CN109625315B - Helicopter takeoff critical decision point trial flight method based on maximum performance - Google Patents

Helicopter takeoff critical decision point trial flight method based on maximum performance Download PDF

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CN109625315B
CN109625315B CN201811263987.0A CN201811263987A CN109625315B CN 109625315 B CN109625315 B CN 109625315B CN 201811263987 A CN201811263987 A CN 201811263987A CN 109625315 B CN109625315 B CN 109625315B
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helicopter
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climbing
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CN109625315A (en
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张华�
吕增岁
沈雳
李亮明
赵敬超
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Chinese Flight Test Establishment
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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Abstract

The invention relates to a helicopter takeoff critical decision point trial flight method based on maximum performance, which belongs to the technical field of flight tests and is characterized in that according to the characteristic of helicopter takeoff critical decision point trial flight, firstly, trial flight is carried out on the helicopter flat flight performance and climbing performance to obtain a normalized flat flight performance curve family and a normalized climbing rate correction relation, then, according to the requirement of the climbing performance of a type A helicopters in CCAR-29-R1, the maximum takeoff weight of the helicopter is determined according to the normalized flat flight performance curve family and the climbing rate correction relation, and finally, the trial flight of the helicopter takeoff critical decision point is completed according to a preset program by the weight, so that the problems of high trial flight time and high economic cost of the helicopter takeoff critical decision point are solved, and trial flight times and cost are reduced.

