CN117002751B - Free flight hooking test simulation system and method for carrier-based aircraft - Google Patents
Free flight hooking test simulation system and method for carrier-based aircraft Download PDFInfo
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- CN117002751B CN117002751B CN202311281880.XA CN202311281880A CN117002751B CN 117002751 B CN117002751 B CN 117002751B CN 202311281880 A CN202311281880 A CN 202311281880A CN 117002751 B CN117002751 B CN 117002751B
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- 238000012360 testing method Methods 0.000 title claims abstract description 141
- 238000004088 simulation Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000004880 explosion Methods 0.000 claims abstract description 84
- 238000005096 rolling process Methods 0.000 claims abstract description 12
- 238000004804 winding Methods 0.000 claims abstract description 5
- 230000005484 gravity Effects 0.000 claims description 15
- 210000001503 joint Anatomy 0.000 claims description 12
- 239000002360 explosive Substances 0.000 claims description 8
- 230000000903 blocking effect Effects 0.000 claims description 5
- 230000001133 acceleration Effects 0.000 claims description 3
- 230000036544 posture Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000012795 verification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000013100 final test Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a free flight hooking test simulation system and method of a carrier-based aircraft, wherein the system comprises a test aircraft, a crane and an air winch which are placed on a test bench and are used for controlling the rolling gesture of the test aircraft, two wings of the test aircraft are respectively provided with a wing clamping plate, the front end and the rear end of the top of each wing clamping plate are respectively provided with a hanging point, each hanging point is internally provided with a first lifting rope, 4 first lifting ropes are gathered upwards at a first explosion point, the rear end of the test aircraft is lifted after being wound for one circle by a second lifting rope, and the winding point of the second lifting rope is provided with a second explosion point. The method comprises the following steps: s1, preparing work; s2, aircraft attitude adjustment; s3, a full-machine drop test; s4, data statistics. The invention can simulate the working condition that the forward landing speed is increased when the carrier-based aircraft freely flies and hooks in a laboratory environment, and can control the forward landing speed more accurately.
Description
Technical Field
The invention relates to the technical field of aviation aircraft tests, in particular to a system and a method for simulating free flight hooking tests of a carrier-based aircraft.
Background
The free flight hooking working condition of the carrier-based aircraft is a working condition of a full-aircraft drop test of the carrier-based aircraft, and is that the carrier-based aircraft is in an upward pitching posture, namely a two-point landing posture, and a blocking rope is hooked in advance under the condition that all landing gears are not contacted with a deck, at the moment, a front landing gear is firstly contacted with the deck, a main landing gear is later contacted with the deck, and the lower pitching rate of the aircraft can cause the front landing gear to land on the ship at a higher sinking speed. The accuracy of the full-machine drop test of the laboratory environment can be effectively improved through accurate simulation of the free flight hooking working condition.
However, at present, the development of the carrier-borne aircraft is still in a starting stage in China, the carrier landing dynamics research on the free flight hooking condition of the carrier-borne aircraft is mostly simulated by utilizing dynamics software, and no experimental verification scheme is provided and experimental verification is carried out.
Disclosure of Invention
Aiming at the problems, the invention provides a system and a method for simulating free flight hooking test of a carrier-based aircraft.
The technical scheme of the invention is as follows:
the free flight hooking test simulation system of the carrier-based aircraft comprises a test aircraft placed on a test bench, a first crane and a second crane for lifting the test aircraft, and a first pneumatic winch and a second pneumatic winch for controlling the rolling gesture of the test aircraft, wherein the first crane and the second crane are respectively fixed on the ground on two sides of the test bench, the first pneumatic winch is fixed on the ground on the inner side of the first crane, and the second pneumatic winch is fixed on the ground on the inner side of the second crane;
two wings of the test aircraft are respectively provided with a wing clamping plate, the two wing clamping plates are symmetrically arranged, the front end and the rear end of the top of each wing clamping plate are respectively provided with a hanging point, each hanging point is internally provided with a first lifting rope, 4 first lifting ropes are gathered upwards at a first explosion point, a first explosion bolt connected with the 4 first lifting ropes is arranged at the first explosion point, and the top of each first explosion bolt is connected with the first crane through a front auxiliary lifting rope;
the rear end of the test aircraft is hoisted after being wound for one circle by a second lifting rope, a second explosion point is arranged at the right upper end of the winding point of the second lifting rope, a second explosion bolt is arranged at the second explosion point, and the top of the second explosion bolt is connected with the second crane by a rear auxiliary lifting rope;
the two same are located on one side the midpoint of the first lifting rope is provided with a first buckle, a first connecting rope is arranged between the two first buckles, and the first connecting rope is correspondingly connected with the output end of the first pneumatic winch.
