CN110920905B - Flight matching method of piston engine and unmanned helicopter - Google Patents

Flight matching method of piston engine and unmanned helicopter Download PDF

Info

Publication number
CN110920905B
CN110920905B CN201911292076.5A CN201911292076A CN110920905B CN 110920905 B CN110920905 B CN 110920905B CN 201911292076 A CN201911292076 A CN 201911292076A CN 110920905 B CN110920905 B CN 110920905B
Authority
CN
China
Prior art keywords
flight
total distance
relation
unmanned helicopter
curve
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
Application number
CN201911292076.5A
Other languages
Chinese (zh)
Other versions
CN110920905A (en
Inventor
夏宗权
张雅铭
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Continental Union Chaolun Technology Beijing Co ltd
Original Assignee
Continental Union Chaolun Technology Beijing Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Continental Union Chaolun Technology Beijing Co ltd filed Critical Continental Union Chaolun Technology Beijing Co ltd
Priority to CN201911292076.5A priority Critical patent/CN110920905B/en
Publication of CN110920905A publication Critical patent/CN110920905A/en
Application granted granted Critical
Publication of CN110920905B publication Critical patent/CN110920905B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/04—Aircraft characterised by the type or position of power plants of piston type
    • 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
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

The invention discloses a flight matching method of a piston engine and an unmanned helicopter, wherein the flight matching method is used for controllingThe method comprises the following operation steps of judging the flight state of the current unmanned helicopter; if the current unmanned helicopter is in a hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure DDA0002319445420000011
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure DDA0002319445420000012
The corresponding relationship of (a); if the current unmanned helicopter is in a forward flight state, different forward flight speeds V are passed0Required power N ofXUTotal distance from
Figure DDA0002319445420000013
Relation, finally obtaining the time throttle OIL and the total distance under the front flying state
Figure DDA0002319445420000014
The corresponding relationship of (1). The flight control method not only ensures the balance of force, but also ensures the balance of power, thereby avoiding the flight accident of the piston type unmanned helicopter caused by improper coordination with the engine.