Description

Helicopter takeoff critical decision point trial flight method based on maximum performance
Technical Field
The invention discloses a helicopter takeoff critical decision point trial flight method based on maximum performance, and belongs to the technical field of flight tests.
Background
For the A-type helicopters with two or more than two engines, in the process of taking off in the All-engine operating state (AEO for short), once single-engine-in-operation (OEI for short) occurs, continuous taking off or taking off is selected to be interrupted. Therefore, a Takeoff critical decision point (TDP) defined by two parameters, namely height and speed, needs to be defined on the Takeoff trajectory of the class a helicopter, and the Takeoff critical decision point is used as a dividing point for determining whether to land immediately after a single failure occurs in the Takeoff process.
The takeoff critical decision point of the Helicopter is comprehensively influenced by the flight weight, the atmospheric temperature and the atmospheric pressure of the Helicopter, the takeoff critical decision point needs to be determined through a flight Test, a related flight Test method is described in detail in Helicopter Test and Evaluation published by AIAA (Helicopter Test and Evaluation, Alastair K.Cooke and Eric W.H.Fitzparrick, AIAA, US, 2002), and a Test flight method in Helicopter Test and Evaluation needs to determine the influence of the flight weight, the atmospheric temperature and the atmospheric pressure on the takeoff decision point of the Helicopter through a plurality of Test flights, so that the time and economic cost are high, and the risk is high.
Disclosure of Invention
The purpose of the invention is as follows: the helicopter takeoff critical decision point trial flight method based on the maximum performance is provided to perform helicopter takeoff critical decision point trial flight.
The technical scheme of the invention is as follows:
a helicopter takeoff critical decision point trial flight method based on maximum performance comprises the following steps:
step 1, performing level flight performance test flight on the helicopter, determining the level flight performance of the helicopter, and performing normalization processing on the power P, the weight W and the speed V of the helicopter according to formulas (1) to (3) to obtain a normalized level flight performance curve family;
Figure BDA0001842829620000011
Figure BDA0001842829620000012
Figure BDA0001842829620000013
wherein: pN，WN，VNNormalized power, normalized weight, and normalized speed, respectively; sigma is the ratio of the atmospheric density, i.e. the actual atmospheric density to 1.225kg/m3The ratio of (A) to (B); omega is the ratio of the actual rotor rotation speed to the standard rotor rotation speed;
step 2, climbing performance test flight is carried out on the helicopter, the helicopter is respectively subjected to climbing performance test flight according to different preset climbing rates, and the actual climbing rate V is obtainedVAccording to the formulas (4) and (5) to the actual climbing rate VVTheory of the formation ofNormalizing the climbing rate V' to obtain a normalized climbing rate correction relation of the helicopter;
Figure BDA0001842829620000021
Figure BDA0001842829620000022
the theoretical climbing rate V 'is obtained by interpolating data in the normalized flat flight performance curve family determined in the step 1 and calculating the theoretical climbing rate V' under the condition that the flight weight, power, atmospheric density and flight speed are the same as those of the helicopter in climbing performance test flight;
hover induced velocity VihIs the hover induction speed V under the condition of the same flight weight and atmospheric density when the helicopter performs climbing performance test flightih，
Calculating to obtain normalized actual climbing rate VVNAnd theoretical climbing rate V'N；
Step 3, determining atmospheric temperature and pressure conditions of the helicopter during actual test flight, and determining the maximum takeoff weight of the helicopter according to the requirements of CCAR-29-R1 transportation type rotor aircraft airworthiness regulation 29.67A helicopters on climbing performance and the corrected relation of the normalized level flight performance curve family and the normalized climbing rate of the helicopter obtained in the steps 1 and 2;
and 4, step 4: and (3) according to a preset takeoff program of the helicopter, respectively carrying out takeoff critical decision points on the helicopter to continue takeoff and stop takeoff trial flight according to the maximum takeoff weight of the helicopter determined in the step (3), and finally determining the takeoff critical decision points.
When the helicopter flat flight performance test flight is carried out in the step 1, the normalized quality W corresponding to each curve on the normalized flat flight performance curve family is maintained by adopting the variable air pressure height helicopter flat flight performance test flight methodNAnd is not changed.
When the trial flight of the climbing performance of the helicopter is carried out in the step 2, the climbing rate of 0.5m/s is taken as the initial state of the climbing performance of the helicopter, and the trial flight of the climbing performance is carried out by setting the climbing rate interval of 0.5 m/s.
And 3, when the maximum takeoff weight of the helicopter is determined in the step 3, taking the weight corresponding to the climbing rate of 0.5m/s of the helicopter as the maximum takeoff weight of the helicopter.
The invention has the advantages that:
according to the normalized flat flight performance curve family and the normalized climbing rate correction relation obtained by trial flight of the helicopter in the flat flight performance and the climbing performance, the maximum takeoff weight of the helicopter is determined to carry out trial flight at the takeoff critical decision point, the trial flight number requirement is low, the time and the economic cost are low, and the risk is low.
Drawings
FIG. 1 is a schematic diagram of a normalized flat-flight performance curve.
FIG. 2 is a graphical illustration of a normalized climb rate correction relationship.
Fig. 3 is a schematic diagram of a takeoff critical decision point continuous takeoff test approach procedure.
FIG. 4 is a schematic diagram of a takeoff threshold decision point takeoff trial approach routine.
Fig. 5 is a diagram of flight procedures specified for continuation and suspension of takeoff at the takeoff critical decision point.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
A helicopter takeoff critical decision point trial flight method based on maximum performance comprises the following steps:
step 1, performing level flight performance test flight on the helicopter, determining the level flight performance of the helicopter, and performing normalization processing on the power P, the weight W and the speed V of the helicopter according to formulas (1) to (3) to obtain a normalized level flight performance curve family, as shown in FIG. 1;
Figure BDA0001842829620000031
Figure BDA0001842829620000032
Figure BDA0001842829620000033
wherein: pN，WN，VNNormalized power, normalized weight, and normalized speed, respectively; sigma is the ratio of the atmospheric density, i.e. the actual atmospheric density to 1.225kg/m3The ratio of (A) to (B); omega is the ratio of the actual rotor rotation speed to the standard rotor rotation speed;
step 2, climbing performance test flight is carried out on the helicopter, the helicopter is respectively subjected to climbing performance test flight according to different preset climbing rates, and the actual climbing rate V is obtainedVAccording to the formulas (4) and (5) to the actual climbing rate VVNormalizing the theoretical climbing rate V' to obtain a normalized climbing rate correction relation of the helicopter;
Figure BDA0001842829620000034
Figure BDA0001842829620000035
the theoretical climbing rate V 'is obtained by interpolating data in the normalized flat flight performance curve family determined in the step 1 and calculating the theoretical climbing rate V' under the condition that the flight weight, power, atmospheric density and flight speed are the same as those of the helicopter in climbing performance test flight;
hover induced velocity VihIs the hover induction speed V under the condition of the same flight weight and atmospheric density when the helicopter performs climbing performance test flightih，
Calculating to obtain normalized actual climbing rate VVNAnd theoretical climbing rate V'N；
Step 3, determining atmospheric temperature and pressure conditions of the helicopter during actual test flight, and determining the maximum takeoff weight of the helicopter according to the requirements of CCAR-29-R1 transportation type rotor aircraft airworthiness regulation 29.67A helicopters on climbing performance and the corrected relation of the normalized level flight performance curve family and the normalized climbing rate of the helicopter obtained in the steps 1 and 2;
and 4, step 4: and (3) according to a preset takeoff program of the helicopter, respectively carrying out takeoff critical decision points on the helicopter to continue takeoff and stop takeoff trial flight according to the maximum takeoff weight of the helicopter determined in the step (3), and finally determining the takeoff critical decision points.
Referring to the approaching programs shown in fig. 3 and 4, a takeoff critical decision point continuous takeoff test and a takeoff stopping test flight are respectively carried out according to the program specified in fig. 5, and the takeoff continuing and takeoff stopping capabilities of the helicopter after single failure on a takeoff track corresponding to a preset takeoff program are determined. The state point of the helicopter which has the capability of continuing taking off and stopping taking off after single failure on the taking-off track is the taking-off critical decision point, and the flight speed and the ground clearance corresponding to the state point can be used for determining the taking-off critical decision point under the taking-off track.
When the helicopter flat flight performance test flight is carried out in the step 1, the normalized quality W corresponding to each curve on the normalized flat flight performance curve family is maintained by adopting the variable air pressure height helicopter flat flight performance test flight methodNAnd is not changed.
When the trial flight of the climbing performance of the helicopter is carried out in the step 2, the climbing rate of 0.5m/s is taken as the initial state of the climbing performance of the helicopter, and the trial flight of the climbing performance is carried out by setting the climbing rate interval of 0.5 m/s.
And 3, when the maximum takeoff weight of the helicopter is determined in the step 3, taking the weight corresponding to the climbing rate of 0.5m/s of the helicopter as the maximum takeoff weight of the helicopter.