Further, two second buckles are arranged at the middle of the first connecting rope at intervals, a first lateral auxiliary rope is arranged at the output end of the first pneumatic winch, a first hook is arranged at the tail end of the first lateral auxiliary rope, the first hook is in butt joint with the first connecting rope between the two second buckles, a cross beam is fixedly arranged on two sides above the position where the test aircraft is located, the first lateral auxiliary rope spans the cross beam, when the first hook is in butt joint with the first connecting rope, a third explosion point is arranged at the midpoint of a connecting line from the cross beam position to the first hook position on the first lateral auxiliary rope, and a third explosion bolt is arranged on the first lateral auxiliary rope at the third explosion point.
Description: can cooperate first pneumatic winch to assist to accomplish the spin gesture adjustment to the test aircraft through the setting of first connecting rope, guarantee the stability between first couple and the first connecting rope through two second buckles, can open simultaneously with first explosion bolt through the setting of third explosion bolt, make the test aircraft can respond the release signal with faster speed.
Still further, be located left side rear or right side rear first lifting rope is through being equipped with on it connect through the second between first buckle and the second lifting rope, be equipped with the slip fixture block on the second connecting rope, the slip fixture block includes two fixed blocks, the fixed block middle part is equipped with the through-hole that is used for making the second connecting rope pass, the through-hole below is equipped with the screw hole, threaded hole is equipped with fixing bolt, and the fixed block top rear side that is located the front end rotates and is connected with the screw sleeve, and the fixed block top front side that is located the rear end is equipped with the threaded rod, screw sleeve and threaded rod cup joint each other, are equipped with the handle on the screw sleeve rear end outer wall, the output of second pneumatic winch is equipped with the supplementary rope of second side direction, the end of the supplementary rope of second side direction is equipped with the second couple, the second coupling rope butt joint between second couple and two fixed blocks makes two fixed blocks carry out fixed centre gripping to the second couple, and the supplementary rope of second side direction strides across the crossbeam and the supplementary rope of second side direction is equipped with the fourth explosion point by the second position wire to the fourth explosion point of second side direction.
Description: the adjustment to test aircraft side rear roll angle can be assisted through the setting of second connecting rope to realize the simulation of various different roll attitudes, press close to in real condition more, can realize the determination to second couple hook point position through the setting of slip fixture block, improve the stability of second couple simultaneously, can open with first explosion bolt is synchronous through the setting of fourth explosion bolt simultaneously, makes test aircraft can respond to release signal with faster speed.
Preferably, the first and second explosion points are both located directly above the central axis of the test aircraft.
Description: the positions of the first explosion point and the second explosion point are optimally adjusted, so that the whole test system is more stable, and the success rate of the test is improved.
