CN103158887A - Fixed wing aircraft open-water-area ditching test apparatus - Google Patents
Fixed wing aircraft open-water-area ditching test apparatus Download PDFInfo
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- CN103158887A CN103158887A CN2012102785271A CN201210278527A CN103158887A CN 103158887 A CN103158887 A CN 103158887A CN 2012102785271 A CN2012102785271 A CN 2012102785271A CN 201210278527 A CN201210278527 A CN 201210278527A CN 103158887 A CN103158887 A CN 103158887A
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Abstract
The invention relates to a fixed wing aircraft open-water-area ditching test apparatus which is composed of a front gantry bracket (1), a middle support (2), a rear gantry bracket (3), a tail adjusting device, a throwing-in support (4), a tackle track (5), a weight throwing-in device, a damping device, a small tackle (6), a model throwing-in control device and a speed test device. The fixed wing aircraft open-water-area ditching test apparatus has the advantages that experimental requirements for fixed wing aircraft ditching under a stagnant-water state and a wave state are met, different throwing-in attitude angles of the an aircraft model are achieved, experimental projects which cannot completed in a pool are solved, and the fixed wing aircraft open-water-area ditching test apparatus is clear in design principle, and has strong operability, namely, maintainability.
Description
Technical field
The present invention relates to a kind of fixed wing aircraft open waters ditching experimental set-up.
Background technology
According to " the 25th airplane in transportation category airworthiness standard of CCAR " (CCAR-25-R3) in § 25.801 ditchings (c) the clause regulation that " must pass through model test; or the aircraft similar to the configuration of known its ditching characteristics compares; check most probably motion and state when aircraft force-lands on the water ", under the prerequisite without the similar configuration aircraft reference of known its ditching characteristics, the airplane in transportation category of development must obtain airworthiness certificate by model ditching test.
At present, because China's aviation industry is started late, civil fixed-wing aircraft open waters ditching test belongs in China to be carried out first, also there is no at home open waters ditching experimental set-up.
Summary of the invention
Purpose of the present invention is exactly at present, because China's aviation industry is started late, civil fixed-wing aircraft open waters ditching test belongs in China to be carried out first, also there is no at home the deficiency of open waters ditching experimental set-up, and a kind of fixed wing aircraft open waters ditching experimental set-up is provided.
the present invention is by front gantry support, midship mounting, rear gantry support, the afterbody control apparatus, throw in support, pulley rail, the weight delivery device, shock absorber, jigger, control setup thrown in by model and speed testing device forms, and midship mounting is thrown in support one end and is movably arranged on front gantry support between front gantry support and rear gantry support, and the other end is arranged on the afterbody control apparatus, and the afterbody control apparatus is by base, motor and screw rod form, motor is arranged on base, screw rod is arranged on base, the power take-off shaft of motor is connected with screw rod one end transmission, throw in the support other end and have tapped bore, tapped bore and the screw flight of throwing in support match, and pulley rail is arranged on to be thrown on support, and the weight delivery device is by the hoisting DC electromagnet, the fixed pulley group, running block, steel rope, A pulley and B pulley form, the hoisting DC electromagnet is arranged on rear gantry support, the fixed pulley group is arranged on rear gantry support top by hanger, running block is arranged on the base of hoisting DC electromagnet by mount pad, the A pulley is arranged on by mount pad and throws in the support front end, the B pulley is arranged on the pulley rail front end by mount pad, steel rope one end is connected with the pulley frame of fixed pulley group, steel rope is on fixed pulley group and running block, the other end is positioned on A pulley and B pulley, and be connected with jigger one end, jigger is arranged on pulley rail 5 by wheel, shock absorber is by a pair of bushing pipe, the left chain wheel group, the right pulley group, a pair of clump weight, the A cable wire, the B cable wire, left support abutment, left chain wheel, right support abutment, right pulley and buffering dolly form, and a pair of bushing pipe lays respectively at the left side of midship mounting, right both sides, the left chain wheel group is arranged on midship mounting, and the right pulley group is arranged on midship mounting, clump weight is positioned at bushing pipe, the A cable wire is positioned on the left chain wheel group, and an end is connected with clump weight, and the other end is on left chain wheel, and be connected with the buffering dolly, the B cable wire is positioned on the right pulley group, and an end is connected with clump weight, and the other end is on right pulley, and be connected with the buffering dolly, left support abutment and right support abutment are arranged on respectively the left side of midship mounting, on right pillar, left chain wheel is arranged on left support abutment by mount pad, and right pulley is arranged on right support abutment by mount pad, and the buffering dolly is arranged on the front end of throwing in support by pulley, and model is thrown in control setup by a pair of front leg strut, a pair of front rod, a pair of A electromagnet, rear support leg, rear linking rod, B electromagnet and electromagnetism dispenser form, a pair of front leg strut is arranged on respectively jigger front end both sides, front rod is arranged on front leg strut one end, the A electromagnet is arranged on front rod one end, rear support leg is arranged on the jigger rear end, rear linking rod is arranged on rear support leg one end, the B electromagnet is arranged on rear linking rod one end, the electromagnetism dispenser is arranged on jigger by hanger, speed testing device is comprised of photoelectric switch and a pair of tablet, photoelectric switch is arranged on pulley rail, a pair of tablet be arranged on respectively jigger before, rear two ends.
