Design of Flight Performance Calculation Component for UAV Mission Planning Based on Performance Data Package

Install thrust propeller and wings to coaxial helicopter, constitute a compound helicopter. Compound helicopter has greater speed, farther voyage, while retaining advantages of the helicopter which can take off and land vertically without runway.Preliminary design is an important stage in compound helicopter design work. It covers aerodynamic analysis, flight mechanics analysis, dynamic analysis, flight performance calculation and weight characteristics calculation. These aspects intertwined, which deepened the complexity of the preliminary design. Use genetic algorithms to optimize the design of the general parameters. Under constraint conditions of meeting flight performance requirements, calculate the general parameters which make the objective function optimal. Objective functions usually include weight efficiency and Miri’s criterion. This method without repeated design can shorten development cycle, improve economy and ensure design quality.

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Flight Performance Estimation of Bionic Flapping-Wing Micro Air Vehicle

Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University ◽

10.1051/jnwpu/20183640636 ◽

2018 ◽

Vol 36 (4) ◽

pp. 636-643

Author(s):

Wenqing Yang ◽

Bifeng Song ◽

Guanglin Gao

Keyword(s):

High Speed ◽

Angle Of Attack ◽

Estimation Method ◽

Flapping Wing ◽

Micro Air Vehicle ◽

Performance Estimation ◽

Estimation Methods ◽

Flight Performance ◽

Air Vehicle ◽

Performance Calculation

Bionic flapping-wing micro air vehicle(MAV) has received worldwide attention.The flight performance calculation is an important step in the conceptual design.The differences in performance estimation methods between the flapping-wing and conventional fixed-wing aircraft are analyzed.Based on the results of the aerodynamic estimation and wind tunnel experimental measurement, the flight performance estimation method of flapping-wing micro air vehicle is proposed, and the performance of level flight, climbing, and duration are calculated and analyzed.The frequency represents the accelerator in a certain extent, while the frequency is coupled with lift and thrust.The results show that there may be two stable cruising states at certain frequencies, one is the small angle of attack with high speed, the other is the small speed with big angle of attack, and the two states have different power consumption.According to the parameters of the vehicle, climbing performance and duration performance can be obtained.The speed versus power characteristic curve is a U shape, minimum slope of the U curve can be obtained through the mapping method to calculate the farthest flight speed, and the minimum velocity of U-shaped curve is the speed for longest duration.The proposed flight performance calculation method can be used to evaluate the flight capability of bionic micro flapping-wing air vehicle.

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Orbiting Astronomical Observatory Heat Pipe Flight Performance Data

Thermophysics and Spacecraft Thermal Control ◽

10.2514/5.9781600865084.0445.0465 ◽

1974 ◽

pp. 445-465 ◽

Cited By ~ 1

Keyword(s):

Heat Pipe ◽

Astronomical Observatory ◽

Performance Data ◽

Flight Performance

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Estimating Rebound Effects for International Air Routes in Korea: Using Airlines’ Flight Performance Data on Four Europe Routes

The Journal of Korean Public Policy ◽

10.37103/kapp.23.2.4 ◽

2021 ◽

Vol 23 (2) ◽

pp. 95-123

Author(s):

Sang-Yong Han

Keyword(s):

Performance Data ◽

Flight Performance ◽

Rebound Effects

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Effects of Chemical Defense Antidotes (Atropine) on Aviator Performance (Simulated Flight and Zero Input Tracking Analyzer)

Proceedings of the Human Factors Society Annual Meeting ◽

10.1177/154193128603001211 ◽

1986 ◽

Vol 30 (12) ◽

pp. 1187-1191

Author(s):

Lewis W. Stone ◽

Ronald R. Simmons ◽

Heber D. Jones ◽

David J. Carter ◽

Roger S. Christiansen

Keyword(s):

Chemical Defense ◽

Saline Solution ◽

Atropine Sulfate ◽

Performance Data ◽

Biological Warfare ◽

Chemical Agent ◽

Flight Performance ◽

Paper Briefly ◽

Psychomotor Effects ◽

Systematic Program

Army aviation is at serious risk in chemical and biological warfare environments. One of the potential countermeasures for aviators against the chemical threat is the development of antidote and pretreatment drugs. Just as the chemical agent carries the threat of degrading aviator performance, antidote and pretreatment drugs could independently produce problems either alone or in combination with an agent. This paper briefly outlines part of the first phase of a systematic program using controlled, simulated flight conditions and a Zero Input Tracking Analyzer (ZITA) to identify and measure flight performance and psychomotor effects of unchallenged atropine (one of the chemical defense antidotes) on aviators. Each of 12 U.S. Army helicopter aviators voluntarily received 3 dosages: 0 mg (saline solution), 2 mg of atropine sulfate, and 4 mg of atropine sulfate. Results indicate that simulator flight performance data did prove to be sensitive in identifying and measuring effects of 4 mg of atropine. Additionally, some ZITA tests showed a statistically significant degradation with the 4 mg dosage.