The invention also provides a simulation method for the free flight hooking test of the carrier-based aircraft, which is based on the simulation system for the free flight hooking test of the carrier-based aircraft and comprises the following steps:
s1, preparing: the wing clamping plate is installed, a first lifting rope is installed in each hanging point, a second lifting rope is wound at the rear end of the test aircraft, a first explosion bolt and a second explosion bolt are installed, and a first crane and a second crane are started to lift the test aircraft;
s2, aircraft attitude adjustment: the output end of the first pneumatic winch is in butt joint with the middle part of the first connecting rope, then the first pneumatic winch is started, so that the first connecting rope is pulled by the first pneumatic winch, the test aircraft rolls to one side, and the rolling gesture of the aircraft is simulated;
s3, a full-machine drop test: starting a first explosion bolt to enable a first crane to release a test aircraft, simultaneously, releasing the butt joint of the output end of a first pneumatic winch and a first connecting rope to enable the front end of the test aircraft to fall, then starting a second explosion bolt to enable a second crane to release the test aircraft, and further simulating the condition that a nose landing gear of a carrier aircraft firstly contacts a deck and a main landing gear contacts the deck under the action of a blocking hook;
s4, data statistics: and collecting the speed data of the front landing gear contact platform of the tested aircraft.
Further, in the step S1, the lifting height of the first crane is greater than the lifting height of the second crane, so that the front end of the test aircraft rotates about the centroid by 0-10 °.
Description: the pitching rotation angle of the aircraft is optimally adjusted and tested, so that the aircraft is more close to the actual ship-borne aircraft landing situation.
Further, the lifting height of the gravity center of the test aircraft in the step S1 is determined by the initial sinking speed of the gravity center of the test aircraft:
h=v 2 /2g
wherein h is the lifting height of the gravity center of the test aircraft, v is the initial sinking speed of the gravity center of the test aircraft, the value range of v is 2-4 m/s, and g is the gravity acceleration.
Further, in the step S2, the first pneumatic winch pulls the first connecting rope to roll the test aircraft to one side by an angle of 0-30 °.
Description: the simulation of various different conditions can be realized by optimizing and adjusting the lateral rolling angle of the test aircraft, and the simulation meets the actual carrier-based aircraft landing condition.
Further, in the step S3, the opening time interval of the first explosion bolt and the second explosion bolt is 0.1-0.5S.
Description: the opening time interval of the first explosion bolt and the second explosion bolt is optimally adjusted, so that the real situation of the carrier-based aircraft landing is more similar.
The beneficial effects of the invention are as follows:
the free flight hooking test simulation system of the carrier-based aircraft can simulate the working condition that the landing speed is increased before the carrier-based aircraft is hooked in free flight in a laboratory environment, and can realize the working condition that the carrier-based aircraft is simulated to be lifted before the aircraft is hooked by a blocking hook in the laboratory on the premise of not increasing the throwing height of a test piece, so that a larger sinking speed touch table appears, and the release mode of adopting the explosion bolt interval release has the characteristics of high stability and quick response, so that the control of the forward lifting sinking speed is more accurate;
according to the ship-based aircraft free flight hooking test simulation system, the rolling gesture adjustment of the test aircraft can be completed in an auxiliary way by matching with the first pneumatic winch through the arrangement of the first connecting rope, the stability between the first hook and the first connecting rope is ensured through the two second buckles, and meanwhile, the test aircraft can synchronously start with the first explosion bolt through the arrangement of the third explosion bolt, so that the test aircraft can respond to a release signal at a higher speed; the second connecting rope can be matched with the second pneumatic winch to assist in adjusting the side rear rolling angle of the test aircraft, so that simulation of various rolling postures is realized, the simulation is closer to the actual situation, the hook point position of the second hook can be determined through the arrangement of the sliding clamping block, meanwhile, the stability of the second hook is improved, and meanwhile, the test aircraft can respond to a release signal at a higher speed through the arrangement of the fourth explosion bolt;