The electromagnetism dispenser is comprised of box body, coil, fixed link, spring, slide block, hook and lid, coil is arranged in box body, fixed link is arranged in box body, slide block is arranged in box body, spring housing is contained on fixed link, and an end is connected with fixed link one end by adapter plate, the other end is connected with slide block, have the fixed link mounting hole on slide block, fixed link one end is positioned at the mounting hole of slide block, the slide block two ends are respectively equipped with A projection and B projection, and hook is arranged in box body by the hook axle, and lid is connected with box body by bolt.
Advantage of the present invention is mainly manifested in the following aspects:
A) realized input speed up to 23m/s;
B) by to throwing in the integrally-regulated of support, realized the rate of sinking of the 1m/s of model, satisfy fixed wing aircraft ditching test requirements document;
C) integrally-regulated by to the input pole that is connected with model realized the release altitude requirement of different model aircrafts, satisfies the requirement of experiment under fixed wing aircraft ditching hydrostatic state and wave state;
D) by the adjusting of respectively throwing in pole to being connected with model, realized that the difference of model aircraft is thrown in attitude angle;
E) design and used the model putting control system, realized fixed point and synchronous input of model aircraft;
F) design and used the short range shock absorber, solved the parking problem after the coaster high-speed motion, avoid the athletic posture that coaster stops after model is thrown in to cause interference;
G) realized in the model aircraft test having solved with the requirement of angle of side slip the experimental project that can not complete in the pond;
H) this device principle of design is clear, has stronger operability namely maintainable.
Description of drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 is the buffer unit structure schematic diagram.
Fig. 3 throws in support and afterbody control apparatus structural representation.
Fig. 4 is electromagnetism dispenser structural representation.
Fig. 5 is weight delivery device structural representation.
Fig. 6 is fixed pulley group and running block structural representation.
Fig. 7 is that model is thrown in the control setup structural representation.
Fig. 8 is the jigger structural representation.
The specific embodiment
as shown in Figure 1, the present invention is by front gantry support 1, midship mounting 2, rear gantry support 3, the afterbody control apparatus, throw in support 4, pulley rail 5, the weight delivery device, shock absorber, jigger 6, control setup thrown in by model and speed testing device forms, midship mounting 2 is between front gantry support 1 and rear gantry support 3, throwing in support 4 one ends is movably arranged on front gantry support 1, the other end is arranged on the afterbody control apparatus, the afterbody control apparatus is by base 7, motor 8 and screw rod 9 form, motor 8 is arranged on base 7, screw rod 9 is arranged on base 1, the power take-off shaft of motor 8 is connected with screw rod 9 one end transmissions, throw in support 4 other ends and have tapped bore, tapped bore and screw rod 9 screw threads of throwing in support 4 match, pulley rail 5 is arranged on to be thrown on support 4, the weight delivery device is by hoisting DC electromagnet 10, fixed pulley group 11, running block 12, steel rope 13, A pulley 14 and B pulley 15 form, hoisting DC electromagnet 7 is arranged on rear gantry support 3, fixed pulley group 11 is arranged on rear gantry support 3 tops by hanger, running block 12 is arranged on the base 7-1 of hoisting DC electromagnet 7 by mount pad, A pulley 14 is arranged on by mount pad and throws in support 4 front ends, B pulley 15 is arranged on pulley rail 5 front ends by mount pad, steel rope 13 1 ends are connected with the pulley frame of fixed pulley group 11, steel rope 13 is on fixed pulley group 11 and running block 12, the other end is positioned on A pulley 14 and B pulley 