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The Specific Fuel Consumption of Aircraft Engines (TSFC versus PSFC)

10.31224/osf.io/gyt7u ◽

2021 ◽

Author(s):

Dieter Scholz

Keyword(s):

Fuel Consumption ◽

Aircraft Engine ◽

Specific Fuel Consumption ◽

Flight Performance ◽

Aircraft Engines ◽

Minimum Drag ◽

Extended Approach ◽

Range Equation ◽

Performance Calculation ◽

Fundamental Consideration

From a fundamental consideration of the efficiency (eta = P_out / P_in) it already follows that the power-specific fuel consumption, PSFC or c_P of an aircraft engine should be approximately constant, while c = c_P * V applies to the thrust-specific fuel consumption, TSFC or c in a first approach. Obviously, fuel is consumed already at static thrust (V=0). For this reason the thrust-specific fuel consumption needs an extended approach c = c_a + c_b * V. Breguet's range equation can certainly be described with a constant thrust-specific fuel consumption c, if c is determined for the cruise speed in question. However, this leads to an error if you want to use it to calculate an optimal flight speed in a flight performance calculation. It is recommended (for a first simple consideration) to write Breguet's range equation for jets with a constant power-specific fuel consumption c_P. This then leads to an optimal cruising speed for maximum range at minimum drag (md) V_md instead of 1.316 * V_md as it is determined with the "classic" derivation. For more detailed considerations, the "Herrmann model" should replace the simple equation c = c_a + c_b * V.

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Metoda Short Takeoff Landing (Studi Kasus Prestasi Terbang Takeoff-Landing Pesawat Udara Turbo Prop CN235)

WARTA ARDHIA ◽

10.25104/wa.v41i2.144.49-58 ◽

2017 ◽

Vol 41 (2) ◽

pp. 49

Author(s):

Sayuti Syamsuar

Keyword(s):

Critical Condition ◽

Aerospace Industry ◽

Aerodynamic Performance ◽

Performance Data ◽

Flight Performance ◽

Aircraft Structure ◽

Trade Off ◽

Study Case ◽

Full Throttle ◽

Obstacle Height

The aircraft category of Short Take-Off Landing, in general, including lightweight aircrafts with take-off weight between 20.000 lb (9.072 kg) and 50.000 lb (22.680 kg) and capable in exceeding 50 ft (15 m) obstacle height with only 1.500 ft (450 m) of take-off and landing distance. Thera are, at least, three general requirements that have to be considered in order to develop this category of aircraft; high aerodynamic performance, powerful engine, qualified skill of pilot, and also the strength of aircraft structure that can sustain heavy load.As for the study case, the author used the flight performance data of CN235-100 (serial N-16) Short Field Landing with 230 flap that was tested in Indonesian Aerospace Industry in 1996 for its trade-off performance. There was also rejected take-off or accelerate stop distance test with 100 flap and full throttle where one of the engine, then suddenly, shut down in order to achieve critical condition and later the power of the another engine being reduced by the pilot so that the aircraft can stop at the end of the runway. Several pilot recommendations are given in the conclusion chapter. Keywords: short take-off landing, height, distance, performance, engine, pilot, flap. Pesawat dengan kategori Short Take-Off Landing pada umumnya adalah pesawat ringan yang mempunyai berat take-off antara 20.000 lb (9.072 kg) hingga 50.000 lb (22.680 kg) dengan kemampuan melewat irintangan setinggi 50 ft (15 m) untuk jarak take-off dan landing sejauh 1.500 ft (450 m). Pengembangan pesawat dengan kategori tersebut perlu memperhatikan tiga persyaratan umum yaitu kemampuan aerodinamika yang tinggi, tenaga mesin yang besar, dan teknik pilot yang baik yang disertai dengan kekuatan struktur yang mampu menahan beban berat. Pada studi kasus ini, penulis menggunakan data prestasi terbang Short Field Landing pesawat CN235-100 (serial N-16) dengan menggunakan flap 230 pada saat pengujian performance trade-off di PT Dirgantara Indonesia pada tahun 1996. Pengujian tersebut juga termasuk uji rejected take-off atau accelerate stop distance dengan menggunakan flap 100 pada tenaga penuh dimana kemudian salah satu mesin dimatikan untuk mencapai kondisi kritis dan pilot mengurangi daya propulsi mesin lainnya untuk dapat berhenti di ujung landasan. Beberapa rekomendasi pilot diberikan pada bagian kesimpulan. Kata kunci: short takeoff landing, tinggi, jarak, performance, engine, pilot, flap.

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