according to the simulation method for the free flight hooking test of the carrier-based aircraft, provided by the invention, the pitching rotation angle of the test aircraft is optimally adjusted, the lateral rolling angle of the test aircraft is optimally adjusted, and the opening time interval of the first explosion bolt and the second explosion bolt is optimally adjusted, so that the simulation method is more similar to the real situation of the carrier-based aircraft during landing, and the accuracy of test data is improved.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a free flight hooking test simulation system of a carrier-based aircraft of the invention;
FIG. 2 is a schematic diagram of the overall structure of the free flight hooking test simulation system of the carrier-based aircraft of the present invention without the second connecting rope installed;
FIG. 3 is a schematic view of the head direction of the free flight hooking test simulation system of the carrier-based aircraft of the present invention after the aircraft is lifted;
FIG. 4 is a schematic view of the head direction of the free flight hooking test simulation system of the carrier-based aircraft of the present invention after the aircraft is lifted and the roll attitude is adjusted;
FIG. 5 is a side view of the free flight hooking test simulation system of the present invention for a carrier-based aircraft in an aircraft lifted position and with the roll attitude adjusted via a second connecting rope;
FIG. 6 is a schematic view of the connection and fixation structure of the first connecting rope and the first hook of the free flight hooking test simulation system of the carrier-based aircraft;
FIG. 7 is a schematic diagram of a connection structure between a second connection rope and a sliding fixture block of the simulation system for the free flight hooking test of the carrier-based aircraft;
FIG. 8 is a schematic diagram of the internal structure of a sliding fixture block of the free flight hooking test simulation system of the carrier-based aircraft of the invention;
FIG. 9 is a flow chart of a method for simulating a free flight hooking test of a carrier-based aircraft according to the invention;
the device comprises a 1-test bench, 11-cross beams, 2-test aircrafts, 21-first lifting ropes, 22-second lifting ropes, 23-first buckles, 24-first connecting ropes, 25-second buckles, 26-second connecting ropes, 3-first cranes, 31-first explosion bolts, 32-front auxiliary lifting ropes, 4-second cranes, 41-second explosion bolts, 42-rear auxiliary lifting ropes, 5-first pneumatic winches, 51-first lateral auxiliary ropes, 52-first hooks, 53-third explosion bolts, 6-second pneumatic winches, 61-second lateral auxiliary ropes, 62-second hooks, 63-fourth explosion bolts, 7-wing clamping plates, 71-hanging points, 8-sliding clamping blocks, 81-fixing blocks, 82-through holes, 83-threaded holes, 84-fixing bolts, 85-threaded sleeves, 86-threaded rods and 87-handles.
Detailed Description
Example 1: as shown in fig. 3, the free flight hooking test simulation system of the ship-based aircraft comprises a test aircraft 2 placed on a test bench 1, a first crane 3 and a second crane 4 for hoisting the test aircraft 2, a first pneumatic winch 5 and a second pneumatic winch 6 for controlling the rolling posture of the test aircraft 2, wherein the first crane 3 and the second crane 4 are respectively fixed on the ground on two sides of the test bench 1, the first pneumatic winch 5 is fixed on the ground on the inner side of the first crane 3, the second pneumatic winch 6 is fixed on the ground on the inner side of the second crane 4, commercially available stress sensors are arranged on the test bench 1, a front landing gear, a main landing gear and a tire of the test aircraft 2, and the first crane 3, the second crane 4, the first pneumatic winch 5 and the second pneumatic winch 6 are commercially available products;