15, and be connected with jigger one end 6, jigger 6 is arranged on pulley rail 5 by wheel, shock absorber is by a pair of bushing pipe 23, left chain wheel group 24, right pulley group 25, a pair of clump weight 26, A cable wire 27-1, B cable wire 27-2, left support abutment 28, left chain wheel 29, right support abutment 30, right pulley 31 and buffering dolly 32 form, a pair of bushing pipe 23 lays respectively at the left side of midship mounting 2, right both sides, left chain wheel group 24 is arranged on midship mounting 2, right pulley group 25 is arranged on midship mounting 2, clump weight 26 is positioned at bushing pipe 23, A cable wire 27-1 is positioned on left chain wheel group 24, one end is connected with clump weight 26, the other end is on left chain wheel 29, and be connected with buffering dolly 32, B cable wire 27-2 is positioned on right pulley group 25, one end is connected with clump weight 26, the other end is on right pulley 31, and be connected with buffering dolly 32, left support abutment 28 and right support abutment 30 are arranged on respectively the left side of midship mounting 2, on right pillar, left chain wheel 29 is arranged on left support abutment 28 by mount pad, right pulley 31 is arranged on right support abutment 30 by mount pad, buffering dolly 32 is arranged on the front end of throwing in support 4 by pulley, model is thrown in control setup by a pair of front leg strut 16, a pair of front rod 17, a pair of A electromagnet 18, rear support leg 19, rear linking rod 20, B electromagnet 21 and electromagnetism dispenser 22 form, a pair of front leg strut 16 is arranged on respectively jigger 6 front end both sides, front rod 17 is arranged on front leg strut 16 1 ends, A electromagnet 18 is arranged on front rod 17 1 ends, rear support leg 19 is arranged on jigger 6 rear ends, rear linking rod 20 is arranged on rear support leg 19 1 ends, B electromagnet 21 is arranged on rear linking rod 20 1 ends, electromagnetism dispenser 22 is arranged on jigger 6 by hanger, speed testing device is comprised of photoelectric switch and a pair of tablet 24, photoelectric switch is arranged on pulley rail 5, a pair of tablet 24 be arranged on respectively jigger 6 before, rear two ends.
electromagnetism dispenser 22 is by box body 33, coil 34, fixed link 35, spring 36, slide block 37, hook 38 and lid 39 form, coil 34 is arranged in box body 33, fixed link 35 is arranged in box body 33, slide block 37 is arranged in box body 33, spring 36 is sleeved on fixed link 35, and an end is connected with fixed link 35 1 ends by adapter plate, the other end is connected with slide block 37, have fixed link 35 mounting holes on slide block 37, fixed link 35 1 ends are positioned at the mounting hole of slide block 37, slide block 37 two ends are respectively equipped with A projection 37-1 and B projection 37-2, hook 38 is arranged in box body 33 by the hook axle, lid 39 is connected with box body 33 by bolt.
Afterbody control apparatus effect: drive screw rod 9 by motor 8 and rotate, can regulate the height of throwing in support 4 one ends according to forced landing test needs, reach the test height of forced landing test.
weight delivery device effect: before the test of force-landing, one pipe link first is installed on model aircraft, pipe link one end is equipped with link, then the hook 38 by the electromagnetism dispenser tangles the link on model aircraft, A electromagnet 18 on a pair of front rod 17 of model input control setup is adsorbed on respectively the wing both sides of model aircraft, B electromagnet 21 on rear linking rod 20 is adsorbed on the afterbody (the model putting control system plays the effect of determining the model placement position) of model aircraft, start hoisting DC electromagnet 10, steel rope 13 drives jigger 6, jigger 6 moves on pulley rail 5, drive the model aircraft motion on pulley rail 5, the weight delivery device provides power to whole delivery device, fixed pulley group 11, running block 12, A pulley 14 and B pulley 15 play raising speed, increase move distance and the effect (for jigger 6) that reduces acceleration/accel.