Description

Flight matching method of piston engine and unmanned helicopter
Technical Field
The invention relates to the field of unmanned helicopters, in particular to a flight matching method of a piston engine and an unmanned helicopter.
Background
In recent decades, along with the rapid development of composite materials, power systems, sensors and electronic technologies, particularly the development of flight control technologies, unmanned helicopters have been rapidly developed. At present, most unmanned helicopters are small helicopters, piston engines are mostly installed, and due to the fact that the small piston engines are simple in structure and free of fuel oil adjusting systems, how to ensure matching of the small piston engines and the small piston engines under any flight condition becomes a research focus.
The analysis of the flight principle of the unmanned helicopter shows that the unmanned helicopter needs to do fixed-height stable flight in the air, and the tension balance and the power balance must be ensured at the same time:
(1) tension balance-that is, the tension generated by the rotor wing is equal to the weight of the unmanned helicopter; tension balancing is typically achieved by adjusting the collective pitch. In the flight control system, the total distance value is changed by closing a height control loop and sensing the change of the height so as to realize height control. Although the flight weight of the unmanned helicopter is not changed greatly in flight, the total distance value of the unmanned helicopter is different under the same weight and different flight speeds due to the unique aerodynamic characteristics of the rotor wing;
(2) power balance-i.e. the power generated by the engine is equal to the required power N of the unmanned helicopterXU. Therefore, to ensure power balance, the required power of the unmanned helicopter and the available power of the engine must be accurately given. Required power N of unmanned helicopterXUDepending on the weight, flying speed, flying height, atmospheric temperature and other factors of the unmanned helicopter; if the weight, the flying height and the atmospheric temperature of the unmanned helicopter are constant, the power N is requiredXUDepending only on the flight speed. Available power N of engineFADepending on engine speed, throttle opening, flight altitude, atmospheric temperature and humidity; likewise, if the engine speed, the flight altitude, the atmospheric temperature and the humidity are constant, the power N is availableFADepending only on the throttle opening.
Therefore, how to realize the balance of tension and power at the same time under any flight condition is the key for matching the piston engine with the unmanned helicopter.
Disclosure of Invention
The invention aims to provide a flight matching method of a piston engine and an unmanned helicopter, which is a method for correctly matching the piston engine and the unmanned helicopter so as to ensure the safe flight of the unmanned helicopter.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the invention provides a flight matching method of a piston engine and an unmanned helicopter, which comprises the following operation steps:
step S100: judging the flight state of the current unmanned helicopter;
step S200: if the current unmanned helicopter is in a hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure BDA0002319445400000021
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure BDA0002319445400000022
The corresponding relationship of (a);
step S300: if the current unmanned helicopter is in a forward flight state, different forward flight speeds V are passed0Required power N ofXUTotal distance from
Figure BDA0002319445400000023
Relation, finally obtaining the time throttle OIL and the total distance under the front flying state
Figure BDA0002319445400000024
The corresponding relationship of (1).
Further, in the specific operation of step S200, if the current unmanned helicopter is in the hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure BDA0002319445400000025
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure BDA0002319445400000026
The corresponding relation specifically comprises the following operation steps:
step S210: selecting a plurality of flight weights T, and obtaining corresponding total distances through tests or calculation
Figure BDA0002319445400000031
Finally, the total distance is given
Figure BDA0002319445400000032
A relationship curve varying with flight weight T;
step S220: selecting a plurality of flight weights T, and obtaining corresponding required power N through test or calculationXUFinally, the required power N is givenXUA relationship curve varying with flight weight T;
step S230: according to the required power NXUAvailable power NFAThen calls available power NFAAnd finally, obtaining the accelerator OIL and the total distance in relation with the OIL curve
Figure BDA0002319445400000033
The corresponding relationship of (1).
Further, in the specific operation of step S300, if the current unmanned helicopter is in the forward flight state, the current unmanned helicopter passes through different forward flight speeds V0Required power N ofXUTotal distance from
Figure BDA0002319445400000034
Relation, finally obtaining the time throttle OIL and the total distance under the front flying state
Figure BDA0002319445400000035
The corresponding relation specifically comprises the following operation steps:
step S310: selecting a plurality of flight speeds V0The corresponding total distance is obtained through experiment or calculation
Figure BDA0002319445400000036
Finally, the total distance is given
Figure BDA0002319445400000037
With flying speed V0A changing relationship curve;
step S320: selecting a plurality of flight speeds V0，
Obtaining different front flight speeds V through test flight or calculation0Power required by hour NXUFinally, the required power N is obtainedXUFlying speed V0A relation curve;
step S330: according to the required power NXUAvailable power NFAThen calls available power NFAAnd finally, obtaining the accelerator OIL and the total distance in relation with the OIL curve
Figure BDA0002319445400000038
The corresponding relationship of (1).
Further, in step S200, the operation processIn the middle, the flying weight T and the total distance are stored in real time
Figure BDA0002319445400000039
Relationship curve, flight weight T and required power NXURelation curve, available power NFAThe relation with the OIL curve and the final calculation of the throttle OIL and the total distance
Figure BDA00023194454000000310
The corresponding relationship of (1).
Further, during the operation of step S300, the front fly speed V is saved in real time0Total distance from
Figure BDA0002319445400000041
Relation curve, forward flying velocity V0And the required power NXURelation curve, available power NFAThe relation with the OIL curve and the final calculation of the throttle OIL and the total distance
Figure BDA0002319445400000042
The corresponding relationship of (1).
According to the flight matching method of the piston engine and the unmanned helicopter, provided by the embodiment of the invention, the flight state is judged and identified in the flight process, and the accelerator OIL and the total distance are carried out according to the actual flight state
Figure BDA0002319445400000043
Reasonable control is carried out; before control, however, it is necessary to determine whether the current flight state is a hovering state or a forward flight state; the two flight states have respective control methods; for example: if the current unmanned helicopter is in a hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure BDA0002319445400000044
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure BDA0002319445400000045
The corresponding relationship of (a); for example: if no person is present to rise verticallyWhen the aircraft is in the forward flight state, the aircraft passes through different forward flight speeds V0Required power N ofXUTotal distance from
Figure BDA0002319445400000046
Relation, finally obtaining the time throttle OIL and the total distance under the front flying state
Figure BDA0002319445400000047
The corresponding relationship of (1).
Through analysis, the flight matching method of the piston engine and the unmanned helicopter provided by the embodiment of the invention guarantees the balance of the full-aircraft tension and the power balance through the effective coordination control of the accelerator and the collective pitch, so that the flight accident of the piston type unmanned helicopter caused by improper control is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a flow chart of a method of flight matching of a piston engine with an unmanned helicopter in an embodiment of the present invention;
