installing the 7th pick up camera can in the equidirectional motion in front, side, experimental engine overhead, keeps as far as possible and coasting speed that flight test vehicle is same;
Before test, complete the installation and adjustment of pick up camera;
1.6 flight test vehicles enter and leave the coasting speed defining method of experimental tank step by step
Perpendicular on the direction of runway, the extended line of experimental tank entrance limit and Exit-edge is arranged the first digital high-speed photography A and the second digital high-speed video camera B, record the time that flight test vehicle entered and left experimental tank; Digital high-speed video camera and Airborne Testing System all adopt GPS time service, time lock, in the time that airborne testing extracting data first digital high-speed video camera A, the second digital high-speed video camera B record corresponding coasting speed value;
The 1.7 sliding race methods of fixed point constant speed meeting coasting speed, engine condition step by step
1.7.1 determine flight test vehicle coasting speed
The flight test vehicle coasting speed testing test requirements document first chooses about VNO.1=︱ V
r/ 2 ︱ values, other coasting speeds are followed successively by VNO.2, VNO.3 and are incremented to V
rif there is incongruent test results under the coasting speed of VNO.1, then reduce coasting speed and carry out, until test thinks that test results meets the demands, flight test vehicle two closes on the absolute value≤20kn of coasting speed difference;
1.7.2 determine that flight test vehicle plays sliding some distance
According to test coasting speed VNO.1, VNO.2, VNO.2 ..., V
r, design provide theoretical condition calculate different temperatures time under the flight test vehicle configuration, engine condition of test requirements document flight test vehicle acceleration distance L1, L2 ..., LR; Then selected two or three coasting speeds carry out simulating and slidingly run test, under determining the flight test vehicle configuration of this type flight test vehicle test requirements document, engine condition, and the bias △ L that when accelerating to this coasting speed, the gentle wind speed in field affects ground run distance,
During landing configuration, driving engine accelerates at maximum rating, the engine condition needed for motivation to test is received and dispatched under certain coasting speed of flight test vehicle coasting speed being greater than test requirements document, aircraft carries out deceleration, when engine condition and coasting speed reach the coasting speed of test requirements document, this distance is flight test vehicle landing state and plays sliding some distance LZ;
Flight test vehicle add ski-running run section to mark successively to the direction leaving experimental tank entrance each the sliding some L1 that respectively dabble, L2 ..., LR, LZ corresponding rise slip 1, rise slip 2 ..., rise slip V
r, rise slip LZ;
During test, according to the wind speed of test area and field Wen Qi slip L1, L2 ..., LR, LZ increase or reduce △ L;
Step 2 test session
After every dead work puts in place, just can test; Testing sequence is as follows:
Wind speed Vwind, wind direction Dwind, the field temperature T0 of 2.1 record proving grounds step by step;
2.2 pairs of experimental tank water fillings measuring step by step, guarantee that the depth of water of experimental tank area 90% is not less than the depth of water requirement of seaworthiness clause;
2.3 engineerings to navigate front inspection to flight test vehicle step by step, confirm that each system is normal;
The 2.4 pairs of flight test vehicles are tinted according to 1.4 positions of tinting determined step by step step by step, and in a certain order, shooting angle takes pictures to flight test vehicle position of tinting, and carry out mark, confirms the position state of tinting before water spray suppression test;
2.5 flight test vehicles have slided into slip 1 step by step, stop and stop; Arrange the screens that flight test vehicle wing flap is test requirements document, engine test state, releasing of brake flight test vehicle adds ski-running and runs, and passes through experimental tank with coasting speed VNO.1; The each pick up camera step by step described in 1.5 and the digital high-speed video camera journey record step by step described in 1.6 is adopted to dabble image;
The mode of operation of aviator, each system of engineering staff's monitoring test aircraft of taking a flight test in 2.6 processs of the test step by step, abnormal if there is system works, stop test, pending fault proceeds the test of this coasting speed point after getting rid of, if fault can not be discharged or this fault effects to flight safety, then termination test;