The effect of shock absorber: before the test of force-landing, pour a certain amount of water in bushing pipe 23, when jigger 6 moves rapidly forward, the baffle plate 6-1 of jigger 6 front ends can bump with buffering dolly 32, this moment, the clump weight 26 of A cable wire 27-1 and B cable wire 27-2 one end upwards moved in bushing pipe 23, because the water in bushing pipe 23 has applied resistance to clump weight 26, and then jigger 6 has been played buffer action, assurance allows jigger 6 safety, pulsation-free lower speed, prevent the jigger track that flies out, damage model.
Speed testing device effect: when jigger 6 moves on pulley rail 5, when the tablet 24 on jigger 6 passes through photoelectric switch, photoelectric switch inputs to the PLC controller with tachometer signal, the PLC controller is controlled electromagnetism dispenser 22, when magnet coil gets electricly, slide block moves up by suction, until slide block and hook 38 two ends, top break away from, link up with 38 motions this moment until hook opens fully, the link on model aircraft is broken away from hook 38.
Claims (2)
1. fixed wing aircraft open waters ditching experimental set-up, it is characterized in that it is by front gantry support (1), midship mounting (2), rear gantry support (3), the afterbody control apparatus, throw in support (4), pulley rail (5), the weight delivery device, shock absorber, jigger (6), control setup thrown in by model and speed testing device forms, midship mounting (2) is positioned between front gantry support (1) and rear gantry support (3), throwing in support (4) one ends is movably arranged on front gantry support (1), the other end is arranged on the afterbody control apparatus, the afterbody control apparatus is by base (7), motor (8) and screw rod (9) form, motor (8) is arranged on base (7), screw rod (9) is arranged on base (1), the power take-off shaft of motor (8) is connected with screw rod (9) one end transmissions, throw in support (4) other end and have tapped bore, tapped bore and screw rod (9) screw thread of throwing in support (4) match, pulley rail (5) is arranged on to be thrown on support (4), the weight delivery device is by hoisting DC electromagnet (10), fixed pulley group (11), running block (12), steel rope (13), A pulley (14) and B pulley (15) form, hoisting DC electromagnet (7) is arranged on rear gantry support (3), fixed pulley group (11) is arranged on rear gantry support (3) top by hanger, running block (12) is arranged on the base (7-1) of hoisting DC electromagnet (7) by mount pad, A pulley (14) is arranged on by mount pad and throws in support (4) front end, B pulley (15) is arranged on pulley rail (5) front end by mount pad, steel rope (13) one ends are connected with the pulley frame of fixed pulley group (11), steel rope (13) is on fixed pulley group (11) and running block (12), the other end is positioned on A pulley (14) and B pulley (15), and be connected with jigger (6) one ends, jigger (6) is arranged on pulley rail (5) by wheel, shock absorber is by a pair of bushing pipe (23), left chain wheel group (24), right pulley group (25), a pair of clump weight (26), A cable wire (27-1), B cable wire (27-2), left support abutment (28), left chain wheel (29), right support abutment (30), right pulley (31) and buffering dolly (32) form, a pair of bushing pipe (23) lays respectively at the left side of midship mounting (2), right both sides, left chain wheel group (24) is arranged on midship mounting (2), right pulley group (25) is arranged on midship mounting (2), clump weight (26) is positioned at bushing pipe (23), A cable wire (27-1) is positioned on left chain wheel group (24), one end is connected with clump weight (26), the other end is on left chain wheel (29), and be connected with buffering dolly (32), B cable wire (27-2) is positioned on right pulley group (25), one end is connected with clump weight (26), the other end is on right pulley (31), and be connected with buffering dolly (32), left support abutment (28) and right support abutment (30) are arranged on respectively the left side of midship mounting (2), on right pillar, left chain wheel (29) is arranged on left support abutment (28) by mount pad, right pulley (31) is arranged on right support abutment (30) by mount pad, buffering dolly (32) is arranged on the front end of throwing in support (4) by pulley, model is thrown in control setup by a pair of front leg strut (16), a pair of front rod (17), a pair of A electromagnet (18), rear support leg (19), rear linking rod (20), B electromagnet (21) and electromagnetism dispenser (22) form, a pair of front leg strut (16) is arranged on respectively jigger (6) front end both sides, front rod (17) is arranged on front leg strut (16) one ends, A electromagnet (18) is arranged on front rod (17) one ends, rear support leg (19) is arranged on jigger (6) rear end, rear linking rod (20) is arranged on rear support leg (19) one ends, B electromagnet (21) is arranged on rear linking rod (20) one ends, electromagnetism dispenser (22) is arranged on jigger (6) by hanger, speed testing device is by photoelectric switch, a pair of tablet (24) and PLC controller form, photoelectric switch is arranged on pulley rail (5), a pair of tablet (24) be arranged on respectively jigger (6) before, rear two ends, the signal output part of photoelectric switch is electrically connected to the signal input part of PLC controller, the signal output part of PLC controller is electrically connected to the signal input part of electromagnetism dispenser (22).