as shown in fig. 1, 2 and 3, two wings of the test aircraft 2 are respectively provided with a wing clamping plate 7, the two wing clamping plates 7 are symmetrically arranged, the front end and the rear end of the top of each wing clamping plate 7 are respectively provided with a hanging point 71, each hanging point 71 is internally provided with first lifting ropes 21,4 first lifting ropes 21 which are gathered upwards at first explosion points, the first explosion points are provided with first explosion bolts 31 connected with the 4 first lifting ropes 21, and the top of each first explosion bolt 31 is connected with the first crane 3 through a front auxiliary lifting rope 32; the rear end of the test aircraft 2 is hoisted after being wound for one circle by the second lifting rope 22, a second explosion point is arranged at the upper end of the winding point of the second lifting rope 22, a second explosion bolt 41 is arranged at the second explosion point, the top of the second explosion bolt 41 is connected with the second crane 4 by a rear auxiliary lifting rope 42, and the first explosion point and the second explosion point are both positioned right above the central axis of the test aircraft 2;
as shown in fig. 3, fig. 4 and fig. 6, a first buckle 23 is arranged at the middle point of two first lifting ropes 21 positioned at one side, a first connecting rope 24 is arranged between the two first buckles 23, the first connecting rope 24 is correspondingly connected with the output end of a first pneumatic winch 5, two second buckles 25 are arranged at intervals in the middle of the first connecting rope 24, a first lateral auxiliary rope 51 is arranged at the output end of the first pneumatic winch 5, a first hook 52 is arranged at the tail end of the first lateral auxiliary rope 51, the first connecting rope 24 between the first hook 52 and the two second buckles 25 is in butt joint, a cross beam 11 is fixedly arranged at two sides above the position where a test aircraft 2 is positioned, the cross beam 11 is fixed to the other side wall from one side of the laboratory indoor wall, the first lateral auxiliary rope 51 spans across the cross beam 11, when the first hook 52 is in butt joint with the first connecting rope 24, a third explosion point is arranged from the position of the cross beam 11 to the middle point of the connecting line of the position of the first hook 52, a third buckle 53 is arranged on the first lateral auxiliary rope 51, and the first buckles 23, the first hooks 25, the first explosion bolts 53 and the first explosion bolts 41 are all commercial explosion bolts 41;
as shown in fig. 1, fig. 3, fig. 5, fig. 7, fig. 8, be located the first lifting rope 21 of left side rear or right side rear and connect through the second connecting rope 26 between the first buckle 23 that is equipped with on it and the second lifting rope 22, be equipped with slide fixture block 8 on the second connecting rope 26, slide fixture block 8 includes two fixed blocks 81, the fixed block 81 middle part is equipped with the through-hole 82 that is used for making the second connecting rope 26 pass, be equipped with screw hole 83 below the through-hole 82, be equipped with fixing bolt 84 in the screw hole 83, the fixed block 81 top rear side that is located the front end rotates and is connected with threaded sleeve 85, be located the fixed block 81 top front side of rear end and be equipped with threaded rod 86, threaded sleeve 85 and threaded rod 86 cup joint each other, be equipped with handle 87 on the outer wall of threaded sleeve 85 rear end, the output of second pneumatic winch 6 is equipped with second side auxiliary rope 61, second couple 62 is equipped with the end of second side auxiliary rope 61, second couple 62 is equipped with the second connecting rope 26 between two fixed blocks 81, make two fixed blocks 81 stride across second couple 62 after threaded sleeve 85 and threaded rod 86 screw down, make the second couple 81 carry out second couple 62, second couple 62 and second couple 61 is equipped with the second side direction auxiliary rope 61 and take the position to the fourth side direction explosion point is the fourth side direction auxiliary bolt point 11, the explosion point is the position is the fourth side explosion position is the auxiliary bolt point of explosion position is the fourth side explosion position is the auxiliary bolt 11.
