CN105628326A - Low-risk helicopter rising and landing critical decision point test flight method - Google Patents

Abstract

The invention provides a low-risk helicopter rising and landing critical decision point test flight method, and the method is characterized in that the method comprises the following steps: a), carrying out the confirmation test flight of an AEO rising and landing track in a real rising and landing environment; b), carrying out the test flight of OEI acceleration characteristic simulation in a safe height environment; c), carrying out the superposing of V-hr tracks, and obtaining a CDP test flight result.

Description

A kind of critical decision point Flight Test Method of low-risk helicopter landing

Technical field

This technology belongs to helicopter Flight Test Technique field, relates to the proving flight method of the critical decision point of helicopter landing, and this technology can be applicable in the middle of the proving flight of the critical decision point of military, civilian helicopter landing.

Background technology

CDP proving flight be army/civilian double; two send out, the important performance border checking subject of multiple helicopter, be containing driver's mission task elements at ring, it is necessary to be determined by taking a flight test of true environment or verify. This subject requires to go out helicopter at typical airfield environment by Flight, adopt in the mode/track take-off process of safety, after there is OEI, the position of the critical cut-point CDP on the optional continued takeoff of helicopter pilot or return airport, the description to this position is to use terrain clearance h_rCombination with corresponding speed V. Its core is to verify that helicopter is under different initial energy state, re-establishes the energy transformed space height loss that minimum safe flight is required after there is OEI.

CDP is according to taking off or landing mission can be divided into TDP and LDP. This subject generally under concrete airport environment, the EFP position specified in the landing track determined, use and cut-off or be placed in by an electromotor method helicopter simulating of slow train and taking off or OEI occurs in landing period; Keeping this OEI power rating, it is motor-driven that helicopter is respectively completed continued takeoff/refused landing, until reaching the minimum liftoff safe altitude of 4.5m in the middle of wave off track; Then in same EFP position, simulate OEI, complete to abort/continue the checking action landed, be finally completed the checking to CDP position.

Owing to this subject middle terrain clearance of taking a flight test is low, available horsepower is limited, time and space that pilot disposes are little, adopt said method to carry out CDP to take a flight test and belong to excessive risk subject, at GJB626A-2006 " military fixed wing airplane and gyroplane scientific research take a flight test hazardous project ", this subject is classified as rotor class aircraft and takes a flight test I class hazardous project. In the middle of Flight, once the energy state error in judgement that driver is to current helicopter, or improper maneuver occurs, it is possible to cause serious born or shock consequence.

This section's purpose risk core is " low clearance+underpower ".

The following is the explanation to the abbreviation occurred in the present invention and symbol:

�� CDP: the critical decision point of landing

�� TDP: take off critical decision point

�� LDP: land critical decision point

�� AEO: entirely send out duty

�� OEI: single-shot failure state

�� EFP: power failure point

��V_toss: safe take-off speed

�� V: flight speed

��h_r: terrain clearance

Summary of the invention

The invention provides the critical decision point Flight Test Method of a kind of low-risk helicopter landing, it is characterised in that comprise the following steps:

A) under true landing environment, the confirmation of AEO landing track is taken a flight test

Under fixed region of avoidance boundary constraint, it is thus achieved that the AEO landing track of standard, its flight speed, flying height present fixing corresponding relation. AEO landing when by different airport is taken a flight test, and draws out V-h in landing track_rRelation curve.

B) under safe altitude environment, taking a flight test of OEI accelerating performance it is simulated

Safe altitude sets virtual machine farm height, repeats landing track and draw out V-h in landing track_rRelation curve, at the V-h drawn_rSelecting multiple EFP position on relation curve from high to low, simulation OEI also implements " continued takeoff " or " stopping to land " is motor-driven takes a flight test, it is thus achieved that helicopter eliminates rate of descent and reaches V_tossHeight loss in process.

c)V-h_rTrack superposition obtains CDP and takes a flight test result

The height loss of the OEI accelerator that step b) is obtained adopts the rotor theory of similarity of maturation and dynamic similarity theory to convert, the speed of EFP position in step b) is superimposed in the landing track of step a), safety clearance 4.5m in deduction airworthiness standard or checking requirement, can obtain CDP position.

The present invention is incorporated into hands from two risk group of segmentation, the basic acts of CDP proving flight is decomposed into that above-mentioned a), b) in two steps conventional action content performs respectively, obtain respectively need to data, and processed by data, it is thus achieved that meet the CDP location verification result of demand.

It is two actions of taking a flight test by routine CDP Flight decomposition of movement, has evaded available horsepower deficiency respectively and changed the risk source that limited space the two is main owing to terrain clearance is relatively low.

Flown work by step a) pilot scale, it is possible to obtain different landing environment, including the V-h of typical case's landing track under open smooth airport, helidrome and platform airport environment_rVariation relation curve; Flown work by step b) pilot scale, it is thus achieved that under the energy condition that helicopter climbs in difference, decrease speed is corresponding, use dump power to re-establish the height loss of minimum safe state of flight. On the above results basis, adopt V-h_rThe method of the track superposition flight path that action obtains of taking a flight test to two carries out data process, obtains the particular location of CDP.

The ultimate principle of foundation of the present invention is: helicopter, in the airport environment determined, has the landing mode of the maximum safe clearance of recommendation. Helicopter adopts this landing mode, climbing or in decline process, has metastable V-h_rCorresponding relation. Speed is with highly actual what characterize is the energy that has of helicopter, and different energy accelerates to V corresponding to helicopter after there is OEI_tossAnd eliminate decline, revert to level flight-energy conversion rate in process of climbing, it is embodied in the height loss of helicopter. And this height loss can obtain in higher safe altitude, the danger contacted to earth in low latitude can be prevented effectively from.

The invention have the advantage that the risk of " low clearance+available horsepower not enough " effectively evaded in conventional CDP proving flight, the driving technology of taking a flight test of routine can be adopted to obtain the excessive risk section purpose with certain accuracy and take a flight test result.

Detailed description of the invention

Owing to helicopter landing place is various, it is recommended that landing mode/track be clearly distinguished from, but basic ideas and embodiment are close, for the TDP on helicopter open airport, detailed description of the invention are carried out careful explanation below:

A) confirmation of AEO landing track under true landing environment. Helicopter is on open airport, within the scope of the landing that known region of avoidance is determined, adopts hovering in ground effect-accelerate to take off mode, uses that AEO power rating is repeated multiple times completes take-off process. By flight test data, obtain the representative track V-h that takes off_rRelation curve.

B) the taking a flight test of OEI accelerating performance under safe altitude environment. Helicopter is (unsuitable too high in safe altitude, must ensure that helicopter has hovering and low-speed operations ability) set virtual machine farm height (the selected high 500m in field), hovering and speedup climbing flight is carried out by a) the middle track that takes off set up, after reaching predetermined initial velocity V=40km/h, 65km/h and 80km/h, throttle lever is adopted to adjust to double; two restriction power analog OEI, push rod carries out speedup, and keeps power constant, at the close V analyzing acquisition in advance_tossPull bar before and after speed, sets up stable climbing flight state until eliminating rate of descent or arrives the 2min persistent period, recovering AEO state of flight. Use exterior light examining system to measure the flight path in accelerator, obtain and reach V_tossMaximum height loss.

C) use the conversion method of ripe rotor phase Sihe dynamic similarity principle, the height loss on heliport height 500m is scaled to the high 0m in field. The safe terrain clearance of 4.5m that height loss's value of this conversion and TDP limit is superimposed in a) the track V-h that takes off obtained_rOn curve, the TDP position on helicopter high 0m height on the scene can be obtained.

The recommendation landing track that different take-off venue is corresponding different, needs to reappear this track in a) and b) respectively, and c) method is constant.

Claims (1)

1. the critical decision point Flight Test Method of low-risk helicopter landing, it is characterised in that comprise the following steps:

A) under true landing environment, the confirmation of AEO landing track is taken a flight test

Under fixed region of avoidance boundary constraint, it is thus achieved that the AEO landing track of standard, its flight speed, flying height present fixing corresponding relation, and AEO landing when by different airport is taken a flight test, and draws out V-h in landing track_rRelation curve;

B) under safe altitude environment, taking a flight test of OEI accelerating performance it is simulated

Safe altitude sets virtual machine farm height, repeats landing track and draw out V-h in landing track_rRelation curve, at the V-h drawn_rSelecting multiple EFP position on relation curve from high to low, simulation OEI also implements " continued takeoff " or " stopping to land " is motor-driven takes a flight test, it is thus achieved that helicopter eliminates rate of descent and reaches V_tossHeight loss in process;

c)V-h_rTrack superposition obtains CDP and takes a flight test result

The height loss of the OEI accelerator that step b) is obtained adopts the rotor theory of similarity of maturation and dynamic similarity theory to convert, the speed of EFP position in step b) is superimposed in the landing track of step a), safety clearance 4.5m in deduction airworthiness standard or checking requirement, can obtain CDP position.