CN103837321A - Stability testing method of water surface aircraft real machine - Google Patents
Stability testing method of water surface aircraft real machine Download PDFInfo
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- CN103837321A CN103837321A CN201310575932.4A CN201310575932A CN103837321A CN 103837321 A CN103837321 A CN 103837321A CN 201310575932 A CN201310575932 A CN 201310575932A CN 103837321 A CN103837321 A CN 103837321A
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Abstract
A stability testing method of a water surface aircraft real machine comprises the following steps that (a), water surface aircraft real machine test is prepared; (b), the water surface aircraft real machine test is conducted; (1) ground state of the aircraft is checked; (2) initial state of calm water of the aircraft is checked; (3), the aircraft is heated by an aircraft engine; (4), the aircraft skis water for 5-6 seconds in the same speed, each test condition repeats for 2-3 times; (5), water skiing state of the aircraft needs to be observed; (6), according to test data and test phenomena, the stability of the water surface aircraft is judged. The stability testing method of the water surface aircraft real machine has the advantages of being practical, feasible, simple in operation, reliable in testing results, and wide in application range.
Description
Technical field
Hydrodynamic performance test field when the water surface flying device hydroplaning that the present invention relates to seaplane, amphibious aircraft, land-effect plane (ground effect ship) and other new ideas is taken off, is specifically related to a kind of test unit and test method thereof of hydrodynamic performance.
Background technology
Water surface flying device stability refers on any normal operating speed on the water surface, and water surface flying device must not adventurous or uncontrollable kinetic characteristic.It is the important technology index of weighing water surface flying device hydrodynamic(al) performance.Along with water surface flying device usable range requires to significantly improve, its stability is also had higher requirement at present.For checking water surface flying device stability, main by the scale model stability test of water surface flying device pond, water surface flying device free flight scale model open waters stability test and the stability test of water surface flying device real machine at present.Real machine stability test is checking to pond scale model stability test and the stability test of free flight scale model and perfect.The stability test of water surface flying device real machine is carried out according to the hydroplaning situation of Live Flying device completely, slide aircraft movements state in process, movement locus, attitude variation etc. by observation the stability of aircraft judged, in checking water surface flying device model basin water surface stability test result for the stability test of follow-up water surface flying device wave provides reference frame.Also there is not at present a kind of water surface flying device real machine stability testing method of practicality.
Summary of the invention
The object of the invention is for above-mentioned deficiency, and a kind of water surface flying device real machine stability testing method is provided.
Test procedure of the present invention is as follows:
A) before water surface flying device real machine test, prepare:
With reference to water surface flying device model basin stability test state, real machine is carried out to the counterweight of corresponding trystate and the debugging of center of gravity inertia, generally, real machine centre of gravity place must not be overproof 1%, and weight must not be overproof 2%, and inertia must not overproof 5%;
Real machine hydrostatic floading condition should be with reference to water surface flying device model basin stability test hydrostatic floading condition, and attitude error is no more than 0.1 degree;
Engine answers break-in abundant, and carries out thrust test, records the relation between thrust T and rotational speed N, power P;
Flap angle is fixed as aircraft takeoff flap angle, and elevating rudder is initially 0 degree;
Data acquisition equipment comprises gyroscope and acceleration transducer, gathers respectively attitude angle variation, vertical acceleration and the longitudinal acceleration of real machine;
B) water surface flying device real machine test:
1) the aircraft state of ground checks, ensures that aircraft trystate is normal, can test, and conventionally first tests with minimum take-off weight;
2) the initial hydrostatic status checking of aircraft, the original trim angle of recording aircraft
, initial horizontal inclination angle
, bow aft draft and faulted-stage draft;
3) the hot car of aircraft engine, recording engine rotational speed N, pulling force T, power P;
4) aircraft constant speed water skiing 5 ~ 6 seconds, every trystate repeats 2 ~ 3 times;
5) observation flight device water skiing state, records correlation test data and experimental phenomena;
6), according to test figure and experimental phenomena, with reference to water surface flying device determination of stability weighing apparatus is accurate, real machine stability is judged.
Advantage of the present invention is: the method practicality, feasible, simple to operate, test findings is reliable, applied widely.
Embodiment
Test procedure of the present invention is as follows:
A) before water surface flying device real machine test, prepare:
With reference to water surface flying device model basin stability test state, real machine is carried out to the counterweight of corresponding trystate and the debugging of center of gravity inertia, generally, real machine centre of gravity place must not be overproof 1%, and weight must not be overproof 2%, and inertia must not overproof 5%;
Real machine hydrostatic floading condition should be with reference to water surface flying device model basin stability test hydrostatic floading condition, and attitude error is no more than 0.1 degree;
Engine answers break-in abundant, and carries out thrust test, records the relation between thrust T and rotational speed N, power P;
Flap angle is fixed as aircraft takeoff flap angle, and elevating rudder is initially 0 degree;
Data acquisition equipment comprises gyroscope and acceleration transducer, gathers respectively attitude angle variation, vertical acceleration and the longitudinal acceleration of real machine;
B) water surface flying device real machine test:
1) the aircraft state of ground checks, ensures that aircraft trystate is normal, can test, and conventionally first tests with minimum take-off weight;
2) the initial hydrostatic status checking of aircraft, the original trim angle of recording aircraft
, initial horizontal inclination angle
, bow aft draft and faulted-stage draft;
3) the hot car of aircraft engine, recording engine rotational speed N, pulling force T, power P;
4) aircraft constant speed water skiing 5 ~ 6 seconds, every trystate repeats 2 ~ 3 times;
5) observation flight device water skiing state, records correlation test data and experimental phenomena;
6), according to test figure and experimental phenomena, with reference to water surface flying device determination of stability weighing apparatus is accurate, real machine stability is judged.
Result evaluation:
Test data analyzer personnel carry out determination of stability in conjunction with experimental phenomena according to following weighing apparatus standard according to experimental phenomena:
A), under extraneous (wind, the wave) disturbed condition of nothing, in aircraft water skiing process, be stable without pitching phenomenon.
B) under extraneous (wind, wave) disturbed condition, not making rudder and partially revise, is unstable if aircraft pitching diffuses to 7-8 degree, and convergence is judged to be to stablize.
C) under extraneous (wind, wave) disturbed condition, the aircraft motion that pitches, it is unstable exceeding human body ability to bear.
D) aircraft is with at the uniform velocity water skiing process, under different time or when different displacement, attitude of flight vehicle angle change be judged to be unstable.
E), in aircraft water skiing process, there is dolphin motion, change the inclined to one side correction effect of rudder not obvious be judged to be unstable.
F) in aircraft high speed (get away speed is more than 80%) water skiing process, occur that jump phenomena is judged to be unstable.
G) the dummy vehicle basin test lower limit of stability too low (being less than 2 degree), aircraft real machine high speed slide attitude angle is less than 2.5 degree and is judged to be unstable.
H) in aircraft takeoff process, occur that driftage is judged to be unstable.
Claims (1)
1. a water surface flying device real machine stability testing method, is characterized in that test procedure is as follows:
A) before water surface flying device real machine test, prepare:
With reference to water surface flying device model basin stability test state, real machine is carried out to the counterweight of corresponding trystate and the debugging of center of gravity inertia, generally, real machine centre of gravity place must not be overproof 1%, and weight must not be overproof 2%, and inertia must not overproof 5%;
Real machine hydrostatic floading condition should be with reference to water surface flying device model basin stability test hydrostatic floading condition, and attitude error is no more than 0.1 degree;
Engine answers break-in abundant, and carries out thrust test, records the relation between thrust T and rotational speed N, power P;
Flap angle is fixed as aircraft takeoff flap angle, and elevating rudder is initially 0 degree;
Data acquisition equipment comprises gyroscope and acceleration transducer, gathers respectively attitude angle variation, vertical acceleration and the longitudinal acceleration of real machine;
B) water surface flying device real machine test:
1) the aircraft state of ground checks, ensures that aircraft trystate is normal, can test, and conventionally first tests with minimum take-off weight;
2) the initial hydrostatic status checking of aircraft, the original trim angle of recording aircraft
, initial horizontal inclination angle
, bow aft draft and faulted-stage draft;
3) the hot car of aircraft engine, recording engine rotational speed N, pulling force T, power P;
4) aircraft constant speed water skiing 5 ~ 6 seconds, every trystate repeats 2 ~ 3 times;
5) observation flight device water skiing state, records correlation test data and experimental phenomena;
6), according to test figure and experimental phenomena, with reference to water surface flying device determination of stability weighing apparatus is accurate, real machine stability is judged.
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| CN201310575932.4A CN103837321B (en) | 2013-11-18 | 2013-11-18 | A kind of water surface flying device real machine stability testing method |
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| CN201310575932.4A CN103837321B (en) | 2013-11-18 | 2013-11-18 | A kind of water surface flying device real machine stability testing method |
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| CN103837321A true CN103837321A (en) | 2014-06-04 |
| CN103837321B CN103837321B (en) | 2016-01-13 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104596730A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Surface aircraft splashing whole-machine power model basin test method |
| CN104596731A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Surface aircraft seakeeping whole-machine power model water basin test method |
| CN105373647A (en) * | 2015-09-30 | 2016-03-02 | 成都飞机工业（集团）有限责任公司 | Method for identifying aerodynamic center through ground sliding test |
| CN106323592A (en) * | 2016-11-07 | 2017-01-11 | 中国特种飞行器研究所 | Pool testing method for storm rolling model of helicopter |
| CN106338378A (en) * | 2015-09-05 | 2017-01-18 | 中国特种飞行器研究所 | Water surface aircraft real machine seakeeping test method |
| CN114001861A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flying gravity center of water surface aircraft |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104596730A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Surface aircraft splashing whole-machine power model basin test method |
| CN104596731A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Surface aircraft seakeeping whole-machine power model water basin test method |
| CN104596731B (en) * | 2014-06-26 | 2017-02-08 | 中国特种飞行器研究所 | Surface aircraft seakeeping whole-machine power model water basin test method |
| CN104596730B (en) * | 2014-06-26 | 2017-02-15 | 中国特种飞行器研究所 | Surface aircraft splashing whole-machine power model basin test method |
| 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 |
| CN106338378A (en) * | 2015-09-05 | 2017-01-18 | 中国特种飞行器研究所 | Water surface aircraft real machine seakeeping test method |
| CN105373647A (en) * | 2015-09-30 | 2016-03-02 | 成都飞机工业（集团）有限责任公司 | Method for identifying aerodynamic center through ground sliding test |
| CN105373647B (en) * | 2015-09-30 | 2018-08-24 | 成都飞机工业（集团）有限责任公司 | A method of passing through the pneumatic focus of ground roll-out test identification |
| CN106323592A (en) * | 2016-11-07 | 2017-01-11 | 中国特种飞行器研究所 | Pool testing method for storm rolling model of helicopter |
| CN114001861A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flying gravity center of water surface aircraft |
| CN114001861B (en) * | 2021-10-25 | 2024-05-24 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flight center of gravity of water surface aircraft |
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| CN103837321B (en) | 2016-01-13 |
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