Example 2: the method for simulating the free flight hooking test of the carrier-based aircraft is based on a system for simulating the free flight hooking test of the carrier-based aircraft in the embodiment 1, as shown in fig. 9, and comprises the following steps:
s1, preparing: as shown in fig. 2 and 3, the wing clamping plate 7 is installed, the first lifting rope 21 is installed in each hanging point 71, the second lifting rope 22 is wound at the rear end of the test aircraft 2, the first explosion bolt 31 and the second explosion bolt 41 are installed, the first crane 3 and the second crane 4 are started to lift the test aircraft 2, the lifting height of the first crane 3 is the same as the lifting height of the second crane 4, the front end of the test aircraft 2 rotates 0 degrees around the centroid, and the lifting height of the center of gravity point of the test aircraft 2 is determined by the initial sinking speed of the center of gravity point of the test aircraft 2:
h=v 2 /2g
wherein h is the lifting height of the gravity center of the test aircraft 2, v is the initial sinking speed of the gravity center of the test aircraft 2, v is 3m/s, and g is the gravity acceleration;
s2, aircraft attitude adjustment: as shown in fig. 4, the output end of the first pneumatic winch 5 is abutted with the middle part of the first connecting rope 24, then the first pneumatic winch 5 is started to pull the first connecting rope 24 so as to roll the test aircraft 2 to one side, the aircraft rolling posture is simulated, and the first pneumatic winch 5 pulls the first connecting rope 24 so as to roll the test aircraft 2 to one side at an angle of 10 degrees;
s3, a full-machine drop test: starting a first explosion bolt 31 to enable a first crane 3 to release a test aircraft 2, simultaneously, releasing the butt joint of the output end of a first pneumatic winch 5 and a first connecting rope 24 to enable the front end of the test aircraft 2 to fall, then starting a second explosion bolt 41 to enable a second crane 4 to release the test aircraft 2, and further simulating the condition that a nose landing gear of a carrier aircraft firstly contacts a deck and then contacts the deck after a main landing gear under the action of a blocking hook, wherein the starting time interval of the first explosion bolt 31 and the second explosion bolt 41 is 0.3s;
s4, data statistics: the front and main landing gear landing speed data of the test aircraft 2 is collected.
Example 3: this embodiment differs from embodiment 2 in that:
in the step S1, the lifting height of the first crane 3 is larger than that of the second crane 4 so as to enable the front end of the test aircraft 2 to rotate 5 degrees around the mass center, and v is 2m/S;
in step S2, the first pneumatic winch 5 pulls the first connecting rope 24 to roll the test aircraft 2 to one side by an angle of 20 °;
the opening time interval of the first explosive bolt 31 and the second explosive bolt 41 in step S3 is 0.1S.
Example 4: this embodiment differs from embodiment 2 in that:
in the step S1, the lifting height of the first crane 3 is larger than that of the second crane 4 so as to enable the front end of the test aircraft 2 to rotate 10 degrees around the mass center, and v is 4m/S;
in step S2, the first pneumatic winch 5 pulls the first connecting rope 24 to roll the test aircraft 2 to one side at an angle of 30 °;
the opening time interval of the first explosive bolt 31 and the second explosive bolt 41 in step S3 is 0.5S.
Example 5: this embodiment differs from embodiment 2 in that:
the lifting height of the first crane 3 is greater than the lifting height of the second crane 4 in step S1 so that the front end of the test aircraft 2 is rotated 3 ° about the centre of mass.
Example 6: this embodiment differs from embodiment 2 in that:
the lifting height of the first crane 3 is greater than the lifting height of the second crane 4 in step S1 so that the front end of the test aircraft 2 is rotated 7.7 ° about the centre of mass.
Working principle: the working principle of the free flight hooking test simulation system of the carrier-based aircraft is further described in detail below by combining the method of the invention.
When the attitude adjustment of the aircraft in step S2 is performed, if the adjustment of the lateral rear roll angle of the test aircraft 2 is required, the adjustment is performed by pulling the second connecting rope 26 through the second hook 62, therefore, when the preparation of step S1 is performed, the second connecting rope 26 and the sliding fixture block 8 are required to be installed, the second lateral auxiliary rope 61 of the second pneumatic winch 6 bypasses the cross beam 11, the position of the sliding fixture block 8 is required to be accurately positioned, the fixing bolt 84 is firstly unscrewed during the adjustment, so that the fixing bolt 84 moves downwards in the threaded hole 83, the clamping of the second connecting rope 26 is loosened, so that the two fixing blocks 81 can move through the through hole 82, after the adjustment is performed to a proper position, the second hook 62 is butted on the second connecting rope 26 between the two fixing blocks 81, then the threaded sleeve 85 is rotated through the handle 87, the threaded rod 86 is tightened under the action of the threaded engagement, the distance between the two fixing blocks 81 is reduced, the clamping of the second hook 62 is completed, and finally the fixing bolt 84 is screwed, so that the fixing bolt 84 moves upwards in the threaded hole 83, and the second connecting rope 26 is clamped;
in the step S3 full-machine drop test, the first explosive bolt 31 and the fourth explosive bolt 63 are simultaneously opened.
It should be noted that, the connection between the threaded sleeve 85 and the side wall of the fixed block 81 is provided with an L-shaped rotating ring, and the rotating ring is rotationally embedded in a rotating groove provided on the side wall of the fixed block 81, so that the threaded sleeve 85 and the fixed block 81 do not break away while relatively rotating.
Test example: taking the test parameters in example 5 and example 6 as examples, the mass of the test aircraft 2 was 14000kg, and the final test results are shown in table 1.
TABLE 1 free flight hook condition
As shown in table 1, the test aircraft 2 was able to approximate free-fall motion due to its short drop time while performing free-fall motion with rotational angular velocity, with the forward and main landing gear increasing in vertical velocity increments consistent. The process of rotating the airplane around the rear hanging point can be simplified into the motion process of a simple pendulum to be estimated, and the airplane can provide enough sinking speed around the rear hanging point.
Claims (7)
1. The free flight hooking test simulation system of the ship-based aircraft is characterized by comprising a test aircraft (2) placed on a test bench (1), a first crane (3) and a second crane (4) for hoisting the test aircraft (2), and a first pneumatic winch (5) and a second pneumatic winch (6) for controlling the rolling posture of the test aircraft (2), wherein the first crane (3) and the second crane (4) are respectively fixed on the ground at two sides of the test bench (1), the first pneumatic winch (5) is fixed on the ground at the inner side of the first crane (3), and the second pneumatic winch (6) is fixed on the ground at the inner side of the second crane (4);
two wings of the test aircraft (2) are respectively provided with a wing clamping plate (7), the two wing clamping plates (7) are symmetrically arranged, the front end and the rear end of the top of each wing clamping plate (7) are respectively provided with a hanging point (71), each hanging point (71) is internally provided with a first lifting rope (21), 4 first lifting ropes (21) are upwards converged at a first explosion point, a first explosion bolt (31) connected with the 4 first lifting ropes (21) is arranged at the first explosion point, and the top of each first explosion bolt (31) is connected with the first crane (3) through a front auxiliary lifting rope (32);
the rear end of the test aircraft (2) is hoisted after being wound for one circle by a second lifting rope (22), a second explosion point is arranged at the right upper end of the winding point of the second lifting rope (22), a second explosion bolt (41) is arranged at the second explosion point, and the top of the second explosion bolt (41) is connected with the second crane (4) by a rear auxiliary lifting rope (42);
a first buckle (23) is arranged at the middle point of the two first lifting ropes (21) which are positioned at one side, a first connecting rope (24) is arranged between the two first buckles (23), and the first connecting rope (24) is correspondingly connected with the output end of the first pneumatic winch (5);
two second buckles (25) are arranged in the middle of the first connecting rope (24) at intervals, a first lateral auxiliary rope (51) is arranged at the output end of the first pneumatic winch (5), a first hook (52) is arranged at the tail end of the first lateral auxiliary rope (51), the first connecting ropes (24) between the first hook (52) and the two second buckles (25) are in butt joint, a cross beam (11) is fixedly arranged on two sides above the position where the test aircraft (2) is located, the first lateral auxiliary rope (51) spans the cross beam (11), and when the first hook (52) is in butt joint with the first connecting rope (24), a third explosion point is arranged at the middle point of a connecting line from the position of the cross beam (11) to the position of the first hook (52) on the first lateral auxiliary rope (51), and a third explosion bolt (53) is arranged on the first lateral auxiliary rope (51) at the third explosion point;
the first lifting rope (21) positioned at the left rear side or the right rear side is connected with the second lifting rope (22) through a second connecting rope (26) through a first buckle (23) arranged on the first lifting rope, a sliding clamping block (8) is arranged on the second connecting rope (26), the sliding clamping block (8) comprises two fixing blocks (81), a through hole (82) used for enabling the second connecting rope (26) to pass through is arranged in the middle of the fixing blocks (81), a threaded hole (83) is formed in the lower portion of the through hole (82), a fixing bolt (84) is arranged in the threaded hole (83), a threaded sleeve (85) is rotationally connected to the rear side of the top of the fixing block (81) positioned at the front end, a threaded rod (86) is arranged on the front side of the top of the fixing block (81) positioned at the rear end, the threaded sleeve (85) and the threaded rod (86) are mutually sleeved, a handle (87) is arranged on the outer wall of the rear end of the threaded sleeve (85), a second lateral auxiliary rope (61) is arranged at the output end of the second pneumatic winch (6), a second lateral auxiliary rope (62) is arranged at the tail end, and when the second lateral auxiliary rope (61) is tightly connected with the second hook (62) and the threaded rod (81) through the threaded sleeve (81), the second lateral auxiliary rope (61) spans across the cross beam (11), the midpoint of a connecting line of the second lateral auxiliary rope (61) from the position of the cross beam (11) to the position of the second hook (62) is a fourth explosion point, and a fourth explosion bolt (63) is arranged on the second lateral auxiliary rope (61) at the fourth explosion point.
