CN108045589B - A kind of helicopter VNE alarm method - Google Patents
A kind of helicopter VNE alarm method Download PDFInfo
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
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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 invention relates to the field of helicopter warning system design, in particular to a helicopter VNE warning method.
Background
Conventional helicopter warning systems are more focused on warning whether each system component or equipment has a fault, and the non-overridable speed (VNE) limit is usually placed in a flight manual, and the VNE changes along with changes of atmospheric environment and flight weight, so that the judgment of a pilot on the VNE in the flight process is inconvenient.
Disclosure of Invention
The invention aims to design a helicopter VNE warning method so as to facilitate judgment of a pilot on VNE in the flight process.
The technical scheme of the invention is as follows:
a helicopter VNE warning method comprises the following steps:
step one, judging whether the helicopter in the flight state is in a dynamic state, if so, performing step two; otherwise, carrying out the fifth step;
step two, judging whether the density height in the power state is more than or equal to 2000m or less than 2000 m; if the distance is more than or equal to 2000m, performing a third step; if the distance is less than 2000m, performing the fourth step;
step three, calculating and obtaining the non-surmountable speed V under the power state according to the following formula (1)2：
V2＝k1×V1+b1(1)；
Wherein k is1、b1To correct airspeed conversion formula coefficients; v1Is a corrected airspeed, and is calculated by adopting the following formula (2):
wherein σ is a density ratio, V is a vacuum velocity, and is calculated by the following formula (3):
wherein,vacuum speed at a density height of 2000 m; hd is density height, and the unit is m;
step four, calculating and obtaining the non-surmountable speed V under the power state according to the formula (1)2Wherein the vacuum speed V is calculated according to the following formula (4):
wherein, VWith dynamic thresholdThe critical speed is the critical speed which can not be surpassed; gw is the actual flight weight; gwDatumIs the initial weight input before flight;
judging whether the density height in the unpowered state is more than or equal to 2000m or less than 2000 m; if the distance is larger than or equal to 2000m, performing a sixth step; if the distance is less than 2000m, performing a seventh step;
step six, calculating and obtaining the non-surmountable speed V under the unpowered state according to the following formula (5)5：
V5＝k2×V4+b2(5)；
Wherein k is2、b2To correct airspeed conversion formula coefficients; v4Is a corrected airspeed, calculated using the following equation (6):
wherein, V3The vacuum velocity is calculated by the following formula (7):
wherein,vacuum speed at a density height of 2000 m;
seventhly, calculating and obtaining the non-surmountable speed V under the unpowered state according to the formula (5)5Wherein the vacuum velocity V3Is calculated according to the following formula (8):
wherein, VCritical without powerThe speed is the unpowered critical non-overrunning speed;
step eight, judging the non-overrunning speed obtained by calculation in the step three, the step four, the step six and the step seven, wherein:
when the calculated non-overrunning speed is greater than VNE-10 km/h and less than VNE, the helicopter comprehensive display system sends a first warning signal, wherein VNE is standard non-overrunning speed;
and when the calculated non-overrunning speed is greater than the VNE, the helicopter comprehensive display system sends out a second alarm signal.
Optionally, the step eight further includes:
and when the calculated non-overrunning speed is greater than VNE +3km/h, the comprehensive display system judges and outputs a speed exceeding VNE sound alarm to the language alarm, and the language alarm repeatedly sends out speed exceeding VNE voice to alarm until the speed is reduced to be less than VNE +3 km/h.
Optionally, in the eighth step, the first warning signal is a yellow "VNE" prompt displayed in the flight image and the vertical image; the second warning signal is that red VNE flickers are displayed on the middle surfaces of the flight pictures and the vertical pictures.
Optionally, in the fourth step and the seventh step, the actual flight weight Gw is obtained by using the following formula (9):
GW＝G0-GF0+GF1 (9)；
wherein G0 is the initial weight of the helicopter in kg; GF0 is the initial total oil mass of the oil tank in the engine, unit kg; GF1 is the total oil content in kg of the internal oil tank at a certain moment in the flight.
The invention has the following effects:
according to the warning method of the VNE of the helicopter, the VNE is divided into the dynamic VNE and the unpowered VNE according to whether the engine of the helicopter works normally in the flying process, and meanwhile, the change process of the VNE along with the influence of the atmospheric environment and the flying weight is automatically calculated, so that dynamic VNE tone warning is realized, and the safety judgment of pilots in high-speed flying under different flying states is very convenient.