2.7 flight test vehicles leave normal interruption after experimental tank step by step, slide back to aircraft gate, stop;
Step by step 2.8 with step by step 2.4 order, shooting angle shooting flight test vehicle to tint the photo at position, mark;
Whether each system of 2.9 engineering checkout test aircraft is normal step by step;
If step by step 2.10 step by step 2.9 check normal, according to 2.1 ~ step by step 2.9 tests carrying out coasting speed VNO.2 step by step; If 2.9 checkout test airframe damages or discovery fault, get rid of or do not affect test results and safety, proceeding test step by step, otherwise, termination test;
After 2.11 all test poinies terminate step by step, test before and after photo of tinting, video, engine operating parameter, digital high-speed camera record enter and leave the data information of experimental tank time as analytical test result; By analyzing, determine that the inlet channel flooded condition of this type flight test vehicle under different coasting speed, water inlet critical coasting speed the most serious or critical coasting speed are interval; That determines airspeed system in process of the test indicates whether to there is fluctuation, and whether the pitot-static pressure pipeline water accumulator of static-pressure system exists ponding;
Step by step 2.12 about 2.11 critical coasting speeds determined step by step or critical coasting speed interval reduce coasting speed and be spaced apart 10kn, even 5kn, according to 2.1 ~ step by step 2.11 repeated trials step by step, until can judge that the most serious situation that dabbles and corresponding critical coasting speed or critical coasting speed are interval.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105571880A (en) * | 2016-01-26 | 2016-05-11 | 西北工业大学 | Tyre splashing test device |
| CN106383859A (en) * | 2016-08-31 | 2017-02-08 | 北京蓝天航空科技股份有限公司 | Test flight data analysis processing method |
| CN107576283A (en) * | 2017-09-08 | 2018-01-12 | 中国飞行试验研究院 | Determine that aircraft dabbles the method for angle indirectly by optical measurement parameter |
| CN109502053A (en) * | 2018-12-14 | 2019-03-22 | 中国飞行试验研究院 | A kind of amphibious aircraft fire extinguishing task system Flight Test Method |
| CN110349130A (en) * | 2019-06-24 | 2019-10-18 | 深圳前海达闼云端智能科技有限公司 | Method and device for detecting aircraft air inlet and storage medium |
| CN111994301A (en) * | 2020-08-18 | 2020-11-27 | 常州华创航空科技有限公司 | Helicopter transmission system test device and system |
| CN112407328A (en) * | 2020-11-20 | 2021-02-26 | 中国直升机设计研究所 | Method for evaluating rain erosion resistance of helicopter rotor blade protective material |
| CN114030636A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Design method for air inlet channel configuration of front output shaft engine helicopter |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2214958A (en) * | 1988-02-10 | 1989-09-13 | Ronald Albert William Clarke | Aircraft runway with grooved surface |
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| US20110252863A1 (en) * | 2010-04-15 | 2011-10-20 | Cessna Aircraft Company | On-Board Water Spray System For Aircraft |
-
2013
- 2013-12-02 CN CN201310643675.3A patent/CN104670521B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2214958A (en) * | 1988-02-10 | 1989-09-13 | Ronald Albert William Clarke | Aircraft runway with grooved surface |
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| US20110252863A1 (en) * | 2010-04-15 | 2011-10-20 | Cessna Aircraft Company | On-Board Water Spray System For Aircraft |
Non-Patent Citations (2)
| Title |
|---|
| 戚学锋，曾涛: "民用飞机动力装置溅水试验适航验证方法", 《航空发动机》 * |
| 毛文懿，李涛，贾洪: "运输类飞机溅水试验适航验证要求分析", 《国际航空》 * |
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|---|---|---|---|---|
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| CN105571880A (en) * | 2016-01-26 | 2016-05-11 | 西北工业大学 | Tyre splashing test device |
| CN106383859B (en) * | 2016-08-31 | 2020-11-03 | 北京蓝天航空科技股份有限公司 | Analysis processing method for test flight data |
| CN106383859A (en) * | 2016-08-31 | 2017-02-08 | 北京蓝天航空科技股份有限公司 | Test flight data analysis processing method |
| CN107576283A (en) * | 2017-09-08 | 2018-01-12 | 中国飞行试验研究院 | Determine that aircraft dabbles the method for angle indirectly by optical measurement parameter |
| CN107576283B (en) * | 2017-09-08 | 2021-08-03 | 中国飞行试验研究院 | Method for indirectly determining aircraft water splash angle by means of optical measurement parameters |
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