Claims (4)

1. A helicopter takeoff critical decision point trial flight method based on maximum performance is characterized by comprising the following steps:
step 1, performing level flight performance test flight on the helicopter, determining the level flight performance of the helicopter, and performing normalization processing on the power P, the weight W and the speed V of the helicopter according to formulas (1) to (3) to obtain a normalized level flight performance curve family;
Figure FDA0003466433960000011
Figure FDA0003466433960000012
Figure FDA0003466433960000013
wherein: pN，WN，VNNormalized power, normalized weight, and normalized speed, respectively; sigma is the ratio of the atmospheric density, i.e. the actual atmospheric density to 1.225kg/m3The ratio of (A) to (B); omega is the ratio of the actual rotor rotation speed to the standard rotor rotation speed;
step 2, climbing performance test flight is carried out on the helicopter, the helicopter is respectively subjected to climbing performance test flight according to different preset climbing rates, and the actual climbing rate V is obtainedVAccording to the formulas (4) and (5) to the actual climbing rate VVNormalizing the theoretical climbing rate V' to obtain a normalized climbing rate correction relation of the helicopter;
Figure FDA0003466433960000014
Figure FDA0003466433960000015
the theoretical climbing rate V 'is obtained by interpolating data in the normalized flat flight performance curve family determined in the step 1 and calculating the theoretical climbing rate V' under the condition that the flight weight, power, atmospheric density and flight speed are the same as those of the helicopter in climbing performance test flight;
hover induced velocity VihIs to test the climbing performance with the helicopterHovering induction speed V under the condition of same flying weight and atmospheric densityih，
Calculating to obtain normalized actual climbing rate VVNAnd theoretical climbing rate V'N；
Step 3, determining atmospheric temperature and pressure conditions of the helicopter during actual test flight, and determining the maximum takeoff weight of the helicopter according to the requirements of CCAR-29-R1 transportation type rotor aircraft airworthiness regulation 29.67A helicopters on climbing performance and the corrected relation of the normalized level flight performance curve family and the normalized climbing rate of the helicopter obtained in the steps 1 and 2;
and 4, step 4: and (3) according to a preset takeoff program of the helicopter, respectively carrying out takeoff critical decision points on the helicopter to continue takeoff and stop takeoff trial flight according to the maximum takeoff weight of the helicopter determined in the step (3), and finally determining the takeoff critical decision points.
2. A helicopter take-off critical decision point trial flight method based on maximum performance as defined in claim 1, wherein when the helicopter flat flight performance trial flight is performed in step 1, the helicopter flat flight performance trial flight method with variable barometric pressure altitude is adopted to maintain the normalized quality W corresponding to each curve in the normalized flat flight performance curve familyNAnd is not changed.
3. A helicopter take-off critical decision point trial flight method based on maximum performance as defined in claim 1, wherein when the helicopter climb performance trial flight is performed in step 2, the climb rate of 0.5m/s is used as the initial state of the helicopter climb performance, and the climb rate interval of 0.5m/s is set for the helicopter climb performance trial flight.
4. A helicopter take-off critical decision point trial flight method based on maximum performance as defined in claim 1, wherein when the maximum take-off weight of the helicopter is determined in step 3, the weight corresponding to the climb rate of the helicopter of 0.5m/s is taken as the maximum take-off weight of the helicopter.
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