FIG. 2 is a logic diagram of the relationship between total distance and an accelerator when hovering in the flight matching method of the piston engine and the unmanned helicopter according to the embodiment of the invention;
FIG. 3 is a logical diagram of the relationship between total distance and throttle during forward flight in the flight matching method of the piston engine and the unmanned helicopter in the embodiment of the invention;
fig. 4 is a composite relational graph of a logical graph of a relation between a total distance during hovering and an accelerator and a logical graph of a relation between a total distance during forward flight and an accelerator in the flight matching method of the piston engine and the unmanned helicopter according to the embodiment of the present invention.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present 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.
In the description of the present invention, it should be noted that "connected" is to be understood broadly, for example, it may be fixed, detachable, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The present invention will be described in further detail below with reference to specific embodiments and with reference to the attached drawings.
Referring to fig. 1, the invention provides a flight matching method of a piston engine and an unmanned helicopter, which comprises the following operation steps:
step S100: judging the flight state of the current unmanned helicopter;
step S200: if the current unmanned helicopter is in a hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure BDA0002319445400000061
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure BDA0002319445400000062
The corresponding relationship of (a);
step S300: if the current unmanned helicopter is in a forward flight state, different forward flight speeds V are passed0Required power N ofXUTotal distance from
Figure BDA0002319445400000063
Relation, finally obtaining the accelerator OIL and in the front flying stateTotal distance
Figure BDA0002319445400000064
The corresponding relationship of (1).
Further, in the specific operation of step S200, if the current unmanned helicopter is in the hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure BDA0002319445400000067
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure BDA0002319445400000066
The corresponding relation specifically comprises the following operation steps:
step S210: selecting a plurality of flight weights T, and obtaining the flight weights T and the total distance through trial flight or calculation
Figure BDA0002319445400000065
A relationship curve (e.g., curve c in fig. 2);
step S220: selecting a plurality of flight weights T, and obtaining the flight weights T and the required power N through trial flight or calculationXUA relation curve (e.g., curve a in fig. 2);
step S230: according to the required power NXUAvailable power NFAThen calls available power NFAThe relationship between the OIL curve and the OIL curve (such as the b curve in fig. 2) is finally obtained
Figure BDA00023194454000000610
The corresponding relationship (d-curve in fig. 2).
It should be noted that, in the specific technical solution, the required power N under different flight weights T can be obtained through balance calculation or ground mooring tests of different flight weights T when hoveringXUAnd total distance
Figure BDA00023194454000000611
A relationship; then, the power of the engine of the current unmanned helicopter is calculated or tested to obtain the enginePower NFAA relationship of variation with the throttle OIL; due to stable suspension, NXU＝NFAThus by the required power NXUAnd total distance
Figure BDA0002319445400000069
Relation to Engine Power NFAThe change relation along with the accelerator OIL is converted, so that the accelerator OIL and the total distance are obtained
Figure BDA0002319445400000068
A one-to-one correspondence relationship of;
the specific mode is as follows: firstly, selecting N flight weights T → calculating to obtain corresponding NXU(FIG. 2(a)) and collective pitch
Figure BDA0002319445400000074
(FIG. 2(c)) → according to NXU＝NFA(curve a in fig. 2), curve b in fig. 2)) is at NFAin-OIL Curve, n OIL curves (b curve in FIG. 2) → Total Range and throttle (OIL E &)
Figure BDA0002319445400000071
) Relationship (d-curve in fig. 2).
Further, in the specific operation of step S300, if the current unmanned helicopter is in the forward flight state, the current unmanned helicopter passes through different forward flight speeds V0Required power N ofXUTotal distance from
Figure BDA0002319445400000073
Relation, finally obtaining the time throttle OIL and the total distance under the front flying state
Figure BDA0002319445400000072
The corresponding relation specifically comprises the following operation steps:
step S310: selecting a plurality of forward flight speeds V0Obtaining the front flying speed V according to test flying or calculation0Total distance from
Figure BDA0002319445400000076
A relationship curve (e.g., curve c in fig. 3);
step S320: selecting a plurality of forward flight speeds V0Obtaining the front flying speed V according to test flying or calculation0And the required power NXUA relation curve (e.g., curve a in fig. 3);
step S330: according to the required power NXUAvailable power NFAThen calls available power NFAThe relationship between the OIL curve and the OIL curve (e.g. b curve in fig. 3) is finally obtained
Figure BDA0002319445400000075
The corresponding relationship (d-curve in fig. 3).
It should be noted that, in a specific technical solution, for a situation where the current unmanned helicopter is in a forward flight state, the final correspondence between the throttle OIL and the collective pitch may be calculated through a forward flight speed-collective pitch relationship curve or the like.
The above comparison of the total distance-throttle curves in the hovering state and the forward flying state can be found by combining the accompanying drawings 2 and 3: two different collective-throttle curves at hover and forward flight are derived above, and for ease of comparison, the d-curve in FIG. 2 and the d-curve in FIG. 3 are drawn in a composite fashion, see FIG. 4. As can be seen from fig. 4, the difference between the two curves becomes larger as the collective pitch decreases. He reflects the flight control logic as follows: at V <100km/h, the larger the speed, the smaller the total distance and the smaller the power demand, the larger and larger the difference in this case compared to the value at hover. Therefore, to ensure that the height of the aircraft does not fall during hovering and flying, two lines are adopted for simultaneous coordination control.
Further, in the operation process of step S200, the flight weight T and the collective pitch are stored in real time
Figure BDA0002319445400000084
Relationship curve, flight weight T and required power NXURelation curve, available power NFARelation with OIL curve and finally obtained accelerator OIL and total distance
Figure BDA0002319445400000083
The corresponding relationship of (1).
Further, during the operation of step S300, the front fly speed V is saved in real time0Total distance from
Figure BDA0002319445400000081
Relation curve, forward flying velocity V0And the required power NXURelation curve, available power NFAThe relation with the OIL curve and the final calculation of the throttle OIL and the total distance
Figure BDA0002319445400000082
The corresponding relationship of (1).
It should be noted that, in the specific technical scheme, the relationship curve and the corresponding relationship data are stored in real time, so that the flight data of the unmanned helicopter can be stored, the corresponding flight data relationship can be called conveniently in the future, and meanwhile, a reliable reference is provided for analyzing the performance of the unmanned helicopter.
In addition, if the relationship curve between the collective pitch and the accelerator obtained when the unmanned helicopter performs the test flight test in plain areas (such as Beijing areas), the test result may be different from that in other areas; for example, if an unmanned helicopter is tested in a pilot area (such as Lanzhou region), the calculation or the test is carried out again to obtain a relation curve between the total distance and the throttle of the area; in the actual flight of the unmanned helicopter, due to the fact that flight weight, atmospheric conditions, flight height and the like are different, the required power of the helicopter and the available power of an engine are also different, two total distances and an accelerator curve cannot cover all flight states, and the difference is always a little and is solved through self adjustment of a flight control system, for example, high-altitude flight is realized, and small-height change can be realized through fine adjustment of the total distances.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims (3)

1. A flight matching method of a piston engine and an unmanned helicopter is characterized by comprising the following operation steps:
judging the flight state of the current unmanned helicopter;
if the current unmanned helicopter is in a hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure FDA0002957795290000011
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure FDA0002957795290000012
The corresponding relationship of (a);
if the current unmanned helicopter is in a forward flight state, different forward flight speeds V are passed0Required power N ofXUTotal distance from
Figure FDA0002957795290000013
Relation, finally obtaining the accelerator OIL and the total distance in the front flying state
Figure FDA0002957795290000014
The corresponding relationship of (a);
if the current unmanned helicopter is in a hovering state, the required power N under different flight weights T is passedXUAnd total distance
Figure FDA0002957795290000015
Relation is obtained to finally obtain the accelerator OIL and the total distance
Figure FDA0002957795290000016
The specific operation steps are as follows:
selecting a plurality of flight weights T, and obtaining the total distance of different flight weights T through tests or calculation
Figure FDA0002957795290000017
Finally, the total distance is obtained
Figure FDA0002957795290000018
A relationship curve varying with flight weight T;
selecting a plurality of flight weights T, and obtaining the required power N at different flight weights T through tests or calculationXUFinally, the required power N is obtainedXUA relationship curve varying with flight weight T;
according to the required power NXUAvailable power NFAThen calls available power NFAAnd finally, obtaining the accelerator OIL and the total distance in relation with the OIL curve
Figure FDA0002957795290000019
The corresponding relationship of (a);
if the current unmanned helicopter is in a forward flight state, different forward flight speeds V are passed0Required power N ofXUTotal distance from
Figure FDA00029577952900000110
Relation, finally obtaining the accelerator OIL and the total distance in the front flying state
Figure FDA00029577952900000111
The corresponding relation specifically comprises the following operation steps:
selecting a plurality of forward flight speeds V0Then obtaining different front flying speeds V through test flying or calculation0Total distance of lower
Figure FDA00029577952900000112
Finally, the total distance is obtained
Figure FDA00029577952900000113
Flying speed V0A changing relationship curve;
selecting a plurality of forward flight speeds V0Then obtaining different front flying speeds V through test flying or calculation0Required power N ofXUFinally, the required power N is obtainedXUFlying speed V0A changing relationship curve;
according to the required power NXUAvailable power NFAThen calls available power NFAAnd finally, obtaining the accelerator OIL and the total distance in relation with the OIL curve
Figure FDA0002957795290000021
The corresponding relationship of (1).
2. A method of matching a piston engine to the flight of an unmanned helicopter as claimed in claim 1, characterized by storing the flight weight T and the collective pitch in real time
Figure FDA0002957795290000022
Relationship curve, flight weight T and required power NXURelation curve, available power NFAThe relation with the OIL curve and the final calculation of the throttle OIL and the total distance
Figure FDA0002957795290000023
The corresponding relationship of (1).
3. A method of flight matching of a piston engine and an unmanned helicopter according to claim 1, characterized by storing the forward flight velocity V in real time0Total distance from
Figure FDA0002957795290000024
Relation curve, forward flying velocity V0And the required power NXURelation curve, available power NFAThe relation with the OIL curve and the final calculation of the throttle OIL and the total distance
Figure FDA0002957795290000025
Corresponding to (2)Is described.
CN201911292076.5A 2019-12-16 2019-12-16 Flight matching method of piston engine and unmanned helicopter Active CN110920905B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911292076.5A CN110920905B (en) 2019-12-16 2019-12-16 Flight matching method of piston engine and unmanned helicopter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911292076.5A CN110920905B (en) 2019-12-16 2019-12-16 Flight matching method of piston engine and unmanned helicopter

Publications (2)

Publication Number Publication Date
CN110920905A CN110920905A (en) 2020-03-27
CN110920905B true CN110920905B (en) 2021-06-01

Family

ID=69862666

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911292076.5A Active CN110920905B (en) 2019-12-16 2019-12-16 Flight matching method of piston engine and unmanned helicopter

Country Status (1)

Country Link
CN (1) CN110920905B (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112141350B (en) * 2020-09-25 2022-12-30 中国直升机设计研究所 Ground driving method of helicopter
CN112965540B (en) * 2021-03-31 2022-04-22 南京航空航天大学 Unmanned helicopter piston engine rotating speed control method based on fuzzy active disturbance rejection

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105314120B (en) * 2014-07-31 2017-09-29 深圳市大疆创新科技有限公司 A kind of control method, device and the aircraft of aircraft autostop
GB2566095B (en) * 2017-09-04 2019-10-02 Artemis Intelligent Power Ltd Hydraulic multi-rotor aerial vehicle
CN109533351A (en) * 2018-11-15 2019-03-29 中国直升机设计研究所 A kind of unmanned helicopter piston engine starting clutch control method
CN110001949A (en) * 2019-03-13 2019-07-12 陈铭 A kind of compound rotation unmanned helicopter of close coupled type

Also Published As

Publication number Publication date
CN110920905A (en) 2020-03-27

Similar Documents

Publication Publication Date Title
US20200257313A1 (en) Airplane Climb Thrust Optimization
US8793040B2 (en) Climb-optimized auto takeoff system
CN110920905B (en) Flight matching method of piston engine and unmanned helicopter
CN111717411B (en) Method for correcting cruise thrust increment based on test flight data standard weight
US20190193866A1 (en) Method and assistance system for detecting a degradation of light performance
US20190304206A1 (en) Vehicle anomalous behavior detection
US10759544B2 (en) Methods and systems for controlling thrust produced by a plurality of engines on an aircraft for assisting with certain flight conditions
US4884205A (en) Method and apparatus for limiting adverse yaw-induced roll during engine failure in multiengine aircraft
CN114004021B (en) Cruise fuel flow calculation method for performance management of flight management system
CN113408200B (en) Aviation equipment vibration environment analysis and prediction method
CN112149299B (en) Optimized analysis method for test flight task for data packet development of flight simulator
CN116331510A (en) Speed constraint separation method based on solid rocket engine booster aircraft
Parsons et al. F-35 aerodynamic performance verification
CN115200826B (en) Leeward vortex breaking attack angle correction method for backpack type air inlet small-aspect-ratio flying wing layout
Kratochvíl Flutter problems of electrically powered aircraft
US11803197B2 (en) Systems and methods for controlling a flight boundary of an aircraft
CN117252109B (en) Aeroengine stability analysis method and system based on data processing
Samuelsson Evaluation of Stability and Flying Qualities of a Light Unmanned Aerial Vehicle (UAV)
EP4328547A1 (en) Training data for air data estimation in aircraft
Bingaman Unmanned aircraft and the applicability of military flying qualities standards
CN115203821A (en) Fuel consumption model processing method and system based on flight control data table and storage medium
Bilger et al. In-flight structural dynamic characteristics of the XV-15 tilt-rotorresearch aircraft
Giacomelli et al. Optimization of High lift device system deployment for takeoff performance
Murad MODELING OF AIRCRAFT TRIM PERFORMANCE PARAMETER WITH ANFIS
San Hon et al. Development of a flight simulator for conceptual aircraft design and sizing

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