2. The system for simulating free flight hooking test of a carrier-based aircraft according to claim 1, wherein the first and second explosion points are located directly above the central axis of the test aircraft (2).
3. A method for simulating a free flight hooking test of a carrier-based aircraft, based on the free flight hooking test system of the carrier-based aircraft according to any one of claims 1 to 2, comprising the following steps:
s1, preparing: the method comprises the steps of installing wing clamping plates (7), installing a first lifting rope (21) in each hanging point (71), winding a second lifting rope (22) at the rear end of a test aircraft (2), installing a first explosion bolt (31) and a second explosion bolt (41), and starting a first crane (3) and a second crane (4) to lift the test aircraft (2);
s2, aircraft attitude adjustment: the output end of the first pneumatic winch (5) is in butt joint with the middle part of the first connecting rope (24), then the first pneumatic winch (5) is started, the first connecting rope (24) is pulled by the first pneumatic winch to enable the test aircraft (2) to roll to one side, and the aircraft rolling gesture is simulated;
s3, a full-machine drop test: starting a first explosion bolt (31) to enable a first crane (3) to release a test aircraft (2), simultaneously, releasing the butt joint of the output end of a first pneumatic winch (5) and a first connecting rope (24) to enable the front end of the test aircraft (2) to fall, then starting a second explosion bolt (41) to enable a second crane (4) to release the test aircraft (2), and further simulating the condition that the front landing gear of the carrier aircraft firstly contacts a deck under the action of a blocking hook and then contacts the deck after the main landing gear;
s4, data statistics: front and main landing gear landing speed data of the test aircraft (2) are collected.
4. The simulation method of free flight hooking test of a carrier-based aircraft according to claim 3, wherein in the step S1, the lifting height of the first crane (3) is greater than the lifting height of the second crane (4) so as to enable the front end of the test aircraft (2) to rotate 0-10 ° around the centroid.
5. A method for simulating free flight hooking test of a carrier-based aircraft according to claim 3, wherein the lifting height of the center of gravity of the test aircraft (2) in the step S1 is determined by the initial sinking speed of the center of gravity of the test aircraft (2):
h=v 2 /2g
wherein h is the lifting height of the gravity center of the test aircraft (2), v is the initial sinking speed of the gravity center of the test aircraft (2), the value range of v is 2-4 m/s, and g is gravity acceleration.
6. A method for simulating a free flight hooking test of a carrier-based aircraft according to claim 3, wherein in the step S2, the first connection rope (24) is pulled by the first pneumatic winch (5) to roll the test aircraft (2) to one side by an angle of 0-30 °.
7. The method for simulating free flight hooking test of a carrier-based aircraft according to claim 3, wherein the opening time interval of the first explosive bolt (31) and the second explosive bolt (41) in the step S3 is 0.1-0.5S.
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