2. fixed wing aircraft open waters ditching experimental set-up according to claim 1, it is characterized in that electromagnetism dispenser (22) is by box body (33), coil (34), fixed link (35), spring (36), slide block (37), hook (38) and lid (39) form, coil (34) is arranged in box body (33), fixed link (35) is arranged in box body (33), slide block (37) is arranged in box body (33), spring (36) is sleeved on fixed link (35), and an end is connected with fixed link (35) one ends by adapter plate, the other end is connected with slide block (37), have fixed link (35) mounting hole on slide block (37), fixed link (35) one ends are positioned at the mounting hole of slide block (37), slide block (37) two ends are respectively equipped with A projection (37-1) and B projection (37-2), hook (38) is arranged in box body (33) by the hook axle, lid (39) is connected with box body (33) by bolt.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210278527.1A CN103158887B (en) | 2012-08-08 | 2012-08-08 | Fixed wing aircraft open-water-area ditching test apparatus |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210278527.1A CN103158887B (en) | 2012-08-08 | 2012-08-08 | Fixed wing aircraft open-water-area ditching test apparatus |
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| CN103158887A true CN103158887A (en) | 2013-06-19 |
| CN103158887B CN103158887B (en) | 2015-01-28 |
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Cited By (6)
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| CN103832598A (en) * | 2013-11-18 | 2014-06-04 | 中国特种飞行器研究所 | Water surface aircraft water load full-aircraft power-free model pool test method |
| CN104596729A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Test method for ditching towing tank of fixed-wing airplane model |
| CN106855460A (en) * | 2016-12-20 | 2017-06-16 | 中国船舶重工集团公司第七0研究所 | A kind of air-drop simulation test device with traction |
| CN109515750A (en) * | 2018-12-21 | 2019-03-26 | 中国特种飞行器研究所 | A kind of rotor class aircraft ditching model unloading weight-type lift simulator |
| CN110155368A (en) * | 2019-05-31 | 2019-08-23 | 吉林省农业机械研究院 | A kind of rail mounted flight experiment platform |
| CN112607047A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining suction force at bottom of airplane body of airplane forced landing on water |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103832598A (en) * | 2013-11-18 | 2014-06-04 | 中国特种飞行器研究所 | Water surface aircraft water load full-aircraft power-free model pool test method |
| CN104596729A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Test method for ditching towing tank of fixed-wing airplane model |
| CN104596729B (en) * | 2014-06-26 | 2017-04-26 | 中国特种飞行器研究所 | Test method for ditching towing tank of fixed-wing airplane model |
| CN106855460A (en) * | 2016-12-20 | 2017-06-16 | 中国船舶重工集团公司第七0研究所 | A kind of air-drop simulation test device with traction |
| CN109515750A (en) * | 2018-12-21 | 2019-03-26 | 中国特种飞行器研究所 | A kind of rotor class aircraft ditching model unloading weight-type lift simulator |
| CN109515750B (en) * | 2018-12-21 | 2022-03-15 | 中国特种飞行器研究所 | Unloading weight type lift force simulation device for overwater forced landing model of rotor aircraft |
| CN110155368A (en) * | 2019-05-31 | 2019-08-23 | 吉林省农业机械研究院 | A kind of rail mounted flight experiment platform |
| CN112607047A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining suction force at bottom of airplane body of airplane forced landing on water |
| CN112607047B (en) * | 2020-12-29 | 2022-06-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining suction force at bottom of airplane body of airplane forced landing on water |
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|---|---|
| CN103158887B (en) | 2015-01-28 |
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