Drawings
FIG. 1 is a schematic view of a display interface of an alarm integrated display system in the helicopter VNE alarm method of the present invention.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
When the pilot executes emergency situations such as battlefield escape and the like, the pilot needs to fly at a high speed, in order to ensure the flight safety, the VNE in the flight manual is limited by the VNE alarm on the helicopter comprehensive display system, the pilot can visually judge whether the current speed exceeds the VNE, and the pilot can fly at the high speed within the VNE range according to the situation.
The warning method of the VNE of the helicopter mainly realizes the warning of the VNE on the comprehensive display system of the helicopter, is convenient for a pilot to visually judge whether the VNE is exceeded or not in the flight process, and improves the readability and the safety of the pilot in the flight process.
The helicopter VNE alarm method of the present invention is described in further detail below with reference to fig. 1.
The invention provides a helicopter VNE warning method, which comprises the following steps:
step one, judging whether the helicopter in the flight state is in a dynamic state, if so, performing step two; otherwise, carrying out the fifth step;
step two, judging whether the density height in the power state is more than or equal to 2000m or less than 2000 m; if the distance is more than or equal to 2000m, performing a third step; if the distance is less than 2000m, performing the fourth step;
step three, calculating and obtaining the non-surmountable speed V under the power state according to the following formula (1)2：
V2＝k1×V1+b1(1)；
Wherein k is1、b1To correct airspeed conversion formula coefficients; v1Is a corrected airspeed, and is calculated by adopting the following formula (2):
wherein σ is a density ratio, and is calculated by the following formula (3):
v is the vacuum velocity, calculated using the following equation (3):
wherein,vacuum speed at a density height of 2000 m; hd is density height, and the unit is m;
step four, calculating and obtaining the non-surmountable speed V under the power state according to the formula (1)2Wherein the vacuum speed V is calculated according to the following formula (4):
wherein, VWith dynamic thresholdIs a powered critical non-overrunning speed (available on handbooks); gw is the actual flight weight; gwDatumIs the initial weight input before flight;
judging whether the density height in the unpowered state is more than or equal to 2000m or less than 2000 m; if the distance is larger than or equal to 2000m, performing a sixth step; if the distance is less than 2000m, performing a seventh step;
step six, calculating and obtaining the non-surmountable speed V under the unpowered state according to the following formula (5)5：
V5＝k2×V4+b2(5)；
Wherein k is2、b2To correct airspeed conversion formula coefficients; v4Is a corrected airspeed, calculated using the following equation (6):
wherein, V3The vacuum velocity is calculated by the following formula (7):
wherein,vacuum speed at a density height of 2000 m;
seventhly, calculating and obtaining the non-surmountable speed V under the unpowered state according to the formula (5)5Wherein the vacuum velocity V3Is calculated according to the following formula (8):
wherein, VCritical without powerNo power critical non-overrunning speed (available on handbook);
step eight, judging the non-overrunning speed obtained by calculation in the step three, the step four, the step six and the step seven, wherein:
when the calculated non-overrunning speed is greater than VNE-10 km/h and less than VNE, the helicopter comprehensive display system sends a first alarm signal, wherein VNE is standard non-overrunning speed (found by a manual);
and when the calculated non-overrunning speed is greater than the VNE, the helicopter comprehensive display system sends out a second alarm signal.
Further, in the helicopter VNE alarm method of the present invention, the eighth step further includes:
and when the calculated non-overrunning speed is greater than VNE +3km/h, the comprehensive display system judges and outputs a speed exceeding VNE sound alarm to the language alarm, and the language alarm repeatedly sends out speed exceeding VNE voice to alarm until the speed is reduced to be less than VNE +3 km/h.
Further, in the helicopter VNE warning method of the present invention, in step eight, the first warning signal is a yellow "VNE" prompt displayed in the flight screen or the vertical screen; the second warning signal is that red VNE flickers are displayed on the middle surfaces of the flight pictures and the vertical pictures.
Further, in the helicopter VNE warning method of the present invention, in the fourth step and the seventh step, the actual flying weight Gw is obtained by using the following formula (9):
GW＝G0-GF0+GF1 (9)；
wherein G0 is the initial weight of the helicopter in kg; GF0 is the initial total oil mass of the oil tank in the engine, unit kg; GF1 is the total oil content (from the electromechanical management computer) in kg of the internal oil tank at a certain moment during the flight.
The design key points of the helicopter VNE warning method of the invention are as follows:
1) VNE is not fixed, is dynamically changing with changes in atmospheric environment and flight weight, and is different for powered (engine on) and unpowered (engine off) VNEs;
2) the method comprises the following steps of dividing a VNE into a dynamic VNE and an unpowered VNE according to whether an engine of the helicopter works normally in the flying process, writing the VNE into codes along with the influence change process of atmospheric environment and flying weight, and packaging the codes into software to realize an automatic calculation function;
3) the dynamic VNE tone warning is realized, and safety judgment of pilots in high-speed flight in different flight states is facilitated.
In summary, the warning method of the VNE of the helicopter according to the present invention divides the VNE into the powered VNE and the unpowered VNE according to whether the engine of the helicopter is working normally during the flight, and writes the VNE into a code along with the change of atmospheric environment and flight weight, and packages the code into software, so as to implement the automatic calculation function; the dynamic VNE tone warning is realized, and the safety judgment of pilots in high-speed flight in different flight states is very convenient.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (4)
1. A helicopter VNE alarm method is characterized by comprising the following steps:
step one, judging whether the helicopter in the flight state is in a dynamic state, if so, performing step two; otherwise, carrying out the fifth step;
step two, judging whether the density height in the power state is more than or equal to 2000m or less than 2000 m; if the distance is more than or equal to 2000m, performing a third step; if the distance is less than 2000m, performing the fourth step;
step three, calculating the non-overrunning speed under the power state according to the following formula (1)Degree V2：
V2＝k1×V1+b1(1)；
Wherein k is1、b1To correct airspeed conversion formula coefficients; v1Is a corrected airspeed, and is calculated by adopting the following formula (2):
wherein σ is a density ratio, V is a vacuum velocity, and is calculated by the following formula (3):
wherein,vacuum speed at a density height of 2000 m; hd is density height, and the unit is m;
step four, calculating and obtaining the non-surmountable speed V under the power state according to the formula (1)2Wherein the vacuum speed V is calculated according to the following formula (4):
wherein, VWith dynamic thresholdThe critical speed is the critical speed which can not be surpassed; gw is the actual flight weight; gwDatumIs the initial weight input before flight;
judging whether the density height in the unpowered state is more than or equal to 2000m or less than 2000 m; if the distance is larger than or equal to 2000m, performing a sixth step; if the distance is less than 2000m, performing a seventh step;
step six, calculating and obtaining the non-surmountable speed V under the unpowered state according to the following formula (5)5：
V5＝k2×V4+b2(5)；
Wherein k is2、b2To correct airspeed conversion formula coefficients; v4Is a corrected airspeed, calculated using the following equation (6):
wherein, V3The vacuum velocity is calculated by the following formula (7):
wherein,vacuum speed at a density height of 2000 m;
seventhly, calculating and obtaining the non-surmountable speed V under the unpowered state according to the formula (5)5Wherein the vacuum velocity V3Is calculated according to the following formula (8):
wherein, VCritical without powerThe speed is the unpowered critical non-overrunning speed;
step eight, judging the non-overrunning speed obtained by calculation in the step three, the step four, the step six and the step seven, wherein:
when the calculated non-overrunning speed is greater than VNE-10 km/h and less than VNE, the helicopter comprehensive display system sends a first warning signal, wherein VNE is standard non-overrunning speed;
and when the calculated non-overrunning speed is greater than the VNE, the helicopter comprehensive display system sends out a second alarm signal.
2. A helicopter VNE alarm method according to claim 1, characterized in that said eighth step further comprises:
and when the calculated non-overrunning speed is greater than VNE +3km/h, the comprehensive display system judges and outputs a speed exceeding VNE sound alarm to the language alarm, and the language alarm repeatedly sends out speed exceeding VNE voice to alarm until the speed is reduced to be less than VNE +3 km/h.
3. A helicopter VNE alarm method according to claim 1, characterized in that in said step eight, the first alarm signal is a yellow "VNE" prompt displayed in the flight screen, vertical screen; the second warning signal is that red VNE flickers are displayed on the middle surfaces of the flight pictures and the vertical pictures.
4. A helicopter VNE warning method according to claim 1, characterized in that in said fourth and seventh steps, the actual flying weight Gw is obtained using the following formula (9):
GW＝G0-GF0+GF1 (9)；
wherein G0 is the initial weight of the helicopter in kg; GF0 is the initial total oil mass of the oil tank in the engine, unit kg; GF1 is the total oil content in kg of the internal oil tank at a certain moment in the flight.
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| CN111504341B (en) * | 2020-04-30 | 2023-09-19 | 中国直升机设计研究所 | Helicopter flight state identification method |
| EP4190698B1 (en) | 2021-12-03 | 2025-01-15 | 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 |
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| 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 |
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