CN108045589B - A kind of helicopter VNE alarm method - Google Patents
A kind of helicopter VNE alarm method Download PDFInfo
- Publication number
- CN108045589B CN108045589B CN201711247044.4A CN201711247044A CN108045589B CN 108045589 B CN108045589 B CN 108045589B CN 201711247044 A CN201711247044 A CN 201711247044A CN 108045589 B CN108045589 B CN 108045589B
- Authority
- CN
- China
- Prior art keywords
- vne
- calculated
- speed
- helicopter
- overtaking
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
- B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
Abstract
The present invention relates to helicopter warning system design field, in particular to a kind of helicopter VNE alarm method includes the following steps: to judge whether in dynamic state；Judge the density altitude under dynamic state；The No overtaking speed under dynamic state is calculated；The No overtaking speed under dynamic state is calculated；Judge the density altitude under non-power state；The No overtaking speed under non-power state is calculated；The No overtaking speed under non-power state is calculated；The No overtaking speed being calculated is judged, to issue the first alarm signal or issue the second alarm signal.Helicopter VNE alarm method of the invention, according to helicopter, whether engine is worked normally in flight course, VNE is divided for dynamic VNE and unpowered VNE, the VNE that calculates automatic simultaneously is as the influence of atmospheric environment and flying weight changes, it realizes the alarm of dynamic VNE tone color, pilot under different flight state is facilitated to carry out safety judgement when big speed flight.
Description
Technical field
The present invention relates to helicopter warning system design field, in particular to a kind of helicopter VNE alarm method.
Background technique
The common alarm that helicopter warning system more biases toward each system unit or whether equipment breaks down, and can not
Surmounting speed (VNE) limitation would generally be placed in flight airmanship, and VNE be variation with atmospheric environment and flying weight and
Variation, pilot is not easy in flight course to the judgement of VNE.
Summary of the invention
The purpose of the present invention designs a kind of helicopter VNE alarm method, in order to pilot in flight course to VNE into
Row judgement.
The technical scheme is that
A kind of helicopter VNE alarm method, includes the following steps:
Step 1: judging whether the helicopter in state of flight is in dynamic state, it is, carries out step 2；Otherwise,
Carry out step 5；
Step 2: the density altitude for judging under dynamic state is greater than and is also less than 2000m equal to 2000m；It is greater than
Step 3 is then carried out equal to 2000m；Step 4 is then carried out less than 2000m；
Step 3: the No overtaking speed V under dynamic state is calculated in (1) according to the following formula2:
V2=k1×V1+b1(1)；
Wherein, k1、b1For calibrated airspeed reduction formula coefficient；V1It is calibrated airspeed, is calculated using following formula (2):
Wherein, σ is density ratio, and V is true air speed, is calculated using following formula (3):
Wherein,True air speed when for 2000m density altitude；Hd is density altitude, unit m；
Step 4: the No overtaking speed V under dynamic state is calculated according to above-mentioned formula (1)2, wherein vacuum
Fast V is that (4) are calculated according to the following formula:
Wherein, VIt is dynamic criticalFor dynamic critical No overtaking speed；Gw is practical flight weight；GwBenchmarkFor preceding input of flying
Initial weight；
Step 5: the density altitude for judging under non-power state is greater than and is also less than 2000m equal to 2000m；It is greater than
Step 6 is then carried out equal to 2000m；Step 7 is then carried out less than 2000m；
Step 6: the No overtaking speed V under non-power state is calculated in (5) according to the following formula5:
V5=k2×V4+b2(5)；
Wherein, k2、b2For calibrated airspeed reduction formula coefficient；V4It is calibrated airspeed, is calculated using following formula (6):
Wherein, V3It is true air speed, is calculated using following formula (7):
Wherein,True air speed when for 2000m density altitude；
Step 7: the No overtaking speed V under non-power state is calculated according to above-mentioned formula (5)5, wherein vacuum
Fast V3It is that (8) are calculated according to the following formula:
Wherein, VIt is unpowered criticalFor unpowered critical No overtaking speed；
Step 8: to it is described Step 3: Step 4: the No overtaking speed being calculated in step 6 and step 7 into
Row judgement, in which:
When the No overtaking speed being calculated is greater than VNE-10km/h and is less than VNE, helicopter integrated display system
Issue the first alarm signal, wherein VNE is standard No overtaking speed；
When the No overtaking speed being calculated is greater than VNE, helicopter integrated display system issues the second alarm signal.
Optionally, the step 8 further include:
When the No overtaking speed being calculated is greater than VNE+3km/h, simultaneously output speed is super for integrated display system judgement
VNE audible warning sound gives language alarm device, issues " the super VNE of speed " voice repeatedly by language alarm device and is alerted, until speed
Decrease below VNE+3km/h or less.
Optionally, in the step 8, the first alarm signal is to show yellow in flight picture, vertical picture
" VNE " prompt；Second alarm signal is that face is displayed in red " VNE " flashing in flight picture, vertical picture.
Optionally, in the step 4 and step 7, practical flight weight Gw is obtained using following formula (9):
GW=G0-GF0+GF1 (9)；
Wherein, G0 is helicopter initial weight, units/kg；GF0 is initial total oil mass of fuel tank in machine, units/kg；GF1 is
In flight course in a certain moment machine fuel tank total oil mass, units/kg.
Invention effect:
Helicopter VNE alarm method of the invention, according to helicopter, whether engine is worked normally in flight course, will
VNE points are dynamic VNE and unpowered VNE, while the automatic VNE that calculates was as the influence of atmospheric environment and flying weight changed
Journey realizes the alarm of dynamic VNE tone color, and safety is sentenced when pilot carries out big speed flight under very convenient different flight state
It is disconnected.
Detailed description of the invention
Fig. 1 is alarm integration display system display interface schematic diagram in invention helicopter VNE alarm method.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
Pilot need to use big speed to fly when executing the cases of emergency such as battlefield escape, to guarantee flight safety, flight
VNE limitation in handbook is alerted by the VNE in helicopter integrated display system to be realized, pilot can intuitively judge currently
Whether speed can regard feelings within the scope of VNE and carry out big speed flight more than VNE.
Helicopter VNE alarm method of the invention, mainly the VNE alarm in realization helicopter integrated display system, side
Just pilot in flight course can with intuitive judgment whether more than VNE, promoted pilot in the easy interpretation of flight course and
Safety.
1 pair of helicopter VNE alarm method of the present invention is described in further details with reference to the accompanying drawing.
The present invention provides a kind of helicopter VNE alarm methods, include the following steps:
Step 1: judging whether the helicopter in state of flight is in dynamic state, it is, carries out step 2；Otherwise,
Carry out step 5；
Step 2: the density altitude for judging under dynamic state is greater than and is also less than 2000m equal to 2000m；It is greater than
Step 3 is then carried out equal to 2000m；Step 4 is then carried out less than 2000m；
Step 3: the No overtaking speed V under dynamic state is calculated in (1) according to the following formula2:
V2=k1×V1+b1(1)；
Wherein, k1、b1For calibrated airspeed reduction formula coefficient；V1It is calibrated airspeed, is calculated using following formula (2):
Wherein, σ is density ratio, is calculated using following formula (3):
V is true air speed, is calculated using following formula (3):
Wherein,True air speed when for 2000m density altitude；Hd is density altitude, unit m；
Step 4: the No overtaking speed V under dynamic state is calculated according to above-mentioned formula (1)2, wherein vacuum
Fast V is that (4) are calculated according to the following formula:
Wherein, VIt is dynamic criticalFor dynamic critical No overtaking speed (being obtained on handbook)；Gw is practical flight weight；GwBenchmark
For the preceding initial weight inputted that flies；
Step 5: the density altitude for judging under non-power state is greater than and is also less than 2000m equal to 2000m；It is greater than
Step 6 is then carried out equal to 2000m；Step 7 is then carried out less than 2000m；
Step 6: the No overtaking speed V under non-power state is calculated in (5) according to the following formula5:
V5=k2×V4+b2(5)；
Wherein, k2、b2For calibrated airspeed reduction formula coefficient；V4It is calibrated airspeed, is calculated using following formula (6):
Wherein, V3It is true air speed, is calculated using following formula (7):
Wherein,True air speed when for 2000m density altitude；
Step 7: the No overtaking speed V under non-power state is calculated according to above-mentioned formula (5)5, wherein vacuum
Fast V3It is that (8) are calculated according to the following formula:
Wherein, VIt is unpowered criticalFor unpowered critical No overtaking speed (being obtained on handbook)；
Step 8: to it is described Step 3: Step 4: the No overtaking speed being calculated in step 6 and step 7 into
Row judgement, in which:
When the No overtaking speed being calculated is greater than VNE-10km/h and is less than VNE, helicopter integrated display system
Issue the first alarm signal, wherein VNE is standard No overtaking speed (handbook is found)；
When the No overtaking speed being calculated is greater than VNE, helicopter integrated display system issues the second alarm signal.
Further, in helicopter VNE alarm method of the invention, step 8 further include:
When the No overtaking speed being calculated is greater than VNE+3km/h, simultaneously output speed is super for integrated display system judgement
VNE audible warning sound gives language alarm device, issues " the super VNE of speed " voice repeatedly by language alarm device and is alerted, until speed
Decrease below VNE+3km/h or less.
Further, in helicopter VNE alarm method of the invention, in step 8, the first alarm signal is in flight picture
Show that yellow " VNE " is prompted in face, vertical picture；Second alarm signal is that face is displayed in red in flight picture, vertical picture
" VNE " flashing.
Further, in helicopter VNE alarm method of the invention, in step 4 and step 7, practical flight weight Gw is adopted
It is obtained with following formula (9):
GW=G0-GF0+GF1 (9)；
Wherein, G0 is helicopter initial weight, units/kg；GF0 is initial total oil mass of fuel tank in machine, units/kg；GF1 is
In flight course in a certain moment machine fuel tank total oil mass (being derived from Electromechanical Management computer), units/kg.
Helicopter VNE alarm method designing points of the invention are:
1), VNE is not fixed value, and is had as the variation of atmospheric environment and flying weight is dynamic change
Power (engine operation) and unpowered (power failure) VNE are different；
2), according to helicopter, whether engine is worked normally in flight course, and VNE is divided for dynamic VNE and without dynamic
Power VNE, while by VNE as the influence change procedure of atmospheric environment and flying weight is write as code wrap into software, it realizes
Automatic computing function；
3) alarm of dynamic VNE tone color, is realized, when pilot carries out big speed flight under very convenient different flight state
Safety judgement.
In conclusion helicopter VNE alarm method of the invention, according to helicopter, just whether engine in flight course
VNE divide for dynamic VNE and unpowered VNE by often work, while by VNE with the influence change of atmospheric environment and flying weight
Change process is write as code wrap into software, realizes automatic computing function；Realize dynamic VNE tone color alarm, it is very convenient not
Safety judges when carrying out big speed flight with pilot under state of flight.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (4)
1. a kind of helicopter VNE alarm method, which comprises the steps of:
Step 1: judging whether the helicopter in state of flight is in dynamic state, it is, carries out step 2；Otherwise, it carries out
Step 5；
Step 2: the density altitude for judging under dynamic state is greater than and is also less than 2000m equal to 2000m；It is more than or equal to
2000m then carries out step 3；Step 4 is then carried out less than 2000m；
Step 3: the No overtaking speed V under dynamic state is calculated in (1) according to the following formula2:
V2=k1×V1+b1(1)；
Wherein, k1、b1For calibrated airspeed reduction formula coefficient；V1It is calibrated airspeed, is calculated using following formula (2):
Wherein, σ is density ratio, and V is true air speed, is calculated using following formula (3):
Wherein,True air speed when for 2000m density altitude；Hd is density altitude, unit m；
Step 4: the No overtaking speed V under dynamic state is calculated according to above-mentioned formula (1)2, wherein true air speed V is
(4) are calculated according to the following formula:
Wherein, VIt is dynamic criticalFor dynamic critical No overtaking speed；Gw is practical flight weight；GwBenchmarkFor the first of preceding input that fly
Starting weight amount；
Step 5: the density altitude for judging under non-power state is greater than and is also less than 2000m equal to 2000m；It is more than or equal to
2000m then carries out step 6；Step 7 is then carried out less than 2000m；
Step 6: the No overtaking speed V under non-power state is calculated in (5) according to the following formula5:
V5=k2×V4+b2(5)；
Wherein, k2、b2For calibrated airspeed reduction formula coefficient；V4It is calibrated airspeed, is calculated using following formula (6):
Wherein, V3It is true air speed, is calculated using following formula (7):
Wherein,True air speed when for 2000m density altitude；
Step 7: the No overtaking speed V under non-power state is calculated according to above-mentioned formula (5)5, wherein true air speed V3It is
(8) are calculated according to the following formula:
Wherein, VIt is unpowered criticalFor unpowered critical No overtaking speed；
Step 8: to described Step 3: Step 4: the No overtaking speed being calculated in step 6 and step 7 is sentenced
It is disconnected, in which:
When the No overtaking speed being calculated is greater than VNE-10km/h and is less than VNE, helicopter integrated display system is issued
First alarm signal, wherein VNE is standard No overtaking speed；
When the No overtaking speed being calculated is greater than VNE, helicopter integrated display system issues the second alarm signal.
2. helicopter VNE alarm method according to claim 1, which is characterized in that the step 8 further include:
When the No overtaking speed being calculated is greater than VNE+3km/h, integrated display system judgement and the super VNE sound of output speed
Sound is alerted to language alarm device, issues " the super VNE of speed " voice repeatedly by language alarm device and is alerted, until speed is reduced to
Less than VNE+3km/h or less.
3. helicopter VNE alarm method according to claim 1, which is characterized in that in the step 8, the first alarm
Signal is to show that yellow " VNE " is prompted in flight picture, vertical picture；Second alarm signal is in flight picture, vertical picture
Face is displayed in red " VNE " flashing in face.
4. helicopter VNE alarm method according to claim 1, which is characterized in that real in the step 4 and step 7
Border flying weight Gw is obtained using following formula (9):
GW=G0-GF0+GF1 (9)；
Wherein, G0 is helicopter initial weight, units/kg；GF0 is initial total oil mass of fuel tank in machine, units/kg；GF1 is flight
In the process in a certain moment machine fuel tank total oil mass, units/kg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711247044.4A CN108045589B (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter VNE alarm method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711247044.4A CN108045589B (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter VNE alarm method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108045589A CN108045589A (en) | 2018-05-18 |
| CN108045589B true CN108045589B (en) | 2018-12-11 |
Family
ID=62121102
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711247044.4A Active CN108045589B (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter VNE alarm method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045589B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111504341B (en) * | 2020-04-30 | 2023-09-19 | 中国直升机设计研究所 | Helicopter flight state identification method |
| EP4190698A1 (en) | 2021-12-03 | 2023-06-07 | Leonardo S.p.a. | Control unit and indicator for an aircraft capable of hovering or for a flight simulation system of said aircraft, and relative method for assisting the performance of a maneuvre |
| EP4190700B1 (en) | 2021-12-03 | 2024-03-27 | Leonardo S.p.a. | Control unit for an aircraft capable of hovering or for a flight simulation system of said aircraft, and relative method for assisting the performance of a manoeuvre |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4818992A (en) * | 1983-06-10 | 1989-04-04 | Sundstrand Data Control, Inc. | Excessive altitude loss after take-off warning system for rotary wing aircraft |
| US8653990B2 (en) * | 2012-06-18 | 2014-02-18 | The Boeing Company | Stall management system |
| CN103823085A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Comprehensive audio processing tester |
| CN104973260A (en) * | 2014-04-10 | 2015-10-14 | 哈尔滨飞机工业集团有限责任公司 | Helicopter overspeed alarm system |
-
2017
- 2017-12-01 CN CN201711247044.4A patent/CN108045589B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108045589A (en) | 2018-05-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108045589B (en) | A kind of helicopter VNE alarm method | |
| US9165414B2 (en) | Method and system for predicting performance of an aircraft | |
| CN105527709A (en) | Systems and methods for adjusting features within a head-up display | |
| US9409654B2 (en) | System and method for improved low airspeed warning | |
| JP5292314B2 (en) | Flight management system that generates variable thrust cutback at aircraft departure | |
| US20130274965A1 (en) | Automated take off control system and method | |
| US10093431B2 (en) | Aircraft instrumentation systems for displaying electronic circuit breaker information | |
| US10457417B2 (en) | Flight instrument warning display | |
| EP2200020A2 (en) | Method and system for operating a vehicular electronic system with voice command capability | |
| CN103318416A (en) | Situational awareness pilot briefing tool | |
| CN103413464B (en) | A kind of landform perception and warning system and wherein alarm calculate and export the method controlled | |
| CN107284679A (en) | System and method for providing from the automatic flight performance feedback of aircraft to pilot | |
| CN106403995A (en) | Device used for RNP airborne performance monitoring and warning | |
| US20100188276A1 (en) | System and method for processing signals from multiple input devices | |
| CN106020228B (en) | System and method for calculating fuel consumption difference corresponding to aircraft track correction | |
| CN106846715A (en) | Aerocraft system and method with wearable device alarm | |
| JP2004513025A (en) | Low-performance take-off detection for aircraft using a ground approach warning system | |
| US8224506B2 (en) | Method and device for determining a maximum stabilization height in the final flight phase of an airplane | |
| US20080173753A1 (en) | Methods and systems for monitoring approach of rotary wing aircraft | |
| WO2020046983A1 (en) | Non-binary collaborative recovery system | |
| CN109733626A (en) | A kind of alarm of amphibious aircraft hatch door and instruction system | |
| US8498755B2 (en) | Device and method for the coherent management of data deriving from surveillance systems of an aircraft | |
| CN108100298A (en) | A kind of test method for aircraft terrain awareness warning system | |
| US20190161202A1 (en) | Method and system for selecting and displaying an operating protocol for an aerial vehicle | |
| US10017253B1 (en) | Aircraft cabin pressure assessment